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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.
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Designation(s)
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Description
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Rating(s)
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Dates
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Comments
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BE.48
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Two-stage fan, shaft driven from core. Two
vectoring fan nozzles and fixed core nozzle
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10,350 lb
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1956
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Two Olympus 21 stages for fan and BE.25 Orion
core
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BE.52
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BE.48 with Orpheus 3 core
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1956-57
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Offered to Shorts as alternative to RB.108s
in SC1
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BE.53
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BE.52 with 3-stage fan. Separate intakes for
fan and core
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11,350-13,000 lb
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1957
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Fan used Olympus blading. Higher thrust from
water/methanol injection
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BE.53-8
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19,000 lb
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1960
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For Dassault MD 610 Cavalier
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BE.53-11
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Scaled BE.53-5 (Pegasus 5)
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19,540 lb
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1960
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Twin front nozzles and conventional rear nozzle
with reheat on P.1141
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BE.58
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Civil version of Pegasus
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BE.61
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Scaled version of civil Pegasus
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For DH.121 Trident
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BS.53-6
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Pegasus 5 derivative
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18,100/22,000-26,000 lb
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1961
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Became Pegasus 5-6
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BS.53-103
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Pegasus with two nozzles for mixed flow
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1966
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For HS.1175 dry and P.1177 with reheat
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Pegasus 1 (BE.53-2)
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Two-stage overhung fan. 7-stage HP compressor
(from Orpheus). Cannular combustor and single-stage HP turbine. 2-stage LP turbine
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9,000 lb
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First ran Sep. 1959
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Single air intake for fan and core
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Pegasus 2 (BE.53-3)
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Orpheus 6 HP spool
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11,300-12,000 lb
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Ran Feb. 1960
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Powered first two P.1127s
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Pegasus 2A
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Fitted with PCB on front nozzles
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16,200 lb
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Ran Dec. 1962
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Installed in Harrier airframe for PCB tests
during 1980s
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Pegasus 3
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8-stage HP spool with improved compressor blades
and 2-stage HP turbine. 30hr life
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13,500-14,000 lb
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Ran Apr. 1961
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Used on later P.1127s
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Pegasus 4 (BS.53-5D)
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Pegasus 5 variant
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16,000 lb
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1961
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Pegasus 5 (BE/BS.53-5)
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New 3-stage fan annular combustor, air-cooled
HP turbine, variable inlet guide vanes on compressor. Cleared for 50hr 'life'
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15,000-15,500 lb
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Ran Jun. 1962
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For last P.1127 and Kestrels. Designed for
18,400 lb but de-rated
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Pegasus 5-2
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Pegasus 5 variant
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15,500 lb
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Flown 1967
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For Dornier Do.31
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Pegasus 5-4
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Pegasus 5 with anhedral nozzles
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18,000 lb
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For Republic D24CX.
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Pegasus 5-5
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Pegasus 5-4 with PCB
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23,700 lb
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For Republic D24CX
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Pegasus 5-6
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Pegasus 5 variant
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15,500-18,400 /22,000-26,000 lb
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1963
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For AW.681 transport - wing pods with four
nozzles. For P.1150 with PCB
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Pegasus 5-6A
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Uprated Pegasus 5-6 with modified fan, improved
HP turbine and re-matched LP turbine
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20,450 lb
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1963
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For WG.681 transport in pods with two rear
nozzles for mixed flow. Reduced loss bypass duct
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Pegasus 6/Mk 101
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Titanium fan, new combustor, water-injection,
improved fuel system, 2-vane nozzles. Air-cooled 2nd stage HP turbine. 300hr life
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19,000 lb
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Ran Mar. 1965.
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P.1127(RAF) and Harier GR.1
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Pegasus 6F
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Pegasus 6 with increased fan mass-flow (444lb/sec.)
and 30°C increase in TET
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21,000 lb
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1965-66
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Investigated for developed Harrier 1966
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Pegasus 6PCB
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Pegasus 6 with PCB (725°K)
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23,000 lb
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1965-66
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Alternative for developed Harrier. PCB rig
tests undertaken at NGTE
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Pegasus 7
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Uprated Pegasus 6
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20,750/23,950 lb
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1965
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Pegasus 8
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No information available
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Pegasus 9
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Pegasus 10 with 2 inch larger fan (480 lb/sec.)
and 90°C TET increase
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22,500/26,000 lb
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1966
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For HS.1176 without PCB
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Pegasus 9D
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Uprated Pegasus 9 with 2.25 inch fan diameter
increase over Pegasus 10
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25,000 lb
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Became Pegasus 15
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Pegasus 9D-03
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Pegasus 9D with PCB
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34,000 lb
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For HS.1179. Became Pegasus 15-03
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Pegasus 10/Mk 102 /F402-RR-400/Mk 802
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Pegasus 6 with higher fan RPM, 20°C increase
in TET & 32% increase in water flow. 400hr 'life'
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20,500 lb
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Ran Feb. 1969. In service 1971
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Harrier GR.1A & AV-8A
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Pegasus 11 /Mk 103/F402-RR-401 & 402/Mk
803
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Increased airflow with rebladed fan. TET increased
to 1,511°K. 800hr 'life'
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21,500 lb
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Ran Aug. 1969. Type test Feb. 1971
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Harrier GR.4, T.4 and AV-8A, AV-8C and Spanish
Matador. DECS trials on No.922
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Pegasus 11 /Mk 104
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Mk.103 with magensium casing replaced by aluminium
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21,500 lb
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Ran 1976. Flown Aug.1978
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Sea Harrier FRS.1 and FRS.51
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Pegasus 11-03
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Pegasus 11 with PCB and anhedral nozzles
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22,050/30,850 lb
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c.1981
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Proposed for
AV-8SX & P.1212/P.1216 demonstrators
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Pegasus 11-03B
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Pegasus 11 with PCB and anhedral nozzles
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27,000 lb
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Ran 1988
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Tested at Shoeburyness in Harrier airframe
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Pegasus 11-21/Mk 105/F402-RR-404 &404A
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Uprated gearbox. 404A and RAF Mk.105 fitted
with DECS. 1,000hr 'life'
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21,150-21,750 lb
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Ran Sep. 1980. In service 1984
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For YAV-8B, early AV-8B, GR.5 and GR.7
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Pegasus 11-21/Mk 106/F402-RR-406 & 406A/Mk
152-42
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HP turbine with single crystal blades. 406A
has DECS
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21,450 lb
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Ran 1985
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Later AV-8Bs/TAV-8B and Spanish EAV-8B. Rebuilt
from Mk.104 for Sea Harrier F/A.2
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Pegasus 11-21E
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Uprated gearbox and component improvements
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22,200 lb
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c.1979
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For BAe Big Wing Harrier GR.5(K)
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Pegasus 11-21J
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Used for DECS development
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21,750 lb
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Flown 1983
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Test version of Mk.105
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Pegasus 11-21K
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Used for DECS development
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21,450 lb
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Flown 1984
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Vest version of F402-RR-406
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Pegasus 11D
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Pegasus 11 with aerodynamic improvements
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22,300 lb
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Pegasus 11D-43
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Pegasus 11D with PCB
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30,850 lb
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c.1976
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For early HS.1205
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Pegasus 11+
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Pegasus 11D with inreased RPM and 90° TET
increase
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22,500 lb
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Ran late 1974
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Tests used Pegasus 11 compressors with Pegasus
15 hot end. Became Pegasus 12
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Pegasus 11F-33
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Pegasus 11F-35 with PCB
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22,300/33,700 lb
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c.1978-80
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For later P.1205
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Pegasus 11F-33B
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Pegasus 11F-35 with higher PCB temperature
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Core mass flow
209 lb/sec
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Pegasus 11F-33C
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Pegasus 11F-35 with 7% larger front nozzles
and smaller rear nozzles
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22,840/32,220 lb
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1978-79
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For P.1209. 1,600°K PCB
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Pegasus 11F-35
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Rebladed LP compressor with 4.5% inrease in
mass flow and 7% in RPM
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22,700-23,500 lb
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Ran 1981
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Fan tested at RR Halford lab. 23,000 lb recorded
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Pegasus 11F-36A
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Scaled Pegasus 11F-35 with two mixed flow nozzles
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For BAe Warton P.109. Afterburner equipped
version schemed
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Pegasus 11F-36B
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Pegasus 11F-36A with larger fan and 40°C
increase in SOT
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For BAe Warton P.109
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Pegasus 11F-38
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Pegasus 11F-33 with three nozzles
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34,000 lb
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For P.1212/1214/1216. Single rear nozzle gave
improved efficiency
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Pegasus 11F-38B
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Pegasus 11F-33B with three nozzles
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Pegasus 11-61
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Higher pressure ratio fan (model 64B) and new
combustor. Mk.106 turbine
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23,800 lb
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Ran Jun. 1987. First flown Jun. 1989
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Flown in Harrier GR.Mk.5 ZD402
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Pegasus 11-61E/Mk107/F402-RR-408
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Service version of 11-61. Derated for longer
life
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23,400 lb
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1990
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For AV-8B(NA), Harrier II Plus and RAF GR.Mk.7A/9A.
Fitted with DECS
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Pegasus 12
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Pegasus 11+ re-numbered
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22,500 lb
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Pegasus 12D
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Pegasus 12 with improvements
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Pegasus 13
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Pegasus 11 with improved HP pressure ratio
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Pegasus 14
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Pegasus 9 with improved HP pressure ratio
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Pegasus 15/Mk201/F402-RR-403
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Formerly Pegasus 9D. New LP turbine, modified
HP turbine and better aerodynamics. TET 1,285°C
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24,500 lb
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Ran May 1972
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24,900 lb on test
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Pegasus 15-01
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Pegasus 15 with fan increased by 0.5 inch diameter
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25,000 lb
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For AV-16
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Pegasus 15-02
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Pegasus 15 with 1.25 inch smaller fan
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24,500 lb
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For HS.1184
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Pegasus 15-03
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Pegasus 15 with PCB. Formerly Pegasus 9D-03
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34,000 lb
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For HS.1185
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Pegasus 15-13
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Pegasus 15 PCB for subsonic & transonic
aircraft
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AV-16S variants
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Pegasus 15-23
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Pegasus 15 PCB for supersonic aircraft
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AV-16S variants
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Pegasus 16
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Pegasus 10 with new, four-stage fan and TET
of 1,660°K
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34,000 lb
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Pegasus 16-01
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Uprated Pegasus 16. Fan 4 inches larger diameter
than Pegasus 10
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35,500 lb
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Pegasus 16c
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Pegasus 16 with either no 'boost', with PCB
and/or reheat in fixed rear nozzle(s) plus 'clang-box' for core
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HS.1186, HS.1187 variants and HS.1188
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Pegasus 17
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No information available
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Pegasus 18-01
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Pegasus with new high temperature turbines
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26,000 lb
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1982
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Pegasus 18-06
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Pegasus 18-01 with two mixed flow nozzles
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Renumbered RB.508-01
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Pegasus 18-21
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Pegasus 18-01 with improved compressors
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Pegasus 19
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Four nozzles, non-PCB
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c.1984
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P.1227-3
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Pegasus 19-03
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Pegasus 19 with PCB
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c. 1985
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P.1231-1
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Pegasus 420-01
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Liquid hydrogen fuelled with single nozzle
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26,000 lb (29,000 lb in emergency)
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1970
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Propsed for NASA Space Shuttle in pod mounting
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RB.431
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'Straight-through' Pegasus with smaller fan
and reheat
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For HS.1202
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RB.578
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Pegasus 11-61 development
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25,300 lb dry, 41,300 lb reheat, 27,000 lb
in lift mode
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Stowable lift nozzles and rear afterburner
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XG.15
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Developed Pegasus 11-21 with new fan
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25,000 lb+
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Ran Oct. 1986
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Led to Pegasus 11-61
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While not a Pegasus, the engine of the P.1154 should also be mentioned:
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BS.100/8
Phase II
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Four nozzle, PCB equipped vectored thrust engine
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26,200/35,900 lb
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Ran Oct. 1964
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52 inch four stage fan. Olympus 22 HP compressor
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| 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
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Engine
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Compressors (LP+HP)
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Turbines (HP+LP)
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Mass flow (lb/sec.)
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Pressure ratio
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Bypass ratio
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Dry weight (lb)
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Rating lb (dry/augmented)
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Comments
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Rolls-Royce RB.108
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8
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2
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38.8
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5.5
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-
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235
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2130/-
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For P.1126
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Rolls-Royce RB.153 (1950's)
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9
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2
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?
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?
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-
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855
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4,000/5,400
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For P.1137-P.1143
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Rolls-Royce RB.162
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6
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1
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84
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4.25
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-
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c.300
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4,400-6,000/-
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For P.1144 - P.1149, P.1155 & P.1159
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BS.94/5
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?
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?
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?
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?
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c.1
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c.2200
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c.11,500/18,500
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For P.1163 & HS.1170
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Rolls-Royce RB.153 (1960's)
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4 + 12
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2 + 2
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121
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18
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0.7
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1710
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6,850/11,645
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For P.1157
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Rolls-Royce/Allison XJ-99
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2 + 4
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1 + 1
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102
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8.3
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-
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440
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c.9,000/-
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For HS.1175 & HS.1177
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Rolls-Royce Spey PCB (RB.168D)
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5 + 12
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2 + 2
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c.210
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20
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c.0.7
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c.3,300
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12,000/18,000
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For P.1154
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Turbo-Union RB.199
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3 + 3 + 6
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1 + 1 + 2
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154
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23
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1
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2,000
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9,000/16,000
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For HS.1179
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Rolls-Royce RB.422-60
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3 + 5
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1 + 2
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439.2
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20
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1
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4,643
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31,400/44,600
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For P.1212, P.1216, P.1221, P.1226 & P.1230.
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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.
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Sources:
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.
Links
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