GB948571A - Gas turbine jet propulsion engine - Google Patents

Gas turbine jet propulsion engine

Info

Publication number
GB948571A
GB948571A GB3807762A GB3807762A GB948571A GB 948571 A GB948571 A GB 948571A GB 3807762 A GB3807762 A GB 3807762A GB 3807762 A GB3807762 A GB 3807762A GB 948571 A GB948571 A GB 948571A
Authority
GB
United Kingdom
Prior art keywords
annular
nozzle
jet pipe
compressed air
space
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB3807762A
Inventor
James Oswald Mortlock
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3807762A priority Critical patent/GB948571A/en
Priority to DER36215A priority patent/DE1223626B/en
Priority to FR949987A priority patent/FR1372176A/en
Publication of GB948571A publication Critical patent/GB948571A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/0058—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with vertical jet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes

Abstract

948,571. Jet-propulsion nozzles for controlling aircraft. ROLLS-ROYCE Ltd. Oct. 8, 1962, No. 38077/62. Headings B7 and G1. [Also in Divisions F1 and F2] A jet pipe for a gas turbine jet propulsion engine has an exhaust nozzle pivotally attached to its downstream end, the exhaust nozzle being spaced from said downstream end and being pivotable to vary the direction in which the exhaust gases are discharged, and means for supplying the space between said jet pipe and said exhaust nozzle with compressed air to reduce leakage of said exhaust gases through said space. The jet pipe 14 has an annular nozzle 16 attached thereto by pivots 17 and spaced from the jet pipe by an annular space 20. Compressed air is bled from the compressor 11 by a pipe 19 to an annular manifold 21 supported on the end 15 of the jet pipe by an annular support 22 which carries also an annular shoe 23 of convex shape to define with the inner surface of nozzle 16 an annular Venturi passage 25. Compressed air from manifold 1 is delivered through ports 30, 28 into the annular space 20, thereby drawing in ambient air and preventing the return flow of exhaust gases from the nozzle. Alternative embodiments are described embodying compressed air and labyrinth seals. The engine may be an aircraft lift engine.
GB3807762A 1962-10-08 1962-10-08 Gas turbine jet propulsion engine Expired GB948571A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB3807762A GB948571A (en) 1962-10-08 1962-10-08 Gas turbine jet propulsion engine
DER36215A DE1223626B (en) 1962-10-08 1963-09-27 Jet pipe for gas turbine engines
FR949987A FR1372176A (en) 1962-10-08 1963-10-08 Oscillating Discharge Cone Nozzle for Gas Turbine Jet Engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3807762A GB948571A (en) 1962-10-08 1962-10-08 Gas turbine jet propulsion engine

Publications (1)

Publication Number Publication Date
GB948571A true GB948571A (en) 1964-02-05

Family

ID=10401015

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3807762A Expired GB948571A (en) 1962-10-08 1962-10-08 Gas turbine jet propulsion engine

Country Status (3)

Country Link
DE (1) DE1223626B (en)
FR (1) FR1372176A (en)
GB (1) GB948571A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3429509A (en) * 1967-05-31 1969-02-25 United Aircraft Corp Cooling scheme for a three bearing swivel nozzle
GB2379483A (en) * 2001-09-08 2003-03-12 Rolls Royce Plc Augmented gas turbine propulsion system
EP1698774A2 (en) 2005-03-02 2006-09-06 Rolls-Royce Plc A turbine engine and a method of operating a turbine engine
US10563613B2 (en) * 2015-08-31 2020-02-18 Rolls-Royce North American Technologies Inc. Coanda device for a round exhaust nozzle

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3540943A1 (en) * 1985-11-19 1987-05-21 Mtu Muenchen Gmbh GAS TURBINE JET ENGINE IN MULTI-SHAFT, TWO-STREAM DESIGN

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2630673A (en) * 1950-09-27 1953-03-10 Gen Electric Cooling means for variable area nozzles
GB724004A (en) * 1952-04-29 1955-02-16 Rolls Royce Improvements in or relating to fuel supply arrangements for gas-turbine engines
FR1279495A (en) * 1960-11-10 1961-12-22 Snecma Jet deflection device for jet aircraft

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3429509A (en) * 1967-05-31 1969-02-25 United Aircraft Corp Cooling scheme for a three bearing swivel nozzle
GB2379483A (en) * 2001-09-08 2003-03-12 Rolls Royce Plc Augmented gas turbine propulsion system
EP1698774A2 (en) 2005-03-02 2006-09-06 Rolls-Royce Plc A turbine engine and a method of operating a turbine engine
US7841185B2 (en) 2005-03-02 2010-11-30 Rolls-Royce Plc Turbine engine and a method of operating a turbine engine
EP1698774A3 (en) * 2005-03-02 2012-11-21 Rolls-Royce Plc A turbine engine and a method of operating a turbine engine
US10563613B2 (en) * 2015-08-31 2020-02-18 Rolls-Royce North American Technologies Inc. Coanda device for a round exhaust nozzle

Also Published As

Publication number Publication date
DE1223626B (en) 1966-08-25
FR1372176A (en) 1964-09-11

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