UA84403C2 - Устройство для подачи охлаждающего воздуха к створке регулируемого реактивного сопла турбореактивного двигателя и турбореактивный двигатель - Google Patents

Устройство для подачи охлаждающего воздуха к створке регулируемого реактивного сопла турбореактивного двигателя и турбореактивный двигатель

Info

Publication number
UA84403C2
UA84403C2 UAA200500225A UAA200500225A UA84403C2 UA 84403 C2 UA84403 C2 UA 84403C2 UA A200500225 A UAA200500225 A UA A200500225A UA A200500225 A UAA200500225 A UA A200500225A UA 84403 C2 UA84403 C2 UA 84403C2
Authority
UA
Ukraine
Prior art keywords
turbo
jet engine
cooling air
exhaust nozzle
supplying cooling
Prior art date
Application number
UAA200500225A
Other languages
English (en)
Ukrainian (uk)
Inventor
Гі Ляперг
Рафаель Куртелєн
Дідьє Федер
Original Assignee
Снекма Мотьор
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 Снекма Мотьор filed Critical Снекма Мотьор
Publication of UA84403C2 publication Critical patent/UA84403C2/ru

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
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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)
  • Jet Pumps And Other Pumps (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Silencers (AREA)
  • Lift Valve (AREA)
  • Supercharger (AREA)

Abstract

Устройство, согласно изобретению, для подачи охлаждающего воздуха к створке (21) регулируемого реактивного сопла (1) в газовой турбине, которое содержит трубку (30), которая соединяет створку (21) с источником (31) охлаждающего воздуха. Трубка (30) содержит по крайней мере одну выдвижную часть (32) и одно шаровое соединение (33, 34).
UAA200500225A 2004-01-12 2005-01-10 Устройство для подачи охлаждающего воздуха к створке регулируемого реактивного сопла турбореактивного двигателя и турбореактивный двигатель UA84403C2 (ru)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0400219A FR2865000B1 (fr) 2004-01-12 2004-01-12 Dispositif d'alimentation en air de refroidissement de volets de tuyere

Publications (1)

Publication Number Publication Date
UA84403C2 true UA84403C2 (ru) 2008-10-27

Family

ID=34586485

Family Applications (1)

Application Number Title Priority Date Filing Date
UAA200500225A UA84403C2 (ru) 2004-01-12 2005-01-10 Устройство для подачи охлаждающего воздуха к створке регулируемого реактивного сопла турбореактивного двигателя и турбореактивный двигатель

Country Status (9)

Country Link
US (1) US7213393B2 (ru)
EP (1) EP1553282B1 (ru)
JP (1) JP4057014B2 (ru)
CA (1) CA2492149C (ru)
DE (1) DE602005002660T2 (ru)
ES (1) ES2293507T3 (ru)
FR (1) FR2865000B1 (ru)
RU (1) RU2386049C2 (ru)
UA (1) UA84403C2 (ru)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2860045B1 (fr) * 2003-09-24 2006-01-06 Snecma Moteurs Systeme de ventilation pour une tuyere d'ejection convergente divergente
US7458221B1 (en) * 2003-10-23 2008-12-02 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Variable area nozzle including a plurality of convexly vanes with a crowned contour, in a vane to vane sealing arrangement and with nonuniform lengths
US20080006641A1 (en) * 2005-02-22 2008-01-10 Pratt & Whitney Canada Corp. Positioning arrangement for components of a pressure vessel and method
FR2901321B1 (fr) * 2006-05-18 2011-08-12 Aircelle Sa Procede d'homogeneisation de l'air en sortie de turboreacteur pour abaisser le bruit genere
FR2920195B1 (fr) 2007-08-23 2009-11-20 Snecma Turbomachine a double flux a reduction de bruit de jet
US7861535B2 (en) * 2007-09-24 2011-01-04 United Technologies Corporation Self-aligning liner support hanger
FR2933128B1 (fr) * 2008-06-25 2010-09-17 Snecma Dispositif de prelevement d'air de refroidissement dans une turbomachine
FR2933127B1 (fr) * 2008-06-25 2015-04-24 Snecma Dispositif de prelevement d'air de refroidissement dans une turbomachine
FR2937679B1 (fr) * 2008-10-24 2010-12-03 Snecma Dispositif de prelevement d'air de refroidissement dans une turbomachine
US8991191B2 (en) * 2009-11-24 2015-03-31 General Electric Company Thermally actuated passive gas turbine engine compartment venting
RU2456468C1 (ru) * 2011-02-04 2012-07-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Система переброса рабочего тела для поворотного сопла турбореактивного двигателя
US9249732B2 (en) 2012-09-28 2016-02-02 United Technologies Corporation Panel support hanger for a turbine engine
US9243515B2 (en) 2012-09-28 2016-01-26 United Technologies Corporation Support hanger for flexibly connecting a plurality of panels
WO2014160449A2 (en) * 2013-03-13 2014-10-02 Rolls-Royce North American Technologies, Inc. Three stream, variable area fixed aperture nozzle with pneumatic actuation
EP3097301B1 (en) * 2014-01-24 2018-05-02 United Technologies Corporation Divergent flap
RU2578944C1 (ru) * 2014-12-11 2016-03-27 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО УМПО Регулируемое сверхзвуковое сопло турбореактивного двигателя
RU2678235C1 (ru) * 2017-12-22 2019-01-24 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Поворотное осесимметричное сопло турбореактивного двигателя
CN114151228B (zh) * 2022-02-09 2022-04-22 中国航发四川燃气涡轮研究院 二元矢量喷管调节片离散式冷气分区的方法
CN115614176B (zh) * 2022-08-29 2024-04-19 中国航发四川燃气涡轮研究院 基于内外涵结构一体化的红外与雷达综合隐身装置

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE337119C (de) * 1921-05-26 Friedrich Wilhelm Koehler Rohrkupplung mit halbkugelfoermigen Endflanschen
US5101624A (en) * 1989-09-07 1992-04-07 General Electric Company Exhaust nozzle hinge
US5720434A (en) * 1991-11-05 1998-02-24 General Electric Company Cooling apparatus for aircraft gas turbine engine exhaust nozzles
US5255849A (en) * 1991-11-05 1993-10-26 General Electric Company Cooling air transfer apparatus for aircraft gas turbine engine exhaust nozzles
US5603531A (en) * 1994-12-06 1997-02-18 United Technologies Corporation Blind assembly-swivel crossover tube
US5680755A (en) * 1995-09-25 1997-10-28 General Electric Company Convertible ejector selectively cooled thrust vectoring exhaust nozzle
US6301877B1 (en) * 1995-11-13 2001-10-16 United Technologies Corporation Ejector extension cooling for exhaust nozzle

Also Published As

Publication number Publication date
DE602005002660T2 (de) 2008-06-19
CA2492149A1 (fr) 2005-07-12
ES2293507T3 (es) 2008-03-16
JP4057014B2 (ja) 2008-03-05
JP2005201265A (ja) 2005-07-28
EP1553282B1 (fr) 2007-10-03
RU2005100177A (ru) 2006-06-20
DE602005002660D1 (de) 2007-11-15
US20050210864A1 (en) 2005-09-29
FR2865000A1 (fr) 2005-07-15
RU2386049C2 (ru) 2010-04-10
FR2865000B1 (fr) 2006-06-09
CA2492149C (fr) 2011-11-15
US7213393B2 (en) 2007-05-08
EP1553282A1 (fr) 2005-07-13

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