- de Havilland Gyron
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 (89 kN) "dry", and 27,000 lbf (120 kN) 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.
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. Flight rating was 18,000 lbf (80,000 N). In 1955 the DGy.1 received an official rating of 15,000 lbf (67,000 N). Addition of a reheat section boosted output to 20,000 lbf (89,000 N) and then 25,000 lbf (110,000 N) in the Dgy.2
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. Government financial support of the Gyron project itself was cancelled in March 1957, at a reported total cost of £ 3.4 million.
Engines on display
Specifications (Gyron D.Gy.1.)
- Type: Turbojet
- Length: 155.5 in
- Diameter: 55.2 in
- Dry weight: 4,270 lb
- Compressor: Seven stage axial flow
- Turbine: Two-stage
- 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:
- Related development
- Comparable engines
- Related lists
- ^ Gunston 1989, p.32.
- ^ http://www.flightglobal.com/pdfarchive/view/1957/1957%20-%201074.html
- ^ "Cancelled projects: the list up-dated" (PDF). Flight: 262. 17 August 1967. http://www.flightglobal.com/pdfarchive/view/1967/1967%20-%201672.html.
- ^ "Gyron" (PDF). Flight: 168. 2 August 1957. http://www.flightglobal.com/pdfarchive/view/1957/1957%20-%201078.html.
- ^ Thought to be in storage at Wroughton and not on display
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
- Photo of DH Gyron at DH Heritage Centre
- Gyron - de Havilland's Supersonic Turbojet, with 25,000lb Reheat Rating - A 1957 Flight magazine article on the Gyron
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