Rolls-Royce Gem: Difference between revisions
→External links: Remove stub tag |
m Avoid redirect, add date |
||
| Line 19: | Line 19: | ||
|} |
|} |
||
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 |
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'''.<ref>Gunston 1989, p.155.</ref> |
||
==Design and development== |
==Design and development== |
||
Revision as of 20:25, 9 January 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 at Take-off, Sea Level Static, ISA, but the Maximum Contingency Rating (MCR) is 1,120 shp.
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.
Specifications (Gem)
General characteristics
- Type: Triple-spool turboshaft
- Length:
- Diameter:
- Dry weight: 320 lb
Components
- Compressor: 4-stage axial LP, single-stage HP
- Turbine: 2-stage power turbine, single stage HP
Performance
- Maximum power output: 900 to 1,200 shp
- Overall pressure ratio: 12:1
- Air mass flow: 7 lb/sec
See also
Comparable engines
Related lists
References
- ^ Gunston 1989, p.155.
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
 |
This aircraft engine article is missing some (or all) of its specifications. If you have a source, you can help Wikipedia by adding them. |