JPH10103153A - 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル - Google Patents

航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル

Info

Publication number
JPH10103153A
JPH10103153A JP9276680A JP27668097A JPH10103153A JP H10103153 A JPH10103153 A JP H10103153A JP 9276680 A JP9276680 A JP 9276680A JP 27668097 A JP27668097 A JP 27668097A JP H10103153 A JPH10103153 A JP H10103153A
Authority
JP
Japan
Prior art keywords
tapered
divergent
flap
exhaust nozzle
gas turbine
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.)
Ceased
Application number
JP9276680A
Other languages
English (en)
Japanese (ja)
Other versions
JPH10103153A5 (enExample
Inventor
Alfredo Cires
アルフレド・サイレス
Jennifer Groceman
ジェニファー・グロースマン
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.)
RTX 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
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of JPH10103153A publication Critical patent/JPH10103153A/ja
Publication of JPH10103153A5 publication Critical patent/JPH10103153A5/ja
Ceased 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
    • F02K1/1223—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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • 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
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/004—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector by using one or more swivable nozzles rotating about their own axis
    • 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
    • F02K1/15—Control or regulation
    • 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
    • F05D2260/15—Load balancing
    • 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)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
JP9276680A 1996-09-27 1997-09-25 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル Ceased JPH10103153A (ja)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/721,890 US5813611A (en) 1996-09-27 1996-09-27 Compact pressure balanced fulcrum-link nozzle
US08/721,890 1996-09-27

Publications (2)

Publication Number Publication Date
JPH10103153A true JPH10103153A (ja) 1998-04-21
JPH10103153A5 JPH10103153A5 (enExample) 2005-06-16

Family

ID=24899736

Family Applications (1)

Application Number Title Priority Date Filing Date
JP9276680A Ceased JPH10103153A (ja) 1996-09-27 1997-09-25 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル

Country Status (5)

Country Link
US (1) US5813611A (enExample)
EP (1) EP0833046B1 (enExample)
JP (1) JPH10103153A (enExample)
KR (1) KR100453669B1 (enExample)
DE (1) DE69720358T2 (enExample)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008111434A (ja) * 2006-10-27 2008-05-15 United Technol Corp <Utc> ガスタービンエンジン用ノズルおよびガスタービンエンジンのノズルを作動させる方法
JP2015500939A (ja) * 2011-12-07 2015-01-08 スネクマ タービンエンジン用コンバージェントダイバージェントノズル

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6622472B2 (en) * 2001-10-17 2003-09-23 Gateway Space Transport, Inc. Apparatus and method for thrust vector control
FR2857414B1 (fr) * 2003-07-08 2007-06-08 Snecma Moteurs Volet souple de tuyere a section variable de turbomachine
US7032835B2 (en) * 2004-01-28 2006-04-25 United Technologies Corporation Convergent/divergent nozzle with modulated cooling
US7624567B2 (en) 2005-09-20 2009-12-01 United Technologies Corporation Convergent divergent nozzle with interlocking divergent flaps
US8205454B2 (en) * 2007-02-06 2012-06-26 United Technologies Corporation Convergent divergent nozzle with edge cooled divergent seals
US7757477B2 (en) * 2007-02-20 2010-07-20 United Technologies Corporation Convergent divergent nozzle with slot cooled nozzle liner
US9719370B2 (en) * 2007-03-30 2017-08-01 United Technologies Corporation Linkage system with wear reduction
US7874160B2 (en) * 2007-08-21 2011-01-25 United Technologies Corporation Nozzle-area ratio float bias
US8020386B2 (en) * 2007-08-21 2011-09-20 United Technologies Corporation Rollertrack pivoting axi-nozzle
US9689346B2 (en) 2013-04-12 2017-06-27 United Technologies Corporation Gas turbine engine convergent/divergent exhaust nozzle divergent seal with dovetail interface
CN104033276B (zh) * 2014-06-09 2016-05-04 中国航空工业集团公司沈阳发动机设计研究所 一种二元喷管的喉道面积控制机构
CN104033275B (zh) * 2014-06-09 2016-02-17 中国航空工业集团公司沈阳发动机设计研究所 一种二元喷管收敛段控制机构
FR3026774B1 (fr) * 2014-10-07 2020-07-17 Safran Aircraft Engines Turbomachine comportant un dispositif de freinage du rotor de soufflante.
US9856956B2 (en) * 2015-01-20 2018-01-02 United Technologies Corporation Rod-and-bracket connector system for securing a pivoting member to a guide anchor moveably secured within a guide track
US9951717B2 (en) 2015-04-15 2018-04-24 Hamilton Sundstrand Corporation Asymmetric load compensation system
FR3062425B1 (fr) * 2017-01-30 2021-01-08 Safran Aircraft Engines Circuit d'alimentation en carburant de turbomachine
FR3062422B1 (fr) * 2017-01-30 2021-05-21 Safran Aircraft Engines Systeme d'alimentation en carburant d'une turbomachine
CN111828196B (zh) * 2020-07-04 2022-11-01 峰特(浙江)新材料有限公司 一种航空发动机尾喷管
CN112431694B (zh) * 2020-11-20 2021-11-05 哈尔滨工程大学 一种使用柔性材料和外置桁架结构的可展开喷管
CN114109645B (zh) * 2021-11-12 2023-12-19 中国航发沈阳发动机研究所 一种轴对称收扩喷管运动机构
CN113864078B (zh) * 2021-12-03 2022-02-22 中国航发沈阳发动机研究所 一种高隐身二元矢量喷管
US20240140611A1 (en) * 2022-10-31 2024-05-02 The Boeing Company Exhaust systems having adjustable nozzles and related methods

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB858579A (en) * 1957-01-17 1961-01-11 Havilland Engine Co Ltd Adjustable propulsion nozzles
US3792815A (en) * 1972-11-24 1974-02-19 United Aircraft Corp Balanced flap converging/diverging nozzle
FR2227433B1 (enExample) * 1973-04-27 1975-08-22 Snecma
GB1444391A (en) * 1973-05-02 1976-07-28 Rolls Royce Exhaust nozzle structures
FR2244917B2 (enExample) * 1973-09-21 1978-01-13 Snecma
US4000854A (en) * 1975-10-02 1977-01-04 General Electric Company Thrust vectorable exhaust nozzle
US4049198A (en) * 1976-06-17 1977-09-20 The United States Of America As Represented By The Secretary Of The Air Force Duct pressure actuated nozzle
GB2254377B (en) * 1981-02-28 1993-03-31 Rolls Royce Pressure balanced variable area nozzle
US4447009A (en) * 1981-12-28 1984-05-08 United Technologies Corporation Three-dimensional axially translatable convergent/divergent nozzle assembly
US4440347A (en) * 1981-12-28 1984-04-03 United Technologies Corporation Simplified means for balancing the loads on a variable area nozzle
US4440346A (en) * 1981-12-28 1984-04-03 United Technologies Corporation Axially translatable variable area convergent/divergent nozzle
US4420932A (en) * 1982-03-02 1983-12-20 The United States Of America As Represented By The Secretary Of The Air Force Pressure control system for convergent-divergent exhaust nozzle
US4456178A (en) * 1982-12-27 1984-06-26 United Technologies Corporation Exhaust nozzle assembly with dual unison ring structure
US5011080A (en) * 1990-04-18 1991-04-30 United Technologies Corporation Convergent/divergent nozzle construction
US5215256A (en) * 1992-07-16 1993-06-01 Barcza W Kevin Flap hinge arrangement for a convergent/divergent nozzle

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2008111434A (ja) * 2006-10-27 2008-05-15 United Technol Corp <Utc> ガスタービンエンジン用ノズルおよびガスタービンエンジンのノズルを作動させる方法
US7854124B2 (en) 2006-10-27 2010-12-21 United Technologies Corporation Combined control for supplying cooling air and support air in a turbine engine nozzle
JP2015500939A (ja) * 2011-12-07 2015-01-08 スネクマ タービンエンジン用コンバージェントダイバージェントノズル

Also Published As

Publication number Publication date
KR19980025050A (ko) 1998-07-06
EP0833046A3 (en) 1999-10-20
US5813611A (en) 1998-09-29
EP0833046B1 (en) 2003-04-02
DE69720358D1 (de) 2003-05-08
EP0833046A2 (en) 1998-04-01
KR100453669B1 (ko) 2004-12-17
DE69720358T2 (de) 2003-10-30

Similar Documents

Publication Publication Date Title
JPH10103153A (ja) 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル
US12241377B2 (en) Turbomachine module equipped with a blade pitch-changing system of a stator vane
US5797544A (en) C/D nozzle with synchronizing ring link suspension
US11731773B2 (en) Engine mount system for a gas turbine engine
US6543718B2 (en) Engine arrangement
US7677047B2 (en) Inverted stiffened shell panel torque transmission for loaded struts and mid-turbine frames
JP3968672B2 (ja) 航空機に動力を供給するガスタービンエンジン動力装置用の先細／末広排気ノズル
US5443229A (en) Aircraft gas turbine engine sideways mount
RU2687861C9 (ru) Газотурбинный двигатель
US8448895B2 (en) Gas turbine engine compressor arrangement
US4704862A (en) Ducted prop engine
US6708482B2 (en) Aircraft engine with inter-turbine engine frame
US8800914B2 (en) Gas turbine engine with low stage count low pressure turbine
US20160047268A1 (en) Gas turbine engine with low stage count low pressure turbine
CN116209821B (zh) 设置有螺旋桨和偏置定子轮叶的涡轮机模块
US5103635A (en) Contra-rotating fan engine
JPH02267325A (ja) パワータービン支持構造
JP2001505636A (ja) 多数のパワー制御回路を有する軸対称形転向ノズル作動装置
JP2006189032A (ja) タービンエンジンノズルおよびそのサブアッセンブリ、ならびに後付けまたは再構成の方法
US11118509B2 (en) Turbojet of the unducted rotor type

Legal Events

Date Code Title Description
A521 Written amendment

Free format text: JAPANESE INTERMEDIATE CODE: A523

Effective date: 20040924

A621 Written request for application examination

Free format text: JAPANESE INTERMEDIATE CODE: A621

Effective date: 20040924

A131 Notification of reasons for refusal

Free format text: JAPANESE INTERMEDIATE CODE: A131

Effective date: 20070424

A601 Written request for extension of time

Free format text: JAPANESE INTERMEDIATE CODE: A601

Effective date: 20070723

A602 Written permission of extension of time

Free format text: JAPANESE INTERMEDIATE CODE: A602

Effective date: 20070726

A01 Written decision to grant a patent or to grant a registration (utility model)

Free format text: JAPANESE INTERMEDIATE CODE: A01

Effective date: 20071204

A045 Written measure of dismissal of application [lapsed due to lack of payment]

Free format text: JAPANESE INTERMEDIATE CODE: A045

Effective date: 20080422