| Gyron | |
|---|---|
 |
|
| de Havilland Gyron at the de Havilland Aircraft Heritage Centre | |
| Type | Turbojet |
| Manufacturer | de Havilland Engine Company |
| First run | 1953 |
| Major applications | Hawker P.1121 (not built) |
| Developed into | de Havilland Gyron Junior |
The de Havilland PS.23 or PS.52 Gyron, originally the Halford H-4, was Frank Halford's last turbojet design while working for de Havilland. Intended to outpower any design then under construction, the Gyron was the most powerful engine of its era, producing 20,000 lbf "dry", and 27,000 lbf with afterburner ("reheat" in British terminology). The engine was actually too large for most roles and saw no production use. It was later scaled down to 45% of its original size to produce the de Havilland Gyron Junior, which was somewhat more successful.[1]
Contents |
Design and development
The Gyron was Halford's first axial-flow design, a complete departure from his earlier centrifugal-flow engines based on Whittle-like designs, the Goblin (H-1) and Ghost (H-2). The Gyron was also one of the first engines designed specifically for supersonic flight.
The Gyron first ran in 1953. Flight testing started in 1955 on a modified Short Sperrin (a bomber design that was instead turned into an experimental aircraft), replacing the lower two Rolls-Royce Avons with the much larger Gyrons.
The Gyron was selected for a number of projects, most notably the Hawker P.1121 (sometimes referred to as the Hurricane) supersonic attack aircraft that was to have been the replacement for the Hawker Hunter. However, this project was eventually cancelled. Another design potentially based on the Gyron was the Operational Requirement F.155 interceptor, which optionally used the Rolls-Royce RB.106. F.155 was also cancelled, part of the 1957 Defence White Paper. The Gyron project itself was cancelled in March 1957, at a reported total cost of £ 3.4 million.[2]
Engines on display
An example of the Gyron is held by the Science Museum (London),[3] another is on public display at the de Havilland Aircraft Heritage Centre, St Albans.[4]
Specifications (Gyron D.Gy.1.)
General characteristics
- Type: Turbojet
- Length: 155.5 in
- Diameter: 55.2 in
- Dry weight: 4,270 lb
Components
- Compressor: Seven stage axial flow
- Turbine: Two-stage
Performance
- Maximum Thrust: 20,000 lb
- Overall pressure ratio: 5.6
- Specific fuel consumption: 1.04 Ib./hr/lb at maximum thrust
- Power-to-weight ratio:
See also
Related development
Comparable engines
Related lists
References
Notes
- ^ Gunston 1989, p.32.
- ^ "Cancelled projects: the list up-dated" (PDF). Flight: 262. 17 August 1967. http://www.flightglobal.com/pdfarchive/view/1967/1967%20-%201672.html.
- ^ Thought to be in storage at Wroughton and not on display
- ^ Photo of DH Gyron at DH Heritage Centre
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
 |
Wikimedia Commons has media related to: De Havilland Gyron |
|
|||||||||||||||||
|
||||||||||||||
This entry is from Wikipedia, the leading user-contributed encyclopedia. It may not have been reviewed by professional editors (see full disclaimer)
