[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

FR2096538A1 - VARIABLE SECTION THRUST REVERSE TUBE - Google Patents

VARIABLE SECTION THRUST REVERSE TUBE

Info

Publication number
FR2096538A1
FR2096538A1 FR7110666A FR7110666A FR2096538A1 FR 2096538 A1 FR2096538 A1 FR 2096538A1 FR 7110666 A FR7110666 A FR 7110666A FR 7110666 A FR7110666 A FR 7110666A FR 2096538 A1 FR2096538 A1 FR 2096538A1
Authority
FR
France
Prior art keywords
variable section
thrust reverse
reverse tube
section thrust
tube
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.)
Pending
Application number
FR7110666A
Other languages
French (fr)
Inventor
Tyra Johnson Jerry
Van Sutherland William
Andrew Krabacher Roy
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 FR2096538A1 publication Critical patent/FR2096538A1/en
Pending 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1215—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 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
    • F02K1/1223—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 upstream ends on the downstream ends of the flaps of the upstream series
    • 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
    • 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)
  • Control Of Turbines (AREA)
FR7110666A 1970-06-29 1971-03-25 VARIABLE SECTION THRUST REVERSE TUBE Pending FR2096538A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US5041470A 1970-06-29 1970-06-29

Publications (1)

Publication Number Publication Date
FR2096538A1 true FR2096538A1 (en) 1972-02-18

Family

ID=21965121

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7110666A Pending FR2096538A1 (en) 1970-06-29 1971-03-25 VARIABLE SECTION THRUST REVERSE TUBE

Country Status (3)

Country Link
US (1) US3610533A (en)
CA (1) CA929358A (en)
FR (1) FR2096538A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2525688A1 (en) * 1982-04-26 1983-10-28 Nightingale Douglas NOZZLE FOR TURBOMACHINE
US4502639A (en) * 1982-04-26 1985-03-05 Rolls-Royce Inc. Turbomachine ejector nozzle
US4502638A (en) * 1982-04-26 1985-03-05 Rolls-Royce Inc. Turbomachine ejector nozzle and thrust reverser
EP0622538A1 (en) * 1993-04-29 1994-11-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable geometry exhaust nozzle for turbomachine
EP0647777A1 (en) * 1993-10-06 1995-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Axis-symmetric, convergent/divergent exhaust nozzle with thrust reverser

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1288834A (en) * 1970-03-14 1972-09-13
US3747855A (en) * 1972-03-01 1973-07-24 Gen Electric Propulsion nozzles
US3913869A (en) * 1973-09-10 1975-10-21 American Optical Corp Slow-speed tape recorder drive mechanism
US4043121A (en) * 1975-01-02 1977-08-23 General Electric Company Two-spool variable cycle engine
GB1504793A (en) * 1975-02-14 1978-03-22 Rolls Royce Ducted fan gas turbine engine gas flow ducts
US4026105A (en) * 1975-03-25 1977-05-31 The Boeing Company Jet engine thrust reverser
US4043509A (en) * 1976-05-13 1977-08-23 General Electric Company Actuation system for a gas turbine engine exhaust device
FR2712929B1 (en) * 1993-11-24 1995-12-29 Hispano Suiza Sa Dual flow turbojet thrust reverser.
US6948317B2 (en) * 2003-10-31 2005-09-27 General Electric Company Methods and apparatus for flade engine nozzle
US9611808B2 (en) * 2014-03-21 2017-04-04 Rohr, Inc. Blocker door lock mechanism of a thrust reverser for a turbofan engine
US10451002B2 (en) * 2016-01-22 2019-10-22 Honeywell International Inc. Translating cowl thrust reverser that prevents unintended door rotation
US11754018B2 (en) * 2021-12-17 2023-09-12 Rohr, Inc. Aircraft propulsion system exhaust nozzle with ejector passage(s)
US12065977B2 (en) 2022-07-22 2024-08-20 Rtx Corporation Multi-duct exhaust system for gas turbine engine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2525688A1 (en) * 1982-04-26 1983-10-28 Nightingale Douglas NOZZLE FOR TURBOMACHINE
US4502639A (en) * 1982-04-26 1985-03-05 Rolls-Royce Inc. Turbomachine ejector nozzle
US4502638A (en) * 1982-04-26 1985-03-05 Rolls-Royce Inc. Turbomachine ejector nozzle and thrust reverser
EP0622538A1 (en) * 1993-04-29 1994-11-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable geometry exhaust nozzle for turbomachine
FR2704599A1 (en) * 1993-04-29 1994-11-04 Snecma Variable geometry ejection nozzle for turbomachine.
EP0647777A1 (en) * 1993-10-06 1995-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Axis-symmetric, convergent/divergent exhaust nozzle with thrust reverser
FR2710951A1 (en) * 1993-10-06 1995-04-14 Snecma Axisymmetric, convergent-divergent turbojet exhaust nozzle with reverse thrust.
US5470020A (en) * 1993-10-06 1995-11-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Combination turbojet engine nozzle and thrust reverser

Also Published As

Publication number Publication date
CA929358A (en) 1973-07-03
US3610533A (en) 1971-10-05

Similar Documents

Publication Publication Date Title
FR2096538A1 (en) VARIABLE SECTION THRUST REVERSE TUBE
CH519905A (en) Centrifuge tube
NL178813B (en) TUBE CONNECTION.
NL172271C (en) TUBE SCREW CONNECTION.
AT310515B (en) Pipe connection
DK134361B (en) Snake.
CH538626A (en) Pipe connection
IT941346B (en) SEGMENTED GEARS
BE806118A (en) PROXIMITY ROCKET
CH530270A (en) Line end control arrangement
NL168924C (en) TUBE CONNECTION.
BE764642R (en) TUBE
IT972401B (en) TUBULAR BULLET
AT318327B (en) tube
IT965633B (en) IMPROVEMENTS REGARDING EXTRUSION
BE801421A (en) TUBE PART WITH FLANNED END
AT326034B (en) CLEAR, EXPRESSABLE TUBE
AT307832B (en) Pipe connection
BE746697R (en) TUBE A
CH542667A (en) Tube bending machine
SE417546B (en) Piston-cylinder assembly
AT325332B (en) ELECTROFLUIDIC CONVERTER
AT316230B (en) Pipe connection
BE762995A (en) PIPE CONNECTION WITH BRANCH
CH519149A (en) Tube furnace