EP2496817A1 - Dispositif d'inversion de poussee - Google Patents

Dispositif d'inversion de poussee

Info

Publication number
EP2496817A1
EP2496817A1 EP10787831A EP10787831A EP2496817A1 EP 2496817 A1 EP2496817 A1 EP 2496817A1 EP 10787831 A EP10787831 A EP 10787831A EP 10787831 A EP10787831 A EP 10787831A EP 2496817 A1 EP2496817 A1 EP 2496817A1
Authority
EP
European Patent Office
Prior art keywords
flap
nacelle
lever
lever arm
cowl
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.)
Withdrawn
Application number
EP10787831A
Other languages
German (de)
English (en)
French (fr)
Inventor
Pierre Caruel
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.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
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 Aircelle SA filed Critical Aircelle SA
Publication of EP2496817A1 publication Critical patent/EP2496817A1/fr
Withdrawn legal-status Critical Current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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • 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
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Definitions

  • flaps are pivotally mounted on the sliding cowl between a retracted position in which they provide, with said movable cowl, aerodynamic continuity of the inner wall of the nacelle and a deployed position in which, in reverse thrust situation, they come at least partially closing the annular channel to deflect a flow of gas to the deflection grids discovered by the sliding of the movable cowl.
  • Another object of the present invention is to provide a thrust reverser device without connecting rod in the annular channel having a drive system of the simple locking flaps while being reliable.
  • Another object of the present invention is to provide a thrust reverser device without connecting rod in the annular channel in which the impact of the shutter drive system on the structure of the movable cowl and its sealing is limited.
  • the device may comprise one or more of the following features, taken in isolation or in combination technically possible:
  • the first lever arm has a length greater than that of the second lever arm
  • FIG. 1 is a longitudinal sectional view of a thrust reverser device according to a first embodiment of the present invention
  • the thrust reverser device 10 comprises a plurality of inversion flaps 30, distributed around the circumference of the cap 20, and each mounted pivoting at one end around a hinge pin on the sliding cowl 20 between a retracted position in which the flap 30 closes the opening and ensures the internal aerodynamic continuity of the vein V and an extended position in which, in reverse thrust situation, it at least partially closes the vein V in order to deflect a flow of gas towards the gate opening 2.
  • the lever assembly 50 comprises two distinct lever arms 51 and 52 forming a generally V-shaped shape, the tip of which is pivotally mounted about a pivot axis X (in FIG. 3) perpendicular to the plane containing the axis of articulation of the flap 30 and parallel to the longitudinal axis of the nacelle, thanks to a hinge fitting 22 integral with the cover 20.
  • this plan will be designated as the plane P.
  • the pivot axis X of the lever assembly 50 is placed as close as possible to the downstream periphery of the inverting flap 30.
  • the second lever arm 52 is fixed, for its part, by a first pivoted connection 3, at one end of a second connecting rod 62 connected, at the opposite end, by a second rotatable connection 4, at the downstream end of the inversion flap 30.
  • a rigid connection 53 makes the first lever arm 51 integral with the adjacent end of the second lever arm 52.
  • rotational guiding means 70 of the lever assembly 50 about its pivot axis X, in order to ensure its stability during its pivoting.
  • the end of the second lever arm 52 provided with a first shoe on the one hand, and the middle part of the first lever arm 51 at the rigid connection 54 with the second arm of lever 52 provided with a second shoe, on the other hand, are thus received in the guide rail 71.
  • Such a guiding device may also be placed at the junction between the first link 61 and the first lever arm 51 so as to prevent the first link rod 61 - first lever arm 51 from vibrating.
  • the sealing diaphragm 80 comprises upstream sealing means 81 (illustrated in FIG. 1 also) of the cover 20 with the front frame 1, sealing the vein, of the seal type. seal.
  • Figures 7 to 9 show the thrust reverser device 10 in said transit configuration in which the inversion flap 30 has different pivoting positions between its retracted position and its final position of closure of the vein.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Wind Motors (AREA)
  • Superstructure Of Vehicle (AREA)
  • Body Structure For Vehicles (AREA)
  • Transmission Devices (AREA)
EP10787831A 2009-11-05 2010-10-22 Dispositif d'inversion de poussee Withdrawn EP2496817A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0905294A FR2952128B1 (fr) 2009-11-05 2009-11-05 Dispositif d'inverseur de poussee
PCT/FR2010/052262 WO2011055056A1 (fr) 2009-11-05 2010-10-22 Dispositif d'inversion de poussee

Publications (1)

Publication Number Publication Date
EP2496817A1 true EP2496817A1 (fr) 2012-09-12

Family

ID=42245995

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10787831A Withdrawn EP2496817A1 (fr) 2009-11-05 2010-10-22 Dispositif d'inversion de poussee

Country Status (8)

Country Link
US (1) US9074554B2 (ru)
EP (1) EP2496817A1 (ru)
CN (1) CN102597475B (ru)
BR (1) BR112012008419A2 (ru)
CA (1) CA2776262A1 (ru)
FR (1) FR2952128B1 (ru)
RU (1) RU2538348C2 (ru)
WO (1) WO2011055056A1 (ru)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2982323B1 (fr) * 2011-11-07 2013-11-15 Aircelle Sa Dispositif d'inversion de poussee
FR2990474B1 (fr) 2012-05-10 2014-05-02 Aircelle Sa Inverseur de poussee a volet de blocage a deploiement controle
FR2994586B1 (fr) * 2012-08-20 2014-08-08 Aircelle Sa Ensemble de poussee a grilles pour turboreacteur d'aeronef
US9938929B2 (en) 2014-03-21 2018-04-10 Rohr, Inc. Thrust reverser for a turbofan engine
US9784214B2 (en) 2014-11-06 2017-10-10 Rohr, Inc. Thrust reverser with hidden linkage blocker doors
US9945324B2 (en) * 2014-11-06 2018-04-17 Rohr, Inc. Sleeve linkage for thrust reverser
US10309343B2 (en) 2014-11-06 2019-06-04 Rohr, Inc. Split sleeve hidden door thrust reverser
US10655564B2 (en) 2016-05-13 2020-05-19 Rohr, Inc. Thrust reverser system with hidden blocker doors
US9976696B2 (en) 2016-06-21 2018-05-22 Rohr, Inc. Linear actuator with multi-degree of freedom mounting structure
FR3054266B1 (fr) * 2016-07-25 2018-08-31 Safran Nacelles Systeme d’actionnement d’un panneau de nacelle de turboreacteur
US10343786B2 (en) 2017-06-28 2019-07-09 General Electric Company System and method of operating a ducted fan propulsion system during aircraft taxi
US10119495B1 (en) 2017-06-28 2018-11-06 General Electric Company System and method of operating a ducted fan propulsion system inflight
FR3068395B1 (fr) * 2017-06-30 2020-09-11 Safran Nacelles Nacelle pour turboreacteur comportant un inverseur de poussee a grilles
FR3086007B1 (fr) 2018-09-18 2020-09-04 Safran Nacelles Nacelle de turboreacteur avec un inverseur de poussee a grilles comprenant un secteur de commande des volets
FR3094412A1 (fr) * 2019-03-25 2020-10-02 Airbus Operations Turboreacteur double flux comportant une serie de lames rotatives pour obturer la veine du flux secondaire
FR3095013A1 (fr) * 2019-04-15 2020-10-16 Airbus Operations Turboreacteur double flux comportant une serie de lames rotatives pour obturer la veine du flux secondaire

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3262269A (en) * 1965-06-07 1966-07-26 Gen Electric Thrust reverser
US3614037A (en) * 1969-09-22 1971-10-19 Boeing Co Aircraft combination thrust reverser and sound suppressor and a particular full range balanced thrust reverser
FR2133520A1 (ru) * 1971-04-16 1972-12-01 Aviat Supply R Uni
GB1388406A (en) * 1971-12-15 1975-03-26 Rolls Royce Gas turbine ducted fan engines
GB1583952A (en) * 1976-07-13 1981-02-04 Short Brothers & Harland Ltd Gas turbine engines
US4216926A (en) * 1978-06-30 1980-08-12 Rohr Industries, Inc. Linkage system for a turbo fan engine thrust reverser
US4313581A (en) * 1979-09-12 1982-02-02 Rohr Industries, Inc. Reverser door mechanisms
DE3008193C2 (de) 1980-03-04 1982-07-08 Dynamit Nobel Ag, 5210 Troisdorf Kältestabile, Katalytisch wirksame Lösung von Diisopropoxy-bis(2,4-pentandionato)-titan(IV)
US4767055A (en) * 1987-03-27 1988-08-30 United Technologies Corporation Method and linkage for positioning a convergent flap and coaxial arc valve
US4807434A (en) * 1987-12-21 1989-02-28 The Boeing Company Thrust reverser for high bypass jet engines
US5309711A (en) * 1991-08-21 1994-05-10 Rohr, Inc. Cascade type thrust reverser for fan jet engines
US5778659A (en) * 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
FR2745036B1 (fr) * 1996-02-15 1998-04-03 Hispano Suiza Sa Inverseur de poussee de turboreacteur a portes associees a un panneau amont
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011055056A1 *

Also Published As

Publication number Publication date
US9074554B2 (en) 2015-07-07
FR2952128B1 (fr) 2011-11-04
US20120193448A1 (en) 2012-08-02
BR112012008419A2 (pt) 2016-03-29
RU2538348C2 (ru) 2015-01-10
CN102597475A (zh) 2012-07-18
RU2012122102A (ru) 2013-12-10
CN102597475B (zh) 2014-12-03
CA2776262A1 (fr) 2011-05-12
WO2011055056A1 (fr) 2011-05-12
FR2952128A1 (fr) 2011-05-06

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