Blade solidity

For blade configuration in general, see airfoil. For how it is linked to turbomachinery application, see Turbomachinery.

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

Airfoil nomenclature

• Blade Solidity = c/s

Where

• ${\displaystyle s=2\pi r_{m}/n_{b}}$ is the spacing
• ${\displaystyle r_{m}}$ is the mean radius
• ${\displaystyle n_{b}}$ is blade number
• Chord length c is the length of the chord line

In case of an axial flow impeller, the mean radius is defined in terms of hub (${\displaystyle r_{h}}$,inner radius) and tip radius (${\displaystyle r_{t}}$,outer radius) as :

• ${\displaystyle r_{m}=[(r_{t}^{2}+r_{h}^{2})/2]^{0.5}}$

Blade solidity affects various turbomachinery parameters, so to vary those parameters, one needs to vary blade solidity. However, there are some limitations imposed by aspect ratio (span/chord) and pitch. If an impeller has only a few blades (i.e a large pitch), it will result in less lift force and in a similar manner for more blades (i.e. very low pitch), there will be high drag force.

Blade solidity should not be confused with rotor solidity, which is the ratio of the total area of the rotor blades to the swept area of the rotor.

Flow over isolated airfoil

Blade solidity is an important parameter that inter relates turbomachine parameters to airfoil parameters. Lift and drag coefficient for an airfoil is inter related to blade solidity as shown:

• ${\displaystyle C_{L}=2(s/c)(\tan \beta _{1}-\tan \beta _{2})cos\beta _{m}}$
• ${\displaystyle C_{d}=\left({\frac {s}{c}}\right)\left({\frac {\Delta p_{0}}{\rho W_{1}^{2}/2}}\right)}$

where:

• ${\displaystyle C_{L}}$ is lift coefficient
• ${\displaystyle C_{d}}$ is the drag coefficient
• ${\displaystyle \beta _{1}}$ is the inlet flow angle on the airfoil
• ${\displaystyle \beta _{2}}$ is the outlet flow angle on the airfoil
• ${\displaystyle \beta _{m}}$ is the mean flow angle
• ${\displaystyle W_{1}}$ is inlet flow velocity i.e relative to airfoil
• ${\displaystyle W_{m}}$ is mean flow velocity
• ${\displaystyle \Delta p_{0}}$ is the pressure loss
• ${\displaystyle \tan \beta _{m}={\frac {1}{2}}(\tan \beta _{1}+\tan \beta _{2})}$

In an airfoil, the mean line curvature is designed to change the flow direction, the vane thickness is for strength and the streamlined shape is to delay the onset of boundary layer separation. Taking all the design factors of an airfoil, the resulting forces of lift and drag can be expressed in terms of lift and drag coefficient.

• ${\displaystyle F_{L}=C_{L}bc\left({\frac {1}{2}}\rho W_{m}^{2}\right)}$
• ${\displaystyle F_{d}=C_{d}bc\left({\frac {1}{2}}\rho W_{m}^{2}\right)}$

where:

• b is the wingspan, and
• c is the chord length

Preliminary design procedure

The design of the impeller depends on specific speed, hub-tip ratio and solidity ratio. To illustrate the dependence, an expression for axial flow pump and fan is shown:

${\displaystyle {\frac {c}{s}}={\frac {10}{(D_{h}/D_{t})(N_{s}/1000)^{1.5}}}}$

where:

• ${\displaystyle {\frac {D_{h}}{D_{t}}}}$ is ratio of hub to tip diameter
• ${\displaystyle N_{s}}$ is the specific speed

Cordier diagram can be used to determine specific speed and impeller tip diameter ${\displaystyle D_{t}}$. Accordingly solidity ratio and hub-tip ratio (range 0.3-0.7) can be adjusted.

Solidity ratio generally falls in the range of 0.4-1.1

See also

• Physics portal

• Aerodynamics
• Turbomachinery
• Axial-flow pump
• Mechanical fan
• Compressors
• Autorotation (helicopter)

References

• Peng, William W. (2008), Fundamentals of Turbomachinery, Wiley, ISBN   978-0-470-12422-2
• Venkanna, B.K. (2009), Fundamentals of Turbomachinery, PHI learning private limited, ISBN   978-81-203-3775-6
• Turton, R.K. (1995), Principles of turbomachinery, Springer (New Delhi), ISBN   8184896042
• Rama, S.R. Gorla (2003), Turbomachinery Design and Theory, Marcel Dekker, Inc., ISBN   0-8247-0980-2
• Yahya, S.M. (2002), Turbines, compressors and fans, TMH, ISBN   0070707022