Rolls-Royce Gem: Difference between revisions
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==Engines on display== |
==Engines on display== |
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*[[Midland Air Museum]] |
*[[Midland Air Museum]] |
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==Specifications (Gem 42)== |
==Specifications (Gem 42)== |
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==See also== |
==See also== |
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{{DHaeroengines}} |
{{DHaeroengines}} |
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{{Aviation lists}} |
{{Aviation lists}} |
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{{aeroengine-specs}} |
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[[Category:Aircraft turboshaft engines]] |
[[Category:Aircraft turboshaft engines]] |
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Revision as of 01:48, 16 July 2009
| Gem | |
|---|---|
| |
| Rolls-Royce Gem at the Midland Air Museum | |
| Type | Turboshaft |
| National origin | United Kingdom |
| Manufacturer | Rolls-Royce Limited |
| Major applications | Westland Lynx |
The Rolls-Royce Gem is a turboshaft engine developed specifically for the Westland Lynx helicopter in the 1970's. The design started off at de Havilland (hence the name starting with "G") and was passed to Bristol Siddeley as the BS.360. When Rolls-Royce bought-out the latter in 1966, it became the RS.360.[1]
Design and development
The Gem's three-shaft engine configuration is rather unusual for turboshaft/turboprop engines. Basic arrangement is a four-stage axial compressor, driven by a single stage IP (Intermediate Pressure) turbine, supercharging a centrifugal HP (High Pressure) compressor, driven by a single stage HP turbine. Power is delivered to the load via a third shaft, connected to a two-stage free (power) turbine. A reverse flow combustor is featured.
The Gem 42 develops 1,000 shp (750 kW) at Take-off, Sea Level Static, ISA, but the Maximum Contingency Rating (MCR) is 1,120 shp (840 kW).
Until recently all versions of the Lynx have been Gem powered. However, now that Rolls-Royce own Allison, they have been marketing the more modern LHTEC T800, developed jointly with Honeywell. The civil version, known as the CTS800, will power the AgustaWestland Super Lynx.
Applications
Engines on display
Specifications (Gem 42)
Data from: [2]
General characteristics
- Type: Triple-spool turboshaft
- Length: 43.4 in (1090 mm)
- Diameter: 23.5 in (590 mm)
- Dry weight: 414 lb (187 kg)
Components
- Compressor: 4-stage axial LP, single-stage centrigugal HP
- Turbine: 2-stage power turbine, single-stage LP, single-stage HP
Performance
- Maximum power output: 1,000 shp (746 kW)
- Overall pressure ratio: 12:1
- Air mass flow: 7 lb/sec
See also
Comparable engines
Related lists
References
- ^ Gunston 1989, p.155.
- ^ Rolls-Royce Gem 42 factsheet Retrieved: 16 July 2009
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
