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Pegasus Variants

Listed below are the 70-plus Pegasus family engines that were used in P.1127/Kestrel/Harrier aircraft or were proposed for other projects over the years. Engines that actually ran are in bold. In addition, there is a section outlining other engines proposed for Kingston V/STOL projects.

Glossary: DECS - Digital Engine Control System, HP - High Pressure, LP - Low Pressure, PCB - Plenum Chamber Burning, RPM - Revolutions Per Minute, TET - Turbine Entry Temperature.
Ratings are sea level, static, uninstalled. Thrust figures divided with a / are for PCB off/on. Other figures are maximum or range of ratings.

Two-stage fan, shaft driven from core. Two vectoring fan nozzles and fixed core nozzle
10,350 lb
Two Olympus 21 stages for fan and BE.25 Orion core
BE.48 with Orpheus 3 core
Offered to Shorts as alternative to RB.108s in SC1
BE.52 with 3-stage fan. Separate intakes for fan and core
11,350-13,000 lb
Fan used Olympus blading. Higher thrust from water/methanol injection
19,000 lb
For Dassault MD 610 Cavalier
Scaled BE.53-5 (Pegasus 5)
19,540 lb
Twin front nozzles and conventional rear nozzle with reheat on P.1141
Civil version of Pegasus
Scaled version of civil Pegasus
For DH.121 Trident
Pegasus 5 derivative
18,100/22,000-26,000 lb
Became Pegasus 5-6
Pegasus with two nozzles for mixed flow
For HS.1175 dry and P.1177 with reheat
Pegasus 1 (BE.53-2)
Two-stage overhung fan. 7-stage HP compressor (from Orpheus). Cannular combustor and single-stage HP turbine. 2-stage LP turbine
9,000 lb
First ran Sep. 1959
Single air intake for fan and core
Pegasus 2 (BE.53-3)
Orpheus 6 HP spool
11,300-12,000 lb
Ran Feb. 1960
Powered first two P.1127s
Pegasus 2A
Fitted with PCB on front nozzles
16,200 lb
Ran Dec. 1962
Installed in Harrier airframe for PCB tests during 1980s
Pegasus 3
8-stage HP spool with improved compressor blades and 2-stage HP turbine. 30hr life
13,500-14,000 lb
Ran Apr. 1961
Used on later P.1127s
Pegasus 4 (BS.53-5D)
Pegasus 5 variant
16,000 lb
Pegasus 5 (BE/BS.53-5)
New 3-stage fan annular combustor, air-cooled HP turbine, variable inlet guide vanes on compressor. Cleared for 50hr 'life'
15,000-15,500 lb
Ran Jun. 1962
For last P.1127 and Kestrels. Designed for 18,400 lb but de-rated
Pegasus 5-2
Pegasus 5 variant
15,500 lb
Flown 1967
For Dornier Do.31
Pegasus 5-4
Pegasus 5 with anhedral nozzles
18,000 lb
For Republic D24CX.
Pegasus 5-5
Pegasus 5-4 with PCB
23,700 lb
For Republic D24CX
Pegasus 5-6
Pegasus 5 variant
15,500-18,400 /22,000-26,000 lb
For AW.681 transport - wing pods with four nozzles. For P.1150 with PCB
Pegasus 5-6A
Uprated Pegasus 5-6 with modified fan, improved HP turbine and re-matched LP turbine
20,450 lb
For WG.681 transport in pods with two rear nozzles for mixed flow. Reduced loss bypass duct
Pegasus 6/Mk 101
Titanium fan, new combustor, water-injection, improved fuel system, 2-vane nozzles. Air-cooled 2nd stage HP turbine. 300hr life
19,000 lb
Ran Mar. 1965.
P.1127(RAF) and Harier GR.1
Pegasus 6F
Pegasus 6 with increased fan mass-flow (444lb/sec.) and 30°C increase in TET
21,000 lb
Investigated for developed Harrier 1966
Pegasus 6PCB
Pegasus 6 with PCB (725°K)
23,000 lb
Alternative for developed Harrier. PCB rig tests undertaken at NGTE
Pegasus 7
Uprated Pegasus 6
20,750/23,950 lb
Pegasus 8
No information available
Pegasus 9
Pegasus 10 with 2 inch larger fan (480 lb/sec.) and 90°C TET increase
22,500/26,000 lb
For HS.1176 without PCB
Pegasus 9D
Uprated Pegasus 9 with 2.25 inch fan diameter increase over Pegasus 10
25,000 lb
Became Pegasus 15
Pegasus 9D-03
Pegasus 9D with PCB
34,000 lb
For HS.1179. Became Pegasus 15-03
Pegasus 10/Mk 102 /F402-RR-400/Mk 802
Pegasus 6 with higher fan RPM, 20°C increase in TET & 32% increase in water flow. 400hr 'life'
20,500 lb
Ran Feb. 1969. In service 1971
Harrier GR.1A & AV-8A
Pegasus 11 /Mk 103/F402-RR-401 & 402/Mk 803
Increased airflow with rebladed fan. TET increased to 1,511°K. 800hr 'life'
21,500 lb
Ran Aug. 1969. Type test Feb. 1971
Harrier GR.4, T.4 and AV-8A, AV-8C and Spanish Matador. DECS trials on No.922
Pegasus 11 /Mk 104
Mk.103 with magensium casing replaced by aluminium
21,500 lb
Ran 1976. Flown Aug.1978
Sea Harrier FRS.1 and FRS.51
Pegasus 11-03
Pegasus 11 with PCB and anhedral nozzles
22,050/30,850 lb
Proposed for
AV-8SX & P.1212/P.1216 demonstrators
Pegasus 11-03B
Pegasus 11 with PCB and anhedral nozzles
27,000 lb
Ran 1988
Tested at Shoeburyness in Harrier airframe
Pegasus 11-21/Mk 105/F402-RR-404 &404A
Uprated gearbox. 404A and RAF Mk.105 fitted with DECS. 1,000hr 'life'
21,150-21,750 lb
Ran Sep. 1980. In service 1984
For YAV-8B, early AV-8B, GR.5 and GR.7
Pegasus 11-21/Mk 106/F402-RR-406 & 406A/Mk 152-42
HP turbine with single crystal blades. 406A has DECS
21,450 lb
Ran 1985
Later AV-8Bs/TAV-8B and Spanish EAV-8B. Rebuilt from Mk.104 for Sea Harrier F/A.2
Pegasus 11-21E
Uprated gearbox and component improvements
22,200 lb
For BAe Big Wing Harrier GR.5(K)
Pegasus 11-21J
Used for DECS development
21,750 lb
Flown 1983
Test version of Mk.105
Pegasus 11-21K
Used for DECS development
21,450 lb
Flown 1984
Vest version of F402-RR-406
Pegasus 11D
Pegasus 11 with aerodynamic improvements
22,300 lb
Pegasus 11D-43
Pegasus 11D with PCB
30,850 lb
For early HS.1205
Pegasus 11+
Pegasus 11D with inreased RPM and 90° TET increase
22,500 lb
Ran late 1974
Tests used Pegasus 11 compressors with Pegasus 15 hot end. Became Pegasus 12
Pegasus 11F-33
Pegasus 11F-35 with PCB
22,300/33,700 lb
For later P.1205
Pegasus 11F-33B
Pegasus 11F-35 with higher PCB temperature
Core mass flow
209 lb/sec
Pegasus 11F-33C
Pegasus 11F-35 with 7% larger front nozzles and smaller rear nozzles
22,840/32,220 lb
For P.1209. 1,600°K PCB
Pegasus 11F-35
Rebladed LP compressor with 4.5% inrease in mass flow and 7% in RPM
22,700-23,500 lb
Ran 1981
Fan tested at RR Halford lab. 23,000 lb recorded
Pegasus 11F-36A
Scaled Pegasus 11F-35 with two mixed flow nozzles
For BAe Warton P.109. Afterburner equipped version schemed
Pegasus 11F-36B
Pegasus 11F-36A with larger fan and 40°C increase in SOT
For BAe Warton P.109
Pegasus 11F-38
Pegasus 11F-33 with three nozzles
34,000 lb
For P.1212/1214/1216. Single rear nozzle gave improved efficiency
Pegasus 11F-38B
Pegasus 11F-33B with three nozzles
Pegasus 11-61
Higher pressure ratio fan (model 64B) and new combustor. Mk.106 turbine
23,800 lb
Ran Jun. 1987. First flown Jun. 1989
Flown in Harrier GR.Mk.5 ZD402
Pegasus 11-61E/Mk107/F402-RR-408
Service version of 11-61. Derated for longer life
23,400 lb
For AV-8B(NA), Harrier II Plus and RAF GR.Mk.7A/9A. Fitted with DECS
Pegasus 12
Pegasus 11+ re-numbered
22,500 lb
Pegasus 12D
Pegasus 12 with improvements
Pegasus 13
Pegasus 11 with improved HP pressure ratio
Pegasus 14
Pegasus 9 with improved HP pressure ratio
Pegasus 15/Mk201/F402-RR-403
Formerly Pegasus 9D. New LP turbine, modified HP turbine and better aerodynamics. TET 1,285°C
24,500 lb
Ran May 1972
24,900 lb on test
Pegasus 15-01
Pegasus 15 with fan increased by 0.5 inch diameter
25,000 lb
For AV-16
Pegasus 15-02
Pegasus 15 with 1.25 inch smaller fan
24,500 lb
For HS.1184
Pegasus 15-03
Pegasus 15 with PCB. Formerly Pegasus 9D-03
34,000 lb
For HS.1185
Pegasus 15-13
Pegasus 15 PCB for subsonic & transonic aircraft
AV-16S variants
Pegasus 15-23
Pegasus 15 PCB for supersonic aircraft
AV-16S variants
Pegasus 16
Pegasus 10 with new, four-stage fan and TET of 1,660°K
34,000 lb
Pegasus 16-01
Uprated Pegasus 16. Fan 4 inches larger diameter than Pegasus 10
35,500 lb
Pegasus 16c
Pegasus 16 with either no 'boost', with PCB and/or reheat in fixed rear nozzle(s) plus 'clang-box' for core
HS.1186, HS.1187 variants and HS.1188
Pegasus 17
No information available
Pegasus 18-01
Pegasus with new high temperature turbines
26,000 lb
Pegasus 18-06
Pegasus 18-01 with two mixed flow nozzles
Renumbered RB.508-01
Pegasus 18-21
Pegasus 18-01 with improved compressors
Pegasus 19
Four nozzles, non-PCB
Pegasus 19-03
Pegasus 19 with PCB
c. 1985
Pegasus 420-01
Liquid hydrogen fuelled with single nozzle
26,000 lb (29,000 lb in emergency)
Propsed for NASA Space Shuttle in pod mounting
'Straight-through' Pegasus with smaller fan and reheat
For HS.1202
Pegasus 11-61 development
25,300 lb dry, 41,300 lb reheat, 27,000 lb in lift mode
Stowable lift nozzles and rear afterburner
Developed Pegasus 11-21 with new fan
25,000 lb+
Ran Oct. 1986
Led to Pegasus 11-61

While not a Pegasus, the engine of the P.1154 should also be mentioned:
Phase II
Four nozzle, PCB equipped vectored thrust engine
26,200/35,900 lb
Ran Oct. 1964
52 inch four stage fan. Olympus 22 HP compressor
The BS.100/3 with 3-stage fan was originally proposed (itself a 0.911 scale of the BS.100/3 for the Fokker-Republic D24 Allianz), rated at 33,150 lb, for the P.1154. The BS.100/8 was originally lower rated for development (Phase I - 32,340 lb). Phase III rating was to be 39,250 lb, available in 1972.

Other engines proposed for Kingston V/STOL projects

Compressors (LP+HP)
Turbines (HP+LP)
Mass flow (lb/sec.)
Pressure ratio
Bypass ratio
Dry weight (lb)
Rating lb (dry/augmented)
Rolls-Royce RB.108
For P.1126
Rolls-Royce RB.153 (1950's)
For P.1137-P.1143
Rolls-Royce RB.162
For P.1144 - P.1149, P.1155 & P.1159
For P.1163 & HS.1170
Rolls-Royce RB.153 (1960's)
4 + 12
2 + 2
For P.1157
Rolls-Royce/Allison XJ-99
2 + 4
1 + 1
For HS.1175 & HS.1177
Rolls-Royce Spey PCB (RB.168D)
5 + 12
2 + 2
For P.1154
Turbo-Union RB.199
3 + 3 + 6
1 + 1 + 2
For HS.1179
Rolls-Royce RB.422-60
3 + 5
1 + 2
For P.1212, P.1216, P.1221, P.1226 & P.1230.

RB.422-60 was originally known as RB.422-X. A derated version was designated RB.422-57. These were successors to the similar three-nozzle, PCB-equipped RB.422-48, which had a bpr of 1.3. The RB.422-49 had reheat in the single rear nozzle in addition to PCB. The RB.422-21 was a four-nozzle subsonic version of the -48. The RB.422-43 was a supersonic four-nozzle version with PCB. The RB.422-56 was a two-nozzle, mixed flow version for transonic applications. Finally, the RB.422-06 was a non-PCB, four nozzle version from 1972 for the HS.1184-7.

The RB.532 was a PCB engine for later P.1216 variants with three nozzles. Four nozzle variants were also schemed. The RB.533 was a non PCB variant with either four nozzles or with a two-nozzle, mixed flow configuration.

The RB.406 was a variable cycle vectored thrust engine used in the HS.1198.

The RB.428 was a three-poster engine for the HS.1185-26 with PCB.

The P.1222 was to be powered by a Rolls-Royce Hybrid Fan Vectored Thrust engine of some 56,000 lb thrust.


Compiled by Michael Pryce. Derived from source material at the Public Record Office, from Alan Baxter's article 'Pegasus Projects - variants that never saw the light of day' in Sleeve Notes, the archive of Brooklands Museum, Bill Gunston's 'Rolls-Royce Aero Engines', 'Pegasus in Space' by Reg Cant and Peter Pavey and the books listed on our Sources page.


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