**Centrifugal compressors**, sometimes called **impeller compressors** or **radial compressors**, are a sub-class of dynamic axisymmetric work-absorbing turbomachinery.^{ [1] }

- Components of a simple centrifugal compressor
- Inlet
- Centrifugal impeller
- Diffuser
- Collector
- Historical contributions, the pioneers
- Aerodynamic-thermodynamic domain
- Physical-mechanical domain
- Partial timeline of historical contributions
- Turbomachinery similarities
- Similarities to axial compressor
- Centrifugal fan
- Squirrel-Cage fan
- Centrifugal pump
- Radial turbine
- Turbomachinery using centrifugal compressors
- Standards
- Applications
- Theory of operation
- Performance
- Performance maps
- Surge
- Maximum flow line versus choke
- Other operating limits
- Dimensional analysis
- Buckingham Π theorem
- Classic turbomachinery similitude
- Other dimensionless combinations
- Affinity laws
- Aero-thermodynamic fundamentals
- Conservation of mass
- Conservation of momentum
- Conservation of energy
- Equation of state
- Pros and cons
- Structural mechanics, manufacture and design compromise
- See also
- References
- External links

They achieve pressure rise by adding energy to the continuous flow of fluid through the rotor/impeller. The following equation shows this specific energy input. A substantial portion of this energy is kinetic which is converted to increased potential energy/static pressure by slowing the flow through a diffuser. The static pressure rise in the impeller may roughly equal the rise in the diffuser.

Equation-0.1

^{ [1] }- where the control volume nomenclature (illustrated in Figure-0.4) is:
- 1 subscript, is the impeller inlet location, station1
- 2 subscript, is the impeller discharge/exit location, station2
- H is the energy input per unit mass, units=(LP/m)
- ω is the impeller's rotation speed, units=(radians/t)
- R is the radius of specified location, units=(L)
- C is velocity of fluid/gas velocity at specified location, units=(L/t)
- θ is the tangential vector component in polar coordinate system

A simple centrifugal compressor stage has four components (listed in order of throughflow): inlet, impeller/rotor, diffuser, and collector.^{ [1] } Figure 1.1 shows each of the components of the flow path, with the flow (working gas) entering the centrifugal impeller axially from left to right. This turboshaft (or turboprop) impeller is rotating counter-clockwise when looking downstream into the compressor. The flow will pass through the compressors from left to right.

The simplest inlet to a centrifugal compressor is typically a simple pipe. Depending upon its use/application inlets can be very complex. They may include other components such as an inlet throttle valve, a shrouded port, an annular duct (see Figure 1.1), a bifurcated duct, stationary guide vanes/airfoils used to straight or swirl flow (see Figure 1.1), movable guide vanes (used to vary pre-swirl adjustably). Compressor inlets often include instrumentation to measure pressure and temperature in order to control compressor performance.

Bernoulli's fluid dynamic principle plays an important role in understanding vaneless stationary components like an inlet. In engineering situations assuming adiatice flow, this equation can be written in the form:

Equation-1.1

where:

- 0 is the inlet of the compressor, station 0
- 1 is the inlet of the impeller, station 1
- p is the pressure
- ρ is the density and indicates that it is a function of pressure
- is the flow speed
- γ is the ratio of the specific heats of the fluid

The identifying component of a centrifugal compressor stage is the centrifugal impeller rotor. Impellers are designed in many configurations including "open" (visible blades), "covered or shrouded", "with splitters" (every other inducer removed), and "w/o splitters" (all full blades). Figures 0.1, 1.2.1, and 1.3 show three different open full inducer rotors with alternating full blades/vanes and shorter length splitter blades/vanes. Generally, the accepted mathematical nomenclature refers to the leading edge of the impeller with subscript 1. Correspondingly, the trailing edge of the impeller is referred to as subscript 2.

As working-gas/flow passes through the impeller from stations 1 to 2, the kinetic and potential energy increase. This is identical to an axial compressor with the exception that the gases can reach higher energy levels through the impeller's increasing radius. In many modern high-efficiency centrifugal compressors the gas exiting the impeller is traveling near the speed of sound.

Most modern high-efficiency impellers use "backsweep" in the blade shape.^{ [2] }^{ [3] }^{ [4] }

A derivation of the general Euler equations (fluid dynamics) is Euler's pump and turbine equation, which plays an important role in understanding impeller performance. This equation can be written in the form:

Equation-1.2 (see Figures 1.2.2 and 1.2.3 illustrating impeller velocity triangles)

where:

- 1 subscript 1 is the impeller leading edge (inlet), station 1
- 2 subscript 2 is the impeller trailing edge (discharge), station 2
- E is the energy added to the fluid
- g is the acceleration due to gravity
- u is the impeller's circumferencal velocity, units velocity
- w is the velocity of flow relative to the impeller, units velocity
- c is the absolute velocity of flow relative to stationary, units velocity

- Figuer1.2.2 -Inlet velocity triangles for centrifugal compressor impeller
- Figuer1.2.3 - Exit velocity triangles for centrifugal compressor impeller

The next component, downstream of the impeller within a simple centrifugal compressor may the diffuser. ^{ [5] }^{ [4] } The diffuser converts the flow's kinetic energy (high velocity) into increased potential energy (static pressure) by gradually slowing (diffusing) the gas velocity. Diffusers can be vaneless, vaned, or an alternating combination. High-efficiency vaned diffusers are also designed over a wide range of solidities from less than 1 to over 4. Hybrid versions of vaned diffusers include wedge (see Figure 1.3), channel, and pipe diffusers. Some turbochargers have no diffuser. Generally accepted nomenclature might refer to the diffuser's lead edge as station 3 and the trailing edge as station 4.

Bernoulli's fluid dynamic principle plays an important role in understanding diffuser performance. In engineering situations assuming adiatice flow, this equation can be written in the form:

Equation-1.3

where:

- 2 is the inlet of the diffuser, station 2
- 4 is the discharge of the diffuser, station 4
- (see inlet above.)

The collector of a centrifugal compressor can take many shapes and forms. ^{ [5] }^{ [4] } When the diffuser discharges into a large empty circumferentially (constant area) chamber, the collector may be termed a *Plenum*. When the diffuser discharges into a device that looks somewhat like a snail shell, bull's horn, or a French horn, the collector is likely to be termed a *volute* or *scroll*.

When the diffuser discharges into an annular bend the collector may be referred to as a *combustor inlet* (as used in jet engines or gas turbines) or a *return-channel* (as used in an online multi-stage compressor). As the name implies, a collector's purpose is to gather the flow from the diffuser discharge annulus and deliver this flow downstream into whatever component the application requires. The collector or discharge pipe may also contain valves and instrumentation to control the compressor. In some applications, collectors will diffuse flow (converting kinetic energy to static pressure) far less efficiently than a diffuser.^{ [6] }

Bernoulli's fluid dynamic principle plays an important role in understanding diffuser performance. In engineering situations assuming adiatice flow, this equation can be written in the form:

Equation-1.4

where:

- 4 is the inlet of the diffuser, station 4
- 5 is the discharge of the diffuser, station 5
- (see inlet above.)

Over the past 100 years, applied scientists including Stodola (1903, 1927–1945),^{ [7] } Pfleiderer (1952),^{ [8] } Hawthorne (1964),^{ [9] } Shepherd (1956),^{ [1] } Lakshminarayana (1996),^{ [10] } and Japikse (many texts including citations),^{ [2] }^{ [11] }^{[ citation needed ]}^{ [12] } have educated young engineers in the fundamentals of turbomachinery. These understandings apply to all dynamic, continuous-flow, axisymmetric pumps, fans, blowers, and compressors in axial, mixed-flow and radial/centrifugal configurations.

This relationship is the reason advances in turbines and axial compressors often find their way into other turbomachinery including centrifugal compressors. Figures 1.1 and 1.2 illustrate the domain of turbomachinery with labels showing centrifugal compressors.^{ [13] }^{ [14] } Improvements in centrifugal compressors have not been achieved through large discoveries. Rather, improvements have been achieved through understanding and applying incremental pieces of knowledge discovered by many individuals.

Figure 2.1 (shown right) represents the aero-thermo domain of turbomachinery. The horizontal axis represents the energy equation derivable from The first law of thermodynamics.^{ [1] }^{ [14] } The vertical axis, which can be characterized by Mach Number, represents the range of fluid compressibility (or elasticity).^{ [1] }^{ [14] } The Z-axis, which can be characterized by Reynolds number, represents the range of fluid viscosities (or stickiness).^{ [14] } Mathematicians and physicists who established the foundations of this aero-thermo domain include:^{ [15] }^{ [16] } Isaac Newton, Daniel Bernoulli, Leonhard Euler, Claude-Louis Navier, George Stokes, Ernst Mach, Nikolay Yegorovich Zhukovsky, Martin Kutta, Ludwig Prandtl, Theodore von Kármán, Paul Richard Heinrich Blasius, and Henri Coandă.

Figure 2.2 (shown right) represents the physical or mechanical domain of turbomachinery. Again, the horizontal axis represents the energy equation with turbines generating power to the left and compressors absorbing power to the right.^{ [1] }^{ [14] } Within the physical domain the vertical axis differentiates between high speeds and low speeds depending upon the turbomachinery application.^{ [1] }^{ [14] } The Z-axis differentiates between axial-flow geometry and radial-flow geometry within the physical domain of turbomachinery.^{ [1] }^{ [14] } It is implied that mixed-flow turbomachinery lie between axial and radial.^{ [1] }^{ [14] } Key contributors of technical achievements that pushed the practical application of turbomachinery forward include:^{ [15] }^{ [16] } Denis Papin,^{ [17] } Kernelien Le Demour, Daniel Gabriel Fahrenheit, John Smeaton, Dr. A. C. E. Rateau,^{ [18] } John Barber, Alexander Sablukov, Sir Charles Algernon Parsons, Ægidius Elling, Sanford Alexander Moss, Willis Carrier, Adolf Busemann, Hermann Schlichting, Frank Whittle and Hans von Ohain.

<1689 | Early turbomachines | Pumps, blowers, fans |

1689 | Denis Papin | Origin of the centrifugal compressor |

1754 | Leonhard Euler | Euler's "Pump & Turbine" equation |

1791 | John Barber | First gas turbine patent |

1899 | A. C. E. Rateau | First practical centrifugal compressor |

1927 | Aurel Boleslav Stodola | Formalized "slip factor" |

1928 | Adolf Busemann | Derived "slip factor" |

1937 | Frank Whittle and Hans von Ohain, independently | First gas turbine using a centrifugal compressor |

>1970 | Modern turbomachines | 3D-CFD, rocket turbo-pumps, heart assist pumps, turbocharged fuel cells |

Centrifugal compressors are similar in many ways to other turbomachinery and are compared and contrasted as follows:

Centrifugal compressors are similar to axial compressors in that they are rotating airfoil-based compressors. Both are shown in the adjacent photograph of an engine with 5 stages of axial compressors and one stage of a centrifugal compressor.^{ [10] }^{[ citation needed ]} The first part of the centrifugal impeller looks very similar to an axial compressor. This first part of the centrifugal impeller is also termed an *inducer*. Centrifugal compressors differ from axials as they use a significant change in radius from inlet to exit of the impeller to produce a much greater pressure rise in a single stage (e.g. 8^{ [19] } in the Pratt & Whitney Canada PW200 series of helicopter engines) than does an axial stage. The 1940s-era German Heinkel HeS 011 experimental engine was the first aviation turbojet to have a compressor stage with radial flow-turning part-way between none for an axial and 90 degrees for a centrifugal. It is known as a mixed/diagonal-flow compressor. A diagonal stage is used in the Pratt & Whitney Canada PW600 series of small turbofans.

Centrifugal compressors are also similar to centrifugal fans of the style shown in the neighboring figure as they both increase the energy of the flow through the increasing radius.^{ [1] } In contrast to centrifugal fans, compressors operate at higher speeds to generate greater pressure rises. In many cases, the engineering methods used to design a centrifugal fan are the same as those to design a centrifugal compressor, so they can look very similar.

For purposes of generalization and definition, it can be said that centrifugal compressors often have density increases greater than 5 percent. Also, they often experience relative fluid velocities above Mach number 0.3^{ [20] } when the working fluid is air or nitrogen. In contrast, fans or blowers are often considered to have density increases of less than five percent and peak relative fluid velocities below Mach 0.3.

Squirrel-Cage fans are primarily used for ventilation. The flow field within this type of fan has internal recirculations. In comparison, a centrifugal fan is uniform circumferentially.

Centrifugal compressors are also similar to centrifugal pumps^{ [1] } of the style shown in the adjacent figures. The key difference between such compressors and pumps is that the compressor working fluid is a gas (compressible) and the pump working fluid is liquid (incompressible). Again, the engineering methods used to design a centrifugal pump are the same as those to design a centrifugal compressor. Yet, there is one important difference: the need to deal with cavitation in pumps.

Centrifugal compressors also look very similar to their turbomachinery counterpart the radial turbine as shown in the figure. While a compressor transfers energy into a flow to raise its pressure, a turbine operates in reverse, by extracting energy from a flow, thus reducing its pressure.^{[ citation needed ]} In other words, power is input to compressors and output from turbines.

As turbomachinery became more common, standards have been created to guide manufacturers to assure end-users that their products meet minimum safety and performance requirements. Associations formed to codify these standards rely on manufacturers, end-users, and related technical specialists. A partial list of these associations and their standards are listed below:

- American Society of Mechanical Engineers:BPVC, PTC.
^{ [21] }^{ [22] } - American Petroleum Institute: API STD 617 8TH ED (E1), API STD 672 5TH ED (2019).
^{ [23] }^{ [24] } - American Society of Heating, Refrigeration, and Airconditioning Engineers: Handbook Fundamentals.
^{ [25] } - Society of Automotive Engineers
^{ [26] } - Compressed Air and Gas Institute
^{ [27] } - International Organization for StandardizationISO 10439, ISO 10442, ISO 18740, ISO 6368, ISO 5389
^{ [28] }

Below, is a partial list of centrifugal compressor applications each with a brief description of some of the general characteristics possessed by those compressors. To start this list two of the most well-known centrifugal compressor applications are listed; gas turbines and turbochargers.^{ [10] }

- In gas turbines and auxiliary power units.
^{ [29] }Ref. Figures 4.1–4.2In their simple form, modern gas turbines operate on the Brayton cycle. (ref Figure 5.1) Either or both axial and centrifugal compressors are used to provide compression. The types of gas turbines that most often include centrifugal compressors include small aircraft engines (i.e. turboshafts, turboprops, and turbofans), auxiliary power units, and micro-turbines. The industry standards applied to all centrifugal compressors used in aircraft applications are set by the relevant civilian and military certification authorities to achieve the safety and durability required in service. Centrifugal impellers used in gas turbines are commonly made from titanium alloy forgings. Their flow-path blades are commonly flank milled or point milled on 5-axis milling machines. When running clearances have to be as small as possible without the impeller rubbing its shroud the impeller is first drawn with its high-temperature, high-speed deflected shape and then drawn in its equivalent cold static shape for manufacturing. This is necessary because the impeller deflections at the most severe running condition can be 100 times larger than the required hot running clearance between the impeller and its shroud.

- In automotive engine and diesel engine turbochargers and superchargers.
^{ [30] }Ref. Figure 1.1Centrifugal compressors used in conjunction with reciprocating internal combustion engines are known as turbochargers if driven by the engine's exhaust gas and turbo-superchargers if mechanically driven by the engine. Standards set by the industry for turbochargers may have been established by SAE.^{ [26] }Ideal gas properties often work well for the design, test and analysis of turbocharger centrifugal compressor performance.

- In pipeline compressors of natural gas to move the gas from the production site to the consumer.
^{ [31] }Centrifugal compressors for such uses may be one- or multi-stage and driven by large gas turbines. Standards set by the industry (ANSI/API, ASME) result in thick casings to achieve a required level of safety. The impellers are often if not always of the covered style which makes them look much like pump impellers. This type of compressor is also often termed an*API-style*. The power needed to drive these compressors is most often in the thousands of horsepower (HP). The use of real gas properties is needed to properly design, test, and analyze the performance of natural gas pipeline centrifugal compressors.

- In oil refineries, natural-gas processing, petrochemical and chemical plants.
^{ [31] }Centrifugal compressors for such uses are often one-shaft multi-stage and driven by large steam or gas turbines. Their casings are termed*horizontally split*if the rotor is lowered into the bottom half during assembly or*barrel*if it has no lengthwise split-line with the rotor being slid in. Standards set by the industry (ANSI/API, ASME) for these compressors result in thick casings to achieve a required level of safety. The impellers are often of the covered style which makes them look much like pump impellers. This type of compressor is also often termed*API-style*. The power needed to drive these compressors is usually in the thousands of HP. Use of real gas properties is needed to properly design, test and analyze their performance.

- Air-conditioning and refrigeration and HVAC: Centrifugal compressors quite often supply the compression in water chillers cycles.
^{ [32] }Because of the wide variety of vapor compression cycles (thermodynamic cycle, thermodynamics) and the wide variety of workings gases (refrigerants), centrifugal compressors are used in a wide range of sizes and configurations. Use of real gas properties is needed to properly design, test and analyze the performance of these machines. Standards set by the industry for these compressors include ASHRAE, ASME & API.

- In industry and manufacturing to supply compressed air for all types of pneumatic tools.
^{ [33] }Centrifugal compressors for such uses are often multistage and driven by electric motors. Inter-cooling is often needed between stages to control air temperature. Road-repair crews and automobile repair garages find screw compressors better adapt to their needs. Standards set by the industry for these compressors include ASME and government regulations that emphasize safety. Ideal gas relationships are often used to properly design, test, and analyze the performance of these machines. Carrier's equation is often used to deal with humidity.

- In air separation plants to manufacture purified end product gases.
^{ [33] }Centrifugal compressors for such uses are often multistage using inter-cooling to control air temperature. Standards set by the industry for these compressors include ASME and government regulations that emphasize safety. Ideal gas relationships are often used to properly design, test, and analyze the performance of these machines when the working gas is air or nitrogen. Other gases require real gas properties.

- In oil field re-injection of high-pressure natural gas to improve oil recovery.
^{ [31] }Centrifugal compressors for such uses are often one-shaft multi-stage and driven by gas turbines. With discharge pressures approaching 700 bar, casings are of the barrel style. Standards set by the industry (API, ASME) for these compressors result in large thick casings to maximize safety. The impellers are often if not always of the covered style which makes them look much like pump impellers. This type of compressor is also often termed*API-style*. The use of real gas properties is needed to properly design, test, and analyze their performance.

In the case where flow passes through a straight pipe to enter a centrifugal compressor, the flow is axial, uniform, and has no vorticity, i.e. swirling motion. As the flow passes through the centrifugal impeller, the impeller forces the flow to spin faster as it gets further from the rotational axis. According to a form of Euler's fluid dynamics equation, known as the * pump and turbine equation *, the energy input to the fluid is proportional to the flow's local spinning velocity multiplied by the local impeller tangential velocity.

In many cases, the flow leaving the centrifugal impeller is traveling near the speed of sound. It then flows through a stationary compressor causing it to decelerate. The stationary compressor is ducting with increasing flow-area where energy transformation takes place. If the flow has to be turned in a rearward direction to enter the next part of the machine, e.g. another impeller or a combustor, flow losses can be reduced by directing the flow with stationary turning vanes or individual turning pipes (pipe diffusers). As described in Bernoulli's principle, the reduction in velocity causes the pressure to rise.^{ [1] }

While illustrating a gas turbine's Brayton cycle,^{ [15] } Figure 5.1 includes example plots of pressure-specific volume and temperature-entropy. These types of plots are fundamental to understanding centrifugal compressor performance at one operating point. The two plots show that the pressure rises between the compressor inlet (station 1) and compressor exit (station 2). At the same time, the specific volume decreases while the density increases. The temperature-entropy plot shows that the temperature increases with increasing entropy (loss). Assuming dry air, and the ideal gas equation of state and an isentropic process, there is enough information to define the pressure ratio and efficiency for this one point. The compressor map is required to understand the compressor performance over its complete operating range.

Figure 5.2, a centrifugal compressor performance map (either test or estimated), shows the flow, pressure ratio for each of 4 speed-lines (total of 23 data points). Also included are constant efficiency contours. Centrifugal compressor performance presented in this form provides enough information to match the hardware represented by the map to a simple set of end-user requirements.

Compared to estimating performance which is very cost effective (thus useful in design), testing, while costly, is still the most precise method.^{ [12] } Further, testing centrifugal compressor performance is very complex. Professional societies such as ASME (i.e. PTC–10, Fluid Meters Handbook, PTC-19.x),^{ [34] } ASHRAE (ASHRAE Handbook) and API (ANSI/API 617–2002, 672–2007)^{ [31] }^{ [33] } have established standards for detailed experimental methods and analysis of test results. Despite this complexity, a few basic concepts in performance can be presented by examining an example test performance map.

Pressure ratio and flow are the main parameters^{ [15] }^{ [31] }^{ [33] }^{ [34] } needed to match the Figure 5.2 performance map to a simple compressor application. In this case, it can be assumed that the inlet temperature is sea-level standard. This assumption is not acceptable in practice as inlet temperature variations cause significant variations in compressor performance. Figure 5.2 shows:

- Corrected mass flow: 0.04 – 0.34 kg/s
- Total pressure ratio, inlet to discharge (PR
_{t-t}= P_{t,discharge}/P_{t,inlet}): 1.0 – 2.6

As is standard practice, Figure 5.2 has a horizontal axis labeled with a flow parameter. While flow measurements use a variety of units, all fit one of 2 categories:

Mass flow units, such as kg/s, are the easiest to use in practice as there is little room for confusion. Questions remaining would involve inlet or outlet (which might involve leakage from the compressor or moisture condensation). For atmospheric air, the mass flow may be wet or dry (including or excluding humidity). Often, the mass flow specification will be presented on an equivalent Mach number basis, .^{ [35] } It is standard in these cases that the equivalent temperature, equivalent pressure, and gas is specified explicitly or implied at a standard condition.

In contrast, all volume flow specifications require the additional specification of density. Bernoulli's fluid dynamic principle is of great value in understanding this problem. Confusion arises through either inaccuracies or misuse of pressure, temperature, and gas constants.

Also as is standard practice, Figure 5.2 has a vertical axis labeled with a pressure parameter. There is a variety of pressure measurement units. They all fit one of two categories:

*A △pressure, ie increase from inlet to exit*(measured with a manometer)*A discharge pressure*

The pressure rise may alternatively be specified as a ratio that has no units:

*A pressure ratio*(exit/inlet)

Other features common to performance maps are:

The two most common methods for producing a map for a centrifugal compressor are at constant shaft speed or with a constant throttle setting. If the speed is held constant, test points are taken along a constant speed line by changing throttle positions. In contrast, if a throttle valve is held constant, test points are established by changing speed and repeated with different throttle positions (common gas turbine practice). The map shown in Figure 5.2 illustrates the most common method; lines of constant speed. In this case, we see data points connected via straight lines at speeds of 50%, 71%, 87%, and 100% RPM. The first three speed-lines have 6 points each while the highest speed line has five.

The next feature to be discussed is the oval-shaped curves representing islands of constant efficiency. In this figure we see 11 contours ranging from 56% efficiency (decimal 0.56) to 76% efficiency (decimal 0.76). General standard practice is to interpret these efficiencies as isentropic rather than polytropic. The inclusion of efficiency islands effectively generates a 3-dimensional topology to this 2-dimensional map. With inlet density specified, it provides a further ability to calculate aerodynamic power. Lines of constant power could just as easily be substituted.

Regarding gas turbine operation and performance, there may be a series of guaranteed points established for the gas turbine's centrifugal compressor. These requirements are of secondary importance to the overall gas turbine performance as a whole. For this reason, it is only necessary to summarize that in the ideal case, the lowest specific fuel consumption would occur when the centrifugal compressor's peak efficiency curve coincides with the gas turbine's required operation line.

In contrast to gas turbines, most other applications (including industrial) need to meet a less stringent set of performance requirements. Historically, centrifugal compressors applied to industrial applications were needed to achieve performance at a specific flow and pressure. Modern industrial compressors are often needed to achieve specific performance goals across a range of flows and pressures; thus taking a significant step toward the sophistication seen in gas turbine applications.

If the compressor represented in Figure 5.2 is used in a simple application, any point (pressure and flow) within the 76% efficiency would provide very acceptable performance. An "End User" would be very happy with the performance requirements of 2.0 pressure ratio at 0.21 kg/s.

Surge - is a low flow phenomenon where the impeller cannot add enough energy to overcome the system resistance or backpressure.^{ [36] } At low flow rate operation, the pressure ratio over the impeller is high, as is back system backpressure. Under critical conditions, the flow will reverse back over the tips of the rotor blades towards the impeller eye (inlet).^{ [37] } This stalling flow reversal may go unnoticed as the fraction of mass flow or energy is too low. When large enough, rapid flow reversal occurs(i.e., surge). The reversed flow exiting the impeller inlet exhibits a strong rotational component, which affects lower radius flow angles (closer to the impeller hub) at the leading edge of the blades. The deterioration of the flow angles causes the impeller to be inefficient. A full flow reversal can occur. (Therefore, surge is sometimes referred to as axisymmetric stall.) When reversed flow reduces to a low enough level, the impeller recovers and regains stability for a short moment at which point the stage may surge again. These cyclic events cause large vibrations, increase temperature and change rapidly the axial thrust. These occurrences can damage the rotor seals, rotor bearings, the compressor driver, and cycle operation. Most turbomachines are designed to easily withstand occasional surging. However, if the machine is forced to surge repeatedly for a long period of time, or if it is poorly designed, repeated surges can result in a catastrophic failure. Of particular interest, is that while turbomachines may be very durable, their physical system can be far less robust.

The surge-line shown in Figure 5.2 is the curve that passes through the lowest flow points of each of the four speed-lines. As a test map, these points would be the lowest flow points possible to record a stable reading within the test facility/rig. In many industrial applications, it may be necessary to increase the stall line due to the system backpressure. For example, at 100% RPM stalling flow might increase from approximately 0.170 kg/s to 0.215 kg/s because of the positive slope of the pressure ratio curve.

As stated earlier, the reason for this is that the high-speed line in Figure 5.2 exhibits a stalling characteristic or positive slope within that range of flows. When placed in a different system those lower flows might not be achievable because of interaction with that system. System resistance or adverse pressure is proven mathematically to be the critical contributor to compressor surge.

Choke occurs under one of 2 conditions. Typically for high speed equipment, as flow increases the velocity of the flow can approach sonic speed somewhere within the compressor stage. This location may occur at the impeller inlet "throat" or at the vaned diffuser inlet "throat". In contrast, for lower speed equipment, as flows increase, losses increase such that the pressure ratio eventually drops to 1:1. In this case, the occurrence of choke is unlikely.

The speed-lines of gas turbine centrifugal compressors typically exhibit choke. This is a situation where the pressure ratio of a speed line drops rapidly (vertically) with little or no change in flow. In most cases the reason for this is that close to Mach 1 velocities have been reached somewhere within the impeller and/or diffuser generating a rapid increase in losses. Higher pressure ratio turbocharger centrifugal compressors exhibit this same phenomenon. Real choke phenomena is a function of compressibility as measured by the local Mach number within an area restriction within the centrifugal pressure stage.

The maximum flow line, shown in Figure 5.2, is the curve that passes through the highest flow points of each speed line. Upon inspection it may be noticed that each of these points has been taken near 56% efficiency. Selecting a low efficiency (<60%) is the most common practice used to terminate compressor performance maps at high flows. Another factor that is used to establish the maximum flow line is a pressure ratio near or equal to 1. The 50% speed line may be considered an example of this.

The shape of Figure 5.2's speed-lines provides a good example of why it is inappropriate to use the term choke in association with a maximum flow of all centrifugal compressor speed-lines. In summary; most industrial and commercial centrifugal compressors are selected or designed to operate at or near their highest efficiencies and to avoid operation at low efficiencies. For this reason there is seldom a reason to illustrate centrifugal compressor performance below 60% efficiency.

Many industrial and commercial multistage compressor performance maps exhibits this same vertical characteristic for a different reason related to what is known as stage stacking.

- Minimum operating speed
- The minimum speed for acceptable operation, below this value the compressor may be controlled to stop or go into an "idle" condition.
- Maximum allowable speed
- The maximum operating speed for the compressor. Beyond this value stresses may rise above prescribed limits and rotor vibrations may increase rapidly. At speeds above this level the equipment will likely become very dangerous and be controlled to lower speeds.

To weigh the advantages between centrifugal compressors it is important to compare 8 parameters classic to turbomachinery. Specifically, pressure rise (p), flow (Q), angular speed (N), power (P), density (ρ), diameter (D), viscosity (μ) and elasticity (e). This creates a practical problem when trying to experimentally determine the effect of any one parameter. This is because it is nearly impossible to change one of these parameters independently.

The method of procedure known as the Buckingham π theorem can help solve this problem by generating 5 dimensionless forms of these parameters.^{ [1] }^{[ citation needed ]}^{ [16] } These Pi parameters provide the foundation for "similitude" and the "affinity-laws" in turbomachinery. They provide for the creation of additional relationships (being dimensionless) found valuable in the characterization of performance.

For the example below Head will be substituted for pressure and sonic velocity will be substituted for elasticity.

The three independent dimensions used in this procedure for turbomachinery are:

**mass (force is an alternative)****length****time**

According to the theorem each of the eight main parameters are equated to its independent dimensions as follows:

Flow | ex. = m^{3}/s | ||

Head | ex. = kg·m/s^{2} | ||

Speed | ex. = m/s | ||

Power | ex. = kg·m^{2}/s^{3} | ||

Density | ex. = kg/m^{3} | ||

Viscosity | ex. = kg/m·s | ||

Diameter | ex. = m | ||

Speed of sound | ex. = m/s |

Completing the task of following the formal procedure results in generating this classic set of five dimensionless parameters for turbomachinery.^{ [1] } Full-similitude is achieved when each one of the 5 Pi-parameters is equivalent when comparing two different cases. This of course would mean the two turbomachines being compared are similar, both geometrically and in terms of performance.

1 | Flow-coefficient | ||

Head-coefficient | |||

3 | Speed-coefficient | ||

4 | Power-coefficient | ||

5 | Reynolds-coefficient |

Turbomachinery analysts gain tremendous insight into performance by comparisons of the 5 parameters shown in the above table. Particularly, performance parameters such as efficiencies and loss-coefficients, which are also dimensionless. In general application, the Flow-coefficient and Head-coefficient are considered of primary importance. Generally, for centrifugal compressors, the Speed-coefficient is of secondary importance while the Reynolds-coefficient is of tertiary importance. In contrast, as expected for pumps, the Reynolds-coefficient becomes of secondary importance and the Speed-coefficient of tertiary importance. It may be found interesting that the Speed-coefficient may be chosen to define the y-axis of Figure 1.1, while at the same time the Reynolds coefficient may be chosen to define the z-axis.

Demonstrated in the table below is another value of dimensional analysis. Any number of new dimensionless parameters can be calculated through exponents and multiplication. For example, a variation of the first parameter shown below is popularly used in aircraft engine system analysis. The third parameter is a simplified dimensional variation of the first and second. This third definition is applicable with strict limitations. The fourth parameter, specific speed, is very well known and useful in that it removes diameter. The fifth parameter, specific diameter, is a less often discussed dimensionless parameter found useful by Balje.^{ [38] }

1 | Corrected mass flow coefficient | ||

2 | Alternate#1 equivalent Mach form | ||

3 | Alternate#2 simplified dimensional form | ||

4 | Specific speed coefficient | ||

5 | Specific diameter coefficient |

It may be found interesting that the specific speed coefficient may be used in place of speed to define the y-axis of Figure 1.2, while at the same time, the specific diameter coefficient may be in place of diameter to define the z-axis.

The following *affinity laws* are derived from the five Π-parameters shown above. They provide a simple basis for scaling turbomachinery from one application to the next.

From flow coefficient | |||

From head coefficient | |||

From power coefficient |

The following equations outline a fully three-dimensional mathematical problem that is very difficult to solve even with simplifying assumptions.^{ [10] }^{ [39] } Until recently, limitations in computational power, forced these equations to be simplified to an Inviscid two-dimensional problem with pseudo losses. Before the advent of computers, these equations were almost always simplified to a one-dimensional problem.

Solving this one-dimensional problem is still valuable today and is often termed *mean-line analysis*. Even with all of this simplification it still requires large textbooks to outline and large computer programs to solve practically.

Also termed *continuity*, this fundamental equation written in general form is as follows:

Also termed the * Navier–Stokes equations *, this fundamental is derivable from Newton's second law when applied to fluid motion. Written in compressible form for a Newtonian fluid, this equation may be written as follows:

The first law of thermodynamics is the statement of the conservation of energy. Under specific conditions, the operation of a Centrifugal compressor is considered a reversible process. For a reversible process, the total amount of heat added to a system can be expressed as where is temperature and is entropy. Therefore, for a reversible process:

Since U, S and V are thermodynamic functions of state, the above relation holds also for non-reversible changes. The above equation is known as the fundamental thermodynamic relation.

The classical ideal gas law may be written:

The ideal gas law may also be expressed as follows

where is the density, is the adiabatic index (ratio of specific heats), is the internal energy per unit mass (the "specific internal energy"), is the specific heat at constant volume, and is the specific heat at constant pressure.

With regard to the equation of state, it is important to remember that while air and nitrogen properties (near standard atmospheric conditions) are easily and accurately estimated by this simple relationship, there are many centrifugal compressor applications where the ideal relationship is inadequate. For example, centrifugal compressors used for large air conditioning systems (water chillers) use a refrigerant as a working gas that cannot be modeled as an ideal gas. Another example are centrifugal compressors design and built for the petroleum industry. Most of the hydrocarbon gases such as methane and ethylene are best modeled as a real gas equation of state rather than ideal gases. The Wikipedia entry for equations of state is very thorough.

- Pros

- Centrifugal compressors offer the advantages of simplicity of manufacturing and relatively low cost. This is due to requiring fewer stages to achieve the same pressure rise.
- Centrifugal compressors are used throughout industry because they have fewer rubbing parts, are relatively energy efficient, and give higher and non-oscillating constant airflow than a similarly sized reciprocating compressor or any other positive displacement pump.
- Centrifugal compressors are mostly used as turbochargers and in small gas turbine engines like in an APU (auxiliary power unit) and as main engine for smaller aircraft like helicopters. A significant reason for this is that with current technology, the equivalent airflow axial compressor will be less efficient due primarily to a combination of rotor and variable stator tip-clearance losses.

- Cons

- Their main drawback is that they cannot achieve the high compression ratio of reciprocating compressors without multiple stages. There are few one-stage centrifugal compressors capable of pressure ratios over 10:1, due to stress considerations which severely limit the compressor's safety, durability and life expectancy.
- Centrifugal compressors are impractical, compared to axial compressors, for use in large gas turbines and turbojet engines propelling large aircraft, due to the resulting weight and stress, and to the frontal area presented by the large diameter of the radial diffuser.

Ideally, centrifugal compressor impellers have thin air-foil blades that are strong, each mounted on a light rotor. This material would be easy to machine or cast and inexpensive. Additionally, it would generate no operating noise, and have a long life while operating in any environment.^{[ clarification needed ]}

From the very start of the aero-thermodynamic design process, the aerodynamic considerations and optimizations [29,30] are critical to have a successful design. during the design, the centrifugal impeller's material and manufacturing method must be accounted for within the design, whether it be plastic for a vacuum cleaner blower, aluminum alloy for a turbocharger, steel alloy for an air compressor or titanium alloy for a gas turbine. It is a combination of the centrifugal compressor impeller shape, its operating environment, its material and its manufacturing method that determines the impeller's structural integrity.^{ [40] }^{ [41] }

- Angular momentum
- Axial compressor
- Centrifugal force
- Centripetal force
- Coandă effect
- Computational fluid dynamics
- Compressibility
- Compressor map
- Coriolis force
- Darcy–Weisbach equation
- Enthalpy
- Entropy
- Euler equations (fluid dynamics)
- Finite element method
- Fluid dynamics
- Gas laws
- Gustaf de Laval
- Ideal gas law
- Kinematics
- Mach number
- Multiphase flow
- Navier–Stokes equations
- Real gas
- Reynolds-averaged Navier–Stokes equations
- Reynolds transport theorem
- Reynolds number
- Rossby number
- Three-dimensional losses and correlation in turbomachinery
- Turbulence
- Viscosity
- von Karman Institute for Fluid Dynamics

A **compressor** is a mechanical device that increases the pressure of a gas by reducing its volume. An air compressor is a specific type of gas compressor.

An **axial compressor** is a gas compressor that can continuously pressurize gases. It is a rotating, airfoil-based compressor in which the gas or working fluid principally flows parallel to the axis of rotation, or axially. This differs from other rotating compressors such as centrifugal compressor, axi-centrifugal compressors and mixed-flow compressors where the fluid flow will include a "radial component" through the compressor. The energy level of the fluid increases as it flows through the compressor due to the action of the rotor blades which exert a torque on the fluid. The stationary blades slow the fluid, converting the circumferential component of flow into pressure. Compressors are typically driven by an electric motor or a steam or a gas turbine.

**Turbomachinery**, in mechanical engineering, describes machines that transfer energy between a rotor and a fluid, including both turbines and compressors. While a turbine transfers energy from a fluid to a rotor, a compressor transfers energy from a rotor to a fluid.

**Centrifugal pumps** are used to transport fluids by the conversion of rotational kinetic energy to the hydrodynamic energy of the fluid flow. The rotational energy typically comes from an engine or electric motor. They are a sub-class of dynamic axisymmetric work-absorbing turbomachinery. The fluid enters the pump impeller along or near to the rotating axis and is accelerated by the impeller, flowing radially outward into a diffuser or volute chamber (casing), from which it exits.

An **axial-flow pump**, or **AFP**, is a common type of pump that essentially consists of a propeller in a pipe. The propeller can be driven directly by a sealed motor in the pipe or by electric motor or petrol/diesel engines mounted to the pipe from the outside or by a right-angle drive shaft that pierces the pipe.

In a hydraulic circuit, **net positive suction head** (**NPSH**) may refer to one of two quantities in the analysis of cavitation:

- The Available NPSH (NPSH
_{A}): a measure of how close the fluid at a given point is to flashing, and so to cavitation. Technically it is the absolute pressure head minus the vapour pressure of the liquid. - The Required NPSH (NPSH
_{R}): the head value at the suction side required to keep the fluid away from cavitating.

A **compressor map** is a chart which shows the performance of a turbomachinery compressor. This type of compressor is used in gas turbine engines, for supercharging reciprocating engines and for industrial processes, where it is known as a dynamic compressor. A map is created from compressor rig test results or predicted by a special computer program. Alternatively the map of a similar compressor can be suitably scaled. This article is an overview of compressor maps and their different applications and also has detailed explanations of maps for a fan and intermediate and high-pressure compressors from a three-shaft aero-engine as specific examples.

As the name suggests, **gas turbine engine compressors** provide the compression part of the gas turbine engine thermodynamic cycle. There are three basic categories of gas turbine engine compressor: axial compressor, centrifugal compressor and mixed flow compressor. A fourth, unusual, type is the free-piston gas generator, which combines the functions of compressor and combustion chamber in one unit.

**Specific speed***N*_{s}, is used to characterize turbomachinery speed. Common commercial and industrial practices use dimensioned versions which are of equal utility. Specific speed is most commonly used in pump applications to define the suction specific speed —a quasi non-dimensional number that categorizes pump impellers as to their type and proportions. In Imperial units it is defined as the speed in revolutions per minute at which a geometrically similar impeller would operate if it were of such a size as to deliver one gallon per minute against one foot of hydraulic head. In metric units flow may be in l/s or m³/s and head in m, and care must be taken to state the units used.

A **centrifugal fan** is a mechanical device for moving air or other gases in a direction at an angle to the incoming fluid. Centrifugal fans often contain a ducted housing to direct outgoing air in a specific direction or across a heat sink; such a fan is also called a **blower**, **blower fan**, or **squirrel-cage fan**. Tiny ones used in computers are sometimes called **biscuit blowers**. These fans move air from the rotating inlet of the fan to an outlet. They are typically used in ducted applications to either draw air through ductwork/heat exchanger, or push air through similar. impellers. Compared to standard axial fans, they can provide similar air movement from a smaller fan package, and overcome higher resistance in air streams.

A **radial turbine** is a turbine in which the flow of the working fluid is radial to the shaft. The difference between axial and radial turbines consists in the way the fluid flows through the components. Whereas for an axial turbine the rotor is 'impacted' by the fluid flow, for a radial turbine, the flow is smoothly orientated perpendicular to the rotation axis, and it drives the turbine in the same way water drives a watermill. The result is less mechanical stress which enables a radial turbine to be simpler, more robust, and more efficient when compared to axial turbines. When it comes to high power ranges the radial turbine is no longer competitive and the efficiency becomes similar to that of the axial turbines.

In fluid dynamics, flow can be decomposed into primary plus **secondary flow**, a relatively weaker flow pattern superimposed on the stronger **primary flow** pattern. The primary flow is often chosen to be an exact solution to simplified or approximated governing equations, such as potential flow around a wing or geostrophic current or wind on the rotating Earth. In that case, the secondary flow usefully spotlights the effects of complicated real-world terms neglected in those approximated equations. For instance, the consequences of viscosity are spotlighted by secondary flow in the viscous boundary layer, resolving the tea leaf paradox. As another example, if the primary flow is taken to be a balanced flow approximation with net force equated to zero, then the secondary circulation helps spotlight acceleration due to the mild imbalance of forces. A smallness assumption about secondary flow also facilitates linearization.

**Cheng Xu** is a Chinese American aerodynamic design engineer and engineering manager. He is a Fellow of the American Society of Mechanical Engineers and a member of the Technical Committee on Energy and Power Systems, IASTED. He also served as a guest editor of International Journal of Rotating Machinery.

In turbomachinery, **degree of reaction** or **reaction ratio (R)** is defined as the ratio of the static pressure rise in the rotating blades of a compressor (or drop in turbine blades) to the static pressure rise in the compressor stage (or drop in a turbine stage). Alternatively it is the ratio of static enthalpy change in the rotor to the static enthalpy change in the stage.

**Compressor characteristic** is a mathematical curve that shows the behaviour of a fluid going through a dynamic compressor. It shows changes in fluid pressure, temperature, entropy, flow rate etc.) with the compressor operating at different speeds.

In turbomachinery, the **slip factor** is a measure of the fluid slip in the impeller of a compressor or a turbine, mostly a centrifugal machine. Fluid slip is the deviation in the angle at which the fluid leaves the impeller from the impeller's blade/vane angle. Being quite small in axial impellers, slip is a very important phenomenon in radial impellers and is useful in determining the accurate estimation of work input or the energy transfer between the impeller and the fluid, rise in pressure and the velocity triangles at the impeller exit.

An **axial fan** is a type of fan that causes gas to flow through it in an axial direction, parallel to the shaft about which the blades rotate. The flow is axial at entry and exit. The fan is designed to produce a pressure difference, and hence force, to cause a flow through the fan. Factors which determine the performance of the fan include the number and shape of the blades. Fans have many applications including in wind tunnels and cooling towers. Design parameters include power, flow rate, pressure rise and efficiency.

An **axial turbine** is a turbine in which the flow of the working fluid is parallel to the shaft, as opposed to radial turbines, where the fluid runs around a shaft, as in a watermill. An axial turbine has a similar construction as an axial compressor, but it operates in the reverse, converting flow of the fluid into rotating mechanical energy.

**Three-dimension losses and correlation in turbomachinery** refers to the measurement of flow-fields in three dimensions, where measuring the loss of smoothness of flow, and resulting inefficiencies, becomes difficult, unlike two-dimensional losses where mathematical complexity is substantially less.

**Blade solidity** is an important design parameter for the axial flow impeller and is defined as the ratio of blade chord length to spacing.

- 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Shepherd, Dennis G. (1956).
*Principles of turbomachinery*(6th ed.). New York: Macmillan. LCCN 56002849. OCLC 5899719. - 1 2 Japikse, David (1996).
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*Design of Radial Turbomachinery*. Longman Scientific and Technical. ISBN 978-0-470-21667-5. - 1 2 3 Aungier, Ronald H. (2000).
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*Mechanical Engineering*. ASME. Archived from the original on 2009-01-15. - ↑ Elliott Company. "Past, Present, Future, 1910-2010" (PDF). Elliott. Retrieved 1 May 2011.
- ↑ =The Development Of Jet And Turbine Aero Engines 4th edition, Bill Gunston 2006, ISBN 0 7509 4477 3, p.217
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*Std 673-2002 Centrifugal Fans for Petroleum, Chemical and Gas Industry Services*. New York: API.^{[ permanent dead link ]} - ↑ American Society of Mechanical Engineers. "ASME BPVC".
*www.asme.org*. ASME. Retrieved 13 December 2021. - ↑ American Society of Mechanical Engineers. "ASME PTC".
*www.asme.org*. ASME. Retrieved 13 December 2021. - ↑ American Petroleum Institute. "API STD 617 8TH ED (E1)".
*www.api.org*. American Petroleum Institute. Retrieved 13 December 2021. - ↑ American Petroleum Institute. "API STD 672 5TH ED (2019)".
*www.api.org*. American Petroleum Institute. Retrieved 13 December 2021. - ↑ "Description 2021 ASHRAE Handbook—Fundamentals".
*www.ashrae.org*. Retrieved 2022-02-20. - 1 2 "SAE Standards".
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*www.cagi.org*. Compressed Air and Gas Institute. Retrieved 13 December 2021.`{{cite web}}`

: Check`|url=`

value (help) - ↑ ISO. "ISO - Search".
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*Std 617-2002 Axial and Centrifugal Compressors and Expander-compressors for Petroleum, Chemical and Gas Industry Services*. New York: API. - ↑ ASHRAE, American Society of Heating, Refrigeration and Air-Conditioning Engineers. "Standards & Guidelines". ASHRAE. Retrieved 23 April 2011.
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*Std 672-2007 Packaged, Integrally Geared Centrifugal Air Compressors for Petroleum, Chemical, and Gas Industry Services*. New York: API. - 1 2
*ASME PTC 10-1997 Test Code on Compressors and Exhausters*. New York: ASME. 1997. ISBN 978-0-7918-2450-4. - ↑ Centrifugal Compressors A Basic Guide, Boyce 2003, ISBN 0 87814 801 9, Figure 2-11 A typical centrifugal compressor performance map
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*Compressor Surge and Stall*. Concepts ETI. ISBN 978-0-933283-05-3. - ↑ Semlitsch, Bernhard; Mihăescu, Mihai (May 2016). "Flow phenomena leading to surge in a centrifugal compressor".
*Energy*.**103**: 572–587. doi:10.1016/j.energy.2016.03.032. - ↑ Balje, O. E. (1961).
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*Compressor Aerodynamics*. Krieger Publishing. ISBN 978-1-57524-247-7. - ↑ Xu, C. and R.S. Amano, The Development of a Centrifugal Compressor Impeller, International Journal for Computational Methods in Engineering Science and Mechanics, Volume 10 Issue 4 2009, Pages 290 – 301.
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Wikimedia Commons has media related to Centrifugal compressors .

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- Glenn Research Center at NASA
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- Ctrend website to calculate the head of centrifugal compressor online

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