GB2429242B - Method for retrofitting a turbine engine - Google Patents

Method for retrofitting a turbine engine

Info

Publication number
GB2429242B
GB2429242B GB0621237A GB0621237A GB2429242B GB 2429242 B GB2429242 B GB 2429242B GB 0621237 A GB0621237 A GB 0621237A GB 0621237 A GB0621237 A GB 0621237A GB 2429242 B GB2429242 B GB 2429242B
Authority
GB
United Kingdom
Prior art keywords
retrofitting
turbine engine
turbine
engine
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 - Fee Related
Application number
GB0621237A
Other versions
GB0621237D0 (en
GB2429242A (en
Inventor
Dale W Petty
Alex J O Simpson
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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
Priority claimed from US10/625,997 external-priority patent/US7225622B2/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to GB0621237A priority Critical patent/GB2429242B/en
Publication of GB0621237D0 publication Critical patent/GB0621237D0/en
Publication of GB2429242A publication Critical patent/GB2429242A/en
Application granted granted Critical
Publication of GB2429242B publication Critical patent/GB2429242B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F02K1/1223—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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1269—Varying effective area of jet pipe or nozzle by means of pivoted flaps of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the internal downstream series having its flaps hinged at their downstream ends on the downstream ends of the flaps of the external downstream series hinged on a fixed structure at their upstream ends
    • 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
    • F02K1/1292—Varying effective area of jet pipe or nozzle by means of pivoted flaps of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure, the internal downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series and at their downstream ends on the downstream ends of the flaps of the external downstream series hinged at their upstream ends on a substantially axially movable structure
GB0621237A 2003-07-21 2004-07-12 Method for retrofitting a turbine engine Expired - Fee Related GB2429242B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0621237A GB2429242B (en) 2003-07-21 2004-07-12 Method for retrofitting a turbine engine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US10/625,997 US7225622B2 (en) 2003-07-21 2003-07-21 Turbine engine nozzle
GB0621237A GB2429242B (en) 2003-07-21 2004-07-12 Method for retrofitting a turbine engine
GB0415554A GB2404222B (en) 2003-07-21 2004-07-12 Turbine engine nozzle

Publications (3)

Publication Number Publication Date
GB0621237D0 GB0621237D0 (en) 2006-12-06
GB2429242A GB2429242A (en) 2007-02-21
GB2429242B true GB2429242B (en) 2008-01-09

Family

ID=38820344

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0621237A Expired - Fee Related GB2429242B (en) 2003-07-21 2004-07-12 Method for retrofitting a turbine engine

Country Status (1)

Country Link
GB (1) GB2429242B (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2484278C1 (en) * 2012-01-31 2013-06-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Adjustable supersonic nozzle of jet turbine engine
US9845768B2 (en) 2013-03-13 2017-12-19 Rolls-Royce North American Technologies, Inc. Three stream, variable area, vectorable nozzle
GB201621331D0 (en) 2016-12-15 2017-02-01 Rolls Royce Plc A Nozzle
US10634092B2 (en) * 2017-09-08 2020-04-28 United Technologies Corporation Linkage assembly preventing axial rotation of the link rod
US11649785B1 (en) * 2021-11-22 2023-05-16 Rohr, Inc. Mixed flow exhaust thrust reverser with area control nozzle systems and methods

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2880575A (en) * 1952-11-28 1959-04-07 Curtiss Wright Corp Combined variable area nozzle and aerodynamic brake
US4176792A (en) * 1977-07-11 1979-12-04 General Electric Company Variable area exhaust nozzle
EP0286572A2 (en) * 1987-04-09 1988-10-12 United Technologies Corporation Thrust vectoring exhaust nozzle arrangement
US5050803A (en) * 1989-10-12 1991-09-24 General Electric Company Actuation system for positioning a vectoring exhaust nozzle
US5154052A (en) * 1990-05-07 1992-10-13 General Electric Company Exhaust assembly for a high speed civil transport aircraft engine
US5520336A (en) * 1980-01-14 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.A.) Nozzle for a jet engine containing an adjustable convergent-divergent portion
US5775589A (en) * 1991-11-05 1998-07-07 General Electric Company Cooling apparatus for aircraft gas turbine engine exhaust nozzles
US5797544A (en) * 1996-09-27 1998-08-25 United Technologies Corporation C/D nozzle with synchronizing ring link suspension
US5820024A (en) * 1994-05-16 1998-10-13 General Electric Company Hollow nozzle actuating ring
US5842643A (en) * 1996-12-03 1998-12-01 General Electric Company Articulated exhaust nozzle fairing
US20020036241A1 (en) * 1999-12-29 2002-03-28 Johnson James Steven Throat configuration for axisymmetric nozzle
US6378294B1 (en) * 1999-01-29 2002-04-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation - S.N.E.C.M.A. System for activating an adjustable tube by means of an elastic ring for a thrust nozzle

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2880575A (en) * 1952-11-28 1959-04-07 Curtiss Wright Corp Combined variable area nozzle and aerodynamic brake
US4176792A (en) * 1977-07-11 1979-12-04 General Electric Company Variable area exhaust nozzle
US5520336A (en) * 1980-01-14 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.A.) Nozzle for a jet engine containing an adjustable convergent-divergent portion
EP0286572A2 (en) * 1987-04-09 1988-10-12 United Technologies Corporation Thrust vectoring exhaust nozzle arrangement
US5050803A (en) * 1989-10-12 1991-09-24 General Electric Company Actuation system for positioning a vectoring exhaust nozzle
US5154052A (en) * 1990-05-07 1992-10-13 General Electric Company Exhaust assembly for a high speed civil transport aircraft engine
US5775589A (en) * 1991-11-05 1998-07-07 General Electric Company Cooling apparatus for aircraft gas turbine engine exhaust nozzles
US5820024A (en) * 1994-05-16 1998-10-13 General Electric Company Hollow nozzle actuating ring
US5797544A (en) * 1996-09-27 1998-08-25 United Technologies Corporation C/D nozzle with synchronizing ring link suspension
US5842643A (en) * 1996-12-03 1998-12-01 General Electric Company Articulated exhaust nozzle fairing
US6378294B1 (en) * 1999-01-29 2002-04-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation - S.N.E.C.M.A. System for activating an adjustable tube by means of an elastic ring for a thrust nozzle
US20020036241A1 (en) * 1999-12-29 2002-03-28 Johnson James Steven Throat configuration for axisymmetric nozzle

Also Published As

Publication number Publication date
GB0621237D0 (en) 2006-12-06
GB2429242A (en) 2007-02-21

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 20210712