| Silvercrest | |
|---|---|
 | |
| The engine on display at the Paris Air Show 2013 | |
| Type | Turbofan |
| National origin | France |
| Manufacturer | Safran |
| First run | September 2012 [1] |
| Major applications | Cessna Citation Hemisphere |
| Number built | 7 [2] |
The Safran Silvercrest was a French turbofan chosen for the Dassault Falcon 5X and Cessna Citation Hemisphere. It did not meet the requirements for either aircraft program and was cancelled while still in the development stage. It was a product of Safran Aircraft Engines.
The engine was announced at the 2006 National Business Aviation Association convention. [3]
The first engine went to test in September 2012. [1] [4] Flight testing started in July 2014 on a Grumman Gulfstream II at Istres-Le Tubé Air Base. [5] Problem areas disclosed at the time included high-pressure compressor operability, oil-fuel heat exchanger performance, carcass distortion and turbine tip clearance control. [6]
In December 2017, Dassault abandoned the Silvercrest due to technical and schedule risks. It terminated the 5X program and launched a new Falcon with the same cross section, Pratt & Whitney Canada engines and a 5,500 nmi (10,200 km) range for a 2022 introduction.
In July 2019, Textron suspended the Cessna Citation Hemisphere development due to engine shortcomings. [7]
It was originally designed as an 8,500–10,500 lbf (38–47 kN) thrust turbofan. [8] It was meant for large-cabin business jets and 40 to 60-seat regional jets with a maximum takeoff weight of 45,000 to 60,000 lb (20,000 to 27,000 kg). [9] In 2016 the thrust range was quoted as 10,000–12,000 lbf (44–53 kN). [10]
The two-shaft engine included a 42.5 in (108 cm) fan with solid wide-chord swept blades, followed by 4 booster stages, all driven by a 4-stage low pressure turbine. The high pressure spool had 4 axial compressor stages and 1 centrifugal stage, driven by a single-stage turbine. [1] An axi-centrifugal compressor was unusual for an engine with more than 10,000 lb thrust. [10]
A related design in 2007 used a smaller 40-inch fan with a lower 4.5 bypass ratio, no booster, an extra high-pressure compressor stage, one less low-pressure turbine stage, a 27:1 overall pressure ratio and a core pressure ratio of "over 17". [11]
Data fromSnecma. [13]
Comparable engines
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