GB1142660A - Improvements in combination jet exhaust nozzle and thrust reverser - Google Patents

Improvements in combination jet exhaust nozzle and thrust reverser

Info

Publication number
GB1142660A
GB1142660A GB35936/66A GB3593666A GB1142660A GB 1142660 A GB1142660 A GB 1142660A GB 35936/66 A GB35936/66 A GB 35936/66A GB 3593666 A GB3593666 A GB 3593666A GB 1142660 A GB1142660 A GB 1142660A
Authority
GB
United Kingdom
Prior art keywords
flaps
nozzle
exhaust gas
thrust reverser
deflecting vanes
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
GB35936/66A
Inventor
Henry Anton Carl
Robert Cooper Foster Jr
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1142660A publication Critical patent/GB1142660A/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
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their flaps hinged at their upstream ends on a fixed structure
    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1246—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their downstream ends on a substantially axially movable structure
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/62—Reversing jet main flow by blocking the rearward discharge by means of flaps
    • F02K1/625—Reversing jet main flow by blocking the rearward discharge by means of flaps the aft end of the engine cowling being movable to uncover openings for the reversed flow
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exhaust Silencers (AREA)
  • Supercharger (AREA)

Abstract

1,142,660. Jet exhaust nozzle and thrust reverser. GENERAL ELECTRIC CO. 11 Aug., 1966, No. 35936/66. Heading B7G. [Also in Division F1] A combined variable area convergent-divergent nozzle and thrust reverser for a jet propulsion engine jet pipe 86 comprises primary flaps 110, secondary flaps 87 and exhaust gas deflecting vanes 134. The primary flaps 110 are pivoted to a ring 124 which is movable axially moving the primary flaps between a first position (shown in full lines) and a second position (shown in broken lines) varying the nozzle throat area, and a third position, Fig. 4 (not shown) in which the flaps 110 block the jet pipe diverting the exhaust gas air flow through the deflecting vanes 134. The secondary flaps 87 pivot, e.g. by axial movement of ring 95, to vary the nozzle outlet area and may be retractible to a position forward of the deflected exhaust gas opening 140 during subsonic flight, Fig. 2 (not shown). The deflecting vanes 134 may be permanently located inside the opening 140 over which a cover 144 may be slid during forward thrust conditions. The nozzle may have a centre body 80 and there may be seals 154 to prevent reverse gas flow during forward thrust conditions. Movement of the flaps 110 and 87, and rings 124 and 95 are controlled by actuators 150 and link mechanisms 132, 104, 114, 98.
GB35936/66A 1963-08-07 1966-08-11 Improvements in combination jet exhaust nozzle and thrust reverser Expired GB1142660A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US30053463A 1963-08-07 1963-08-07
DEG0047737 1966-08-24

Publications (1)

Publication Number Publication Date
GB1142660A true GB1142660A (en) 1969-02-12

Family

ID=25978834

Family Applications (1)

Application Number Title Priority Date Filing Date
GB35936/66A Expired GB1142660A (en) 1963-08-07 1966-08-11 Improvements in combination jet exhaust nozzle and thrust reverser

Country Status (3)

Country Link
BE (1) BE687391A (en)
DE (1) DE1526820A1 (en)
GB (1) GB1142660A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2156004A (en) * 1984-03-15 1985-10-02 Gen Electric Thrust modulation device for a gas turbine engine
GB2189550A (en) * 1986-04-25 1987-10-28 Rolls Royce A gas turbine engine powerplant with flow control devices
GB2347126A (en) * 1999-02-23 2000-08-30 Rolls Royce Plc Thrust reverser with translating cascades
GB2456386A (en) * 1985-04-17 2009-07-22 Snecma Nozzle assembly for a turbo-jet engine
WO2012166271A3 (en) * 2011-05-24 2013-04-11 Advanced Technologies Group, Inc. Adjustable exhaust apparatus for a ram air turbine generating system
WO2015028755A1 (en) 2013-08-30 2015-03-05 Aircelle Nacelle comprising a thrust reverser device with maintained mobile grids
US20170159606A1 (en) * 2015-12-03 2017-06-08 General Electric Company Thrust Reverser System for a Gas Turbine Engine
CN113530706A (en) * 2021-08-18 2021-10-22 中国航发贵阳发动机设计研究所 Connecting structure of active adjusting sheet and active adjusting sheet of engine tail nozzle

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2156004A (en) * 1984-03-15 1985-10-02 Gen Electric Thrust modulation device for a gas turbine engine
GB2456386A (en) * 1985-04-17 2009-07-22 Snecma Nozzle assembly for a turbo-jet engine
GB2456386B (en) * 1985-04-17 2010-01-13 Snecma Jet Nozzle
GB2189550A (en) * 1986-04-25 1987-10-28 Rolls Royce A gas turbine engine powerplant with flow control devices
US6434927B1 (en) 1999-02-23 2002-08-20 Rolls Royce Plc (Derby) Thrust reverser
GB2347126B (en) * 1999-02-23 2003-02-12 Rolls Royce Plc Thrust reverser
US6474059B2 (en) 1999-02-23 2002-11-05 Rolls-Royce Plc Thrust reverser
GB2347126A (en) * 1999-02-23 2000-08-30 Rolls Royce Plc Thrust reverser with translating cascades
WO2012166271A3 (en) * 2011-05-24 2013-04-11 Advanced Technologies Group, Inc. Adjustable exhaust apparatus for a ram air turbine generating system
WO2015028755A1 (en) 2013-08-30 2015-03-05 Aircelle Nacelle comprising a thrust reverser device with maintained mobile grids
US20170159606A1 (en) * 2015-12-03 2017-06-08 General Electric Company Thrust Reverser System for a Gas Turbine Engine
US10247136B2 (en) * 2015-12-03 2019-04-02 General Electric Company Thrust reverser system for a gas turbine engine
CN113530706A (en) * 2021-08-18 2021-10-22 中国航发贵阳发动机设计研究所 Connecting structure of active adjusting sheet and active adjusting sheet of engine tail nozzle
CN113530706B (en) * 2021-08-18 2022-08-05 中国航发贵阳发动机设计研究所 Connecting structure of outer adjusting piece and active adjusting piece of engine tail nozzle

Also Published As

Publication number Publication date
BE687391A (en) 1967-03-01
DE1526820A1 (en) 1970-05-14

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