Safran Silvercrest
French turbofan aircraft engine
From Wikipedia, the free encyclopedia
The Safran Silvercrest was a French turbofan unsuccessful development intended to power the Dassault Falcon 5X and Cessna Citation Hemisphere. A project of Safran Aircraft Engines, it did not meet the requirements for either aircraft program and was cancelled while still in the development stage.
| 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 |
| Status | Development is practically ceased |
| Number built | 7[2] |
Development
The Silvercrest 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 [Lackland Air Base, San Antonio, Texas]. Later, in 2017 moved to 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]
Design
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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]
Applications
- Silvercrest 2C
- Cessna Citation Hemisphere development aircraft only, first flight 2019.
- Silvercrest SC-2D
- Dassault Falcon 5X development aircraft only; thrust 11,450 lbf (50.9 kN). Both aircraft and engine were simultaneously unveiled at the National Business Aviation Association annual convention on October 21, 2013, with entry into service in 2020.[12] Dassault announced the cancellation of the 5X program on 13 December 2017.
Specifications (2D)
Data from Snecma.[13]
General characteristics
- Type: axial and centrifugal flow, twin-shaft, bypass turbofan engine
- Length: approx. 74 inches (190 cm)
- Diameter: 42.5 inches (108 cm) Fan
- Dry weight: 2,290 lb (1,040 kg)[14]
Components
- Compressor: 4 low-pressure stages, 4 high-pressure blisks + 1 centrifugal stage
- Turbine: 1 high-pressure, 4 low-pressure stages
Performance
- Maximum thrust: 11,450 lbf (50.9 kN)
- Overall pressure ratio: 38.5 [15]
- Bypass ratio: 5.9:1
- Thrust-to-weight ratio: 5[14]
See also
Comparable engines
Related lists
