Rolls-Royce Pegasus Information & Rolls-Royce Pegasus Links at HealthHaven.com

Pegasus / F402
	Schematic drawing of RR Pegasus
Type	Turbofan
Manufacturer	Rolls-Royce
First run	1959
Major applications	Hawker Siddeley Harrier; BAE Sea Harrier; AV-8B Harrier II
Number built	over 1,200 (through 2008)

The Rolls Royce Pegasus is a turbofan engine originally designed by Bristol Siddeley (hence the name from Greek mythology) and now manufactured by Rolls-Royce plc. This engine used in Harrier jet aircraft in the 1960s,^[1] is able to direct thrust downwards which can then be swivelled to power a jet aircraft forward. Lightly loaded, it can also manoeuvre like a helicopter, vertically for takeoff and landings.^[2] In US service the engine is given the designation F402.

The unique Pegasus engine powers all versions of the Hawker Siddeley Harrier multi-role military aircraft. Rolls-Royce licensed Pratt & Whitney to build the Pegasus for US built versions. However Pratt & Whitney never completed any engines, with all new build being manufactured by Rolls-Royce in Bristol, England. The Pegasus has also been the planned engine for a number of aircraft projects, among which were the prototypes of the German Dornier Do 31 VSTOL military transport project.^[3]

[edit] Design and development

[edit] History

Rolls-Royce Pegasus

The Bristol Engine Company began work on the BE.53 Pegasus in 1958. The engine was designed in tandem with the prototype of the Hawker Siddeley Harrier, the Hawker P.1127, which first flew in 1960. It was developed from the Bristol Orpheus, overseen by Stanley Hooker. The low pressure stages came from the Bristol Olympus engine. The engine was named 'Pegasus' because the four columns of thrust that the aircraft would hover-on were likened to the four legs of the mythical winged horse.^{[citation needed]} Production and development of the Pegasus was continued by Rolls-Royce when it acquired Bristol in 1966. A related engine design, the 39,500 lbf (with reheat) Bristol Siddeley BS100 for a supersonic VTOL fighter (the Hawker Siddeley P.1154) was not developed to production as the aircraft project was cancelled in 1965.

[edit] Technical description

The Pegasus vectored-thrust turbofan is a two-shaft design featuring three low pressure (LP) and eight high pressure (HP) compressor stages driven by two LP and two HP turbine stages respectively. Unusually the LP and HP spools rotate in opposite directions to greatly reduce the gyroscopic effects which would otherwise hamper low speed handling. The engine employs a simple thrust vectoring system that uses four swivelling nozzles, giving the Harrier thrust both for lift and forward propulsion, allowing for STOVL flight. The front two nozzles are fed with air from the LP compressor, the rear with hot (650^oC) jet exhaust. The airflow split is about 60/40 front back.^[4] It was critical that the nozzles rotate together. This was achieved by using a pair of air motors fed from the HP (high pressure) compressor, in a fail over configuration, pairs of nozzles connected with, surprisingly, motor-cycle chains.

The Pegasus was also the first turbofan engine to have the initial compressor fan, the zeroth stage, ahead of the front bearing. This eliminated radial struts and the icing hazard they represent.

To date, more than 1,200 engines have been produced and almost two million operating hours have been logged with the Harriers of the Royal Air Force, Royal Navy, U.S. Marine Corps and the navies of India, Italy, Spain and Thailand.

The engine is mounted in the centre of the Harrier and as such it is necessary to remove the wing to change the powerplant having already sat the fuselage on trestles; the whole change took a minimum of eight hours.^[5]

[edit] Variants

Rolls-Royce Bristol Pegasus, engine of the vertical takeoff Harrier, in the Bristol Industrial Museum, England.

[edit] Pegasus 2

Otherwise known as the BE53-3, used in the P.1127, 11,500 lbf

[edit] Pegasus 5

Or BS.53-5 (Bristol-Siddeley 53-3). Used for the Hawker Siddeley Kestrel evaluation aircraft. 15,000 lbf

[edit] Pegasus 10

For first Harriers, 20,500 lbf, entering service in 1971.

[edit] Pegasus 11

The Pegasus 11 powered the first generation Harriers, the RAF's Hawker Siddeley Harrier GR.3, the USMC AV-8A and later the Royal Navy's Sea Harrier. The Pegasus 11 produced 21,000 lbf (93.4 kN) and entered service in 1974.

[edit] Pegasus 11-21/Mk.105/Mk.106

The 11-21 was developed for the second generation Harriers, the USMC AV-8B Harrier II and the BAE Harrier IIs. The original model provided an extra 450 lbf (2 kN). The RAF Harriers entered service with the 11-21 Mk.105 which generates 21,500 lbf (96 kN). The Mk.106 development was produced for the Sea Harrier FA2 upgrade and generates 21,750 lbf (97 kN).

[edit] Pegasus 11-61/Mk.107

The 11-61 is the latest and most powerful version of the Pegasus, providing 23,800 lbf (106 kN). This equates to up to 15 percent more thrust at high ambient temperatures, allowing upgraded Harriers to return to an aircraft carrier without having to dump any unused weapons which along with the reduced maintenance reduces total cost of engine use.

This latest Pegasus has also enabled a highly effective radar equipped AV-8B+. This version combines the proven advantages of day and night STOVL operations with an advanced radar system and beyond-visual-range missiles. The RAF/RN is in the process of upgrading its GR7 fleet to GR9 standard, initially through the Joint Upgrade and Maintenance Programme (JUMP) and now through the Harrier Platform Availability Contract (HPAC). All GR7 aircraft are expected to have been upgraded by April 2010. Part of this process is the upgrade of the Mk.105 engines to Mk.107 standard. These aircraft will be known as GR7As and GR9As.

[edit] Specifications (Pegasus 11-61)

General characteristics

Type: Twin spool turbofan
Length: 137 in (3.480 m)
Diameter: 48 in (1.219 m)
Dry weight: 3,960 lb (1,796 kg)

Components

Compressor: 3-stage low pressure, 8-stage high pressure axial flow
Turbine: 2-stage high pressure, 2-stage low pressure

Performance

Maximum Thrust: 23,800 lbf (106 kN)
Overall pressure ratio: 16.3
Thrust-to-weight ratio: 6 lbf/lb

[edit] See also

Rolls-Royce LiftSystem

Related development

Rolls-Royce/MAN Turbo RB193

Comparable engines

Bristol Siddeley BS100

Related lists

List of aircraft engines

[edit] Notes

^ Bolkcom, C. "F-35 Joint Strike Fighter (JSF) Program: Background, Status, and Issues" CRS Report for Congress. (2005). Accessed 14 October 2009.
^ "Air Cadet Publication 33: Flight - Volume 3 Propulsion" 282 East Ham Squadron - Air Training Corps. (2000). Accessed 14 October 2009.
^ http://www.flightglobal.com/pdfarchive/view/1964/1964%20-%201193.html Flight 23 Aprl 1964 p668
^ Flight August 1964 p 328
^ [1]

[edit] References

Not Much of an Engineer, Sir Stanley Hooker, Airlife Publishing, ISBN 0-906393-35-3
Rolls-Royce
Flight Bristol Siddeley Developments IN THE V/STOL POWERPLANT FIELD 1964

[edit] External links

Wikimedia Commons has media related to: Rolls-Royce Pegasus

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[0] Bolkcom, C. "F-35 Joint Strike Fighter (JSF) Program: Background, Status, and Issues" CRS Report for Congress. (2005). Accessed 14 October 2009.

[1] "Air Cadet Publication 33: Flight - Volume 3 Propulsion" 282 East Ham Squadron - Air Training Corps. (2000). Accessed 14 October 2009.

[2] ttp://www.flightglobal.com/pdfarchive/view/1964/1964%20-%201193.html Flight 23 Aprl 1964 p668

[3] Flight August 1964 p 328

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