CA2460854A1 - Converging nozzle thrust reverser - Google Patents

Converging nozzle thrust reverser Download PDF

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Publication number
CA2460854A1
CA2460854A1 CA002460854A CA2460854A CA2460854A1 CA 2460854 A1 CA2460854 A1 CA 2460854A1 CA 002460854 A CA002460854 A CA 002460854A CA 2460854 A CA2460854 A CA 2460854A CA 2460854 A1 CA2460854 A1 CA 2460854A1
Authority
CA
Canada
Prior art keywords
aft
reverser
cowl
face
nozzle
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.)
Granted
Application number
CA002460854A
Other languages
French (fr)
Other versions
CA2460854C (en
Inventor
Thomas J. Jannetta
Frederick H. Peters
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.)
Nordam Group LLC
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of CA2460854A1 publication Critical patent/CA2460854A1/en
Application granted granted Critical
Publication of CA2460854C publication Critical patent/CA2460854C/en
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • 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

Abstract

A thrust reverser (32) includes axially adjoining forward and aft cowls (34,36) defining a fan nacelle for surrounding a fan ( 16) and core engine ( 14) with a fan duct (20) therebetween. The aft cowl (36) has a forward face (42) and the forward cowl (34) has an aft face (40) adjoining each other to define a reverser nozzle (44) which converges radially outwardly. The aft co wl (36) is translatable between a stowed position in which the reverser nozzle is closed and a deployed position in which the reverser nozzle is open for discharging fan air in a forward direction for thrust reversal.

Claims (5)

1. A thrust reverser for reversing fan air discharged from a fan through a fan duct defined between a core engine and a fan nacelle comprising:
a forward cowl of said nacelle having an aft face;
an aft cowl of said nacelle having a forward face adjoining said aft face to define a reverser nozzle converging radially outwardly; and means for axially translating said aft cowl relative to said forward cowl to open .and close said reverser nozzle.
2. A reverser according to claim 1 wherein said aft face is axially convex and said forward face is axially concave with different converging profiles thereof.
3. A reverser according to claim 2 wherein:
radially inner surfaces of said forward and aft faces define therebetween an inlet of said reverser nozzle;
radially outer surfaces of said forward and aft faces define therebetween an outlet of said reverser nozzle; and said inlet is axially larger than said outlet.
4. A reverser according to claim 3 wherein said forward and aft faces at said reverser outlet have substantially equal discharge angles, and said forward and aft faces at said reverser inlet have different incidence angles.
5. A reverser according to claim 4 wherein said aft face is a substantially axially circular arc, and said forward face is a substantially axially circular arc, with radially spaced apart centers of curvature.

deploying said doors as said aft cowl is deployed aft.

13. A turbofan engine thrust reverser comprising:
a core turbine engine joined to a fan;
an annular forward cowl fixedly joined to said core engine and surrounding said fan;
an aft cowl surrounding said core engine and cooperating with said forward cowl to define a fan duct for channeling fan air around said core engine;
said forward cowl having an aft face adjoining a forward face of said aft cowl to define a reverser nozzle converging in flow area radially outwardly from said fan duct;
a plurality of actuators mounted inside said forward cowl for axially translating said aft cowl in axial throw from a stowed position abutting said forward cowl to close said reverser nozzle, to a deployed position extending aft said aft nozzle to open said reverser nozzle; and a plurality of circumferentially adjoining deflector doors pivotally joined between said aft cowl and said core engine for blocking said fan duct aft of said reverser nozzle when said aft cowl is deployed, and unblocking said fan duct when said aft nozzle is stowed.

14. A reverser according to claim 13 wherein:
radially inner surfaces of said forward and aft faces define therebetween an inlet of said reverser nozzle;
radially outer surfaces of said forward and aft faces define therebetween an outlet of said reverser nozzle; and said inlet is axially larger than said outlet.

15. A reverser according to claim 14 wherein said forward and aft faces at said reverser outlet have substantially equal discharge angles, and said forward and aft faces at said reverser inlet have different incidence angles.

16. A reverser according to claim 15 wherein said aft face is axially convex and said forward face is axially concave with different converging profiles thereof.

17. A reverser according to claim 16 wherein said aft face is a substantially axially circular arc, and said forward face is a substantially axially circular arc, with radially spaced apart centers of curvature.

18. A reverser according to claim 17 wherein said center of curvature of said forward face is radially inwardly of said center of curvature of said aft face.

19. A reverser according to claim 18 wherein said reverser nozzle is cascadeless, and said aft cowl throw is generally equal to the radial spa ~
of said fan duct at said reverser inlet.

20. A reverser according ,to claim 19 further comprising a plurality of drag links pivotally joined at outer ends to respective ones of said doors, and having inner ends for being pivotally joined to said core engine for deploying said doors as said aft cowl is deployed aft.
CA2460854A 2001-09-27 2002-09-13 Converging nozzle thrust reverser Expired - Fee Related CA2460854C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US09/965,194 US6568172B2 (en) 2001-09-27 2001-09-27 Converging nozzle thrust reverser
US09/965,194 2001-09-27
PCT/US2002/029109 WO2003027475A1 (en) 2001-09-27 2002-09-13 Converging nozzle thrust reverser

Publications (2)

Publication Number Publication Date
CA2460854A1 true CA2460854A1 (en) 2003-04-03
CA2460854C CA2460854C (en) 2010-04-06

Family

ID=25509611

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2460854A Expired - Fee Related CA2460854C (en) 2001-09-27 2002-09-13 Converging nozzle thrust reverser

Country Status (5)

Country Link
US (1) US6568172B2 (en)
EP (1) EP1430212B1 (en)
BR (1) BR0212845B1 (en)
CA (1) CA2460854C (en)
WO (1) WO2003027475A1 (en)

Families Citing this family (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040149861A1 (en) * 2001-06-06 2004-08-05 Strobl William Charles S & H Cycle Engine
EP1558840A4 (en) * 2002-10-11 2006-03-22 Nordam Group Inc Bifold door thrust reverser
US6968675B2 (en) * 2002-10-29 2005-11-29 Rohr, Inc. Cascadeless fan thrust reverser with plume control
US6845946B2 (en) * 2003-02-21 2005-01-25 The Nordam Group, Inc. Self stowing thrust reverser
US6976352B2 (en) * 2003-03-22 2005-12-20 The Nordam Group, Inc. Toggle interlocked thrust reverser
US7055329B2 (en) * 2003-03-31 2006-06-06 General Electric Company Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air
US7127880B2 (en) * 2003-08-29 2006-10-31 The Nordam Group, Inc. Induction coupled variable nozzle
US7146796B2 (en) * 2003-09-05 2006-12-12 The Nordam Group, Inc. Nested latch thrust reverser
GB0321139D0 (en) * 2003-09-10 2003-10-08 Short Brothers Plc A device
US7264203B2 (en) * 2003-10-02 2007-09-04 The Nordam Group, Inc. Spider actuated thrust reverser
US20110101158A1 (en) * 2005-03-29 2011-05-05 The Boeing Company Thrust Reversers Including Monolithic Components
US7571527B2 (en) * 2005-03-29 2009-08-11 The Boeing Company Mandrel for fabrication of a monolithic composite nacelle panel
US7690190B2 (en) 2005-05-11 2010-04-06 The Boeing Company Aircraft systems including cascade thrust reversers
US7559507B2 (en) * 2005-06-27 2009-07-14 The Boeing Company Thrust reversers including locking assemblies for inhibiting deflection
US7484356B1 (en) * 2005-07-26 2009-02-03 Aeronautical Concepts Of Exhaust, Llc Cascade reverser without blocker doors
US7600371B2 (en) 2005-10-18 2009-10-13 The Boeing Company Thrust reversers including support members for inhibiting deflection
FR2900980B1 (en) * 2006-05-10 2011-08-19 Aircelle Sa NACELLE FOR DOUBLE FLOW TURBOREACTOR WITH HIGH DILUTION RATE
GB0611963D0 (en) * 2006-06-16 2006-07-26 Rolls Royce Plc A flow reverser
US8015797B2 (en) * 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
FR2907170B1 (en) * 2006-10-11 2008-12-12 Aircelle Sa THRUST INVERTER WITH GRIDS FOR REACTION ENGINE
FR2916426B1 (en) * 2007-05-22 2010-04-02 Aircelle Sa NACELLE REAR ASSEMBLY FOR TURBOJET ENGINE.
US7926285B2 (en) * 2007-07-18 2011-04-19 General Electric Company Modular chevron exhaust nozzle
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8051639B2 (en) * 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8052085B2 (en) * 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US7735778B2 (en) 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
FR2929998B1 (en) * 2008-04-14 2011-08-12 Aircelle Sa DOUBLE FLOW TURBOREACTOR NACELLE
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8109466B2 (en) * 2008-06-23 2012-02-07 Rohr, Inc. Thrust reverser cascade assembly and AFT cascade ring with flow deflector portion
US8109467B2 (en) * 2009-04-24 2012-02-07 United Technologies Corporation Thrust reverser assembly with shaped drag links
DE102009033755A1 (en) * 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Turbofan
US8689538B2 (en) * 2009-09-09 2014-04-08 The Boeing Company Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan
US8869507B2 (en) * 2010-01-13 2014-10-28 United Technologies Corporation Translatable cascade thrust reverser
US9038367B2 (en) 2011-09-16 2015-05-26 United Technologies Corporation Fan case thrust reverser
US9086034B2 (en) 2011-10-13 2015-07-21 Rohr, Inc. Thrust reverser cascade assembly with flow deflection shelf
US9822734B2 (en) 2013-02-22 2017-11-21 United Technologies Corporation Tandem thrust reverser with multi-bar linkage
US9617009B2 (en) 2013-02-22 2017-04-11 United Technologies Corporation ATR full ring sliding nacelle
EP3039275B1 (en) 2013-08-28 2020-03-04 United Technologies Corporation Thrust reverser sliding door assembly
US10344711B2 (en) * 2016-01-11 2019-07-09 Rolls-Royce Corporation System and method of alleviating blade flutter
US10823112B2 (en) * 2017-05-25 2020-11-03 The Boeing Company Method for manufacturing and assembly of a thrust reverser cascade
US10465539B2 (en) * 2017-08-04 2019-11-05 Pratt & Whitney Canada Corp. Rotor casing
US11905913B2 (en) * 2021-10-22 2024-02-20 Spirit Aerosystems, Inc. Thrust reverser interspatial blocker system

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1544066A (en) * 1966-09-12 1968-10-31 Rolls Royce Pipes for circulation of a thrust reversal fluid
US3717304A (en) * 1970-05-06 1973-02-20 Rolls Royce Thrust reverser for fluid flow engine
GB1545089A (en) 1976-09-11 1979-05-02 Rolls Royce Jet engine thrust reverser and cowl structure
US4232516A (en) 1977-10-05 1980-11-11 Rolls-Royce Limited Flow deflecting devices
US4502638A (en) * 1982-04-26 1985-03-05 Rolls-Royce Inc. Turbomachine ejector nozzle and thrust reverser
GB2212859B (en) * 1987-12-02 1991-03-06 Rolls Royce Plc Ducted fan gas turbine engine with surge controller
DE3844188C1 (en) 1988-12-29 1990-05-17 Mtu Muenchen Gmbh
US5228641A (en) 1991-08-15 1993-07-20 Rohr, Inc. Cascade type aircraft engine thrust reverser with hidden link actuator
US5904320A (en) * 1994-07-14 1999-05-18 Northrop Gunman Corporation Blockerless thrust reverser
US5655360A (en) 1995-05-31 1997-08-12 General Electric Company Thrust reverser with variable nozzle
GB9613166D0 (en) * 1996-06-24 1996-08-28 Short Brothers Plc Aircraft propulsive power unit
US5806302A (en) 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
US5794434A (en) 1996-10-09 1998-08-18 The Boeing Company Aircraft thrust reverser system with linearly translating inner and outer doors

Also Published As

Publication number Publication date
BR0212845B1 (en) 2011-12-13
WO2003027475A1 (en) 2003-04-03
US20030056493A1 (en) 2003-03-27
EP1430212B1 (en) 2013-09-11
BR0212845A (en) 2004-10-13
EP1430212A1 (en) 2004-06-23
EP1430212A4 (en) 2005-06-01
CA2460854C (en) 2010-04-06
US6568172B2 (en) 2003-05-27

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Effective date: 20200914