BRPI0401807A - Turbomáquina de aviação - Google Patents

Turbomáquina de aviação

Info

Publication number
BRPI0401807A
BRPI0401807A BR0401807-9A BRPI0401807A BRPI0401807A BR PI0401807 A BRPI0401807 A BR PI0401807A BR PI0401807 A BRPI0401807 A BR PI0401807A BR PI0401807 A BRPI0401807 A BR PI0401807A
Authority
BR
Brazil
Prior art keywords
casing
downstream
upstream
diaphragm
annular
Prior art date
Application number
BR0401807-9A
Other languages
English (en)
Inventor
Guy Lapergue
Guillaume Sevi
Jacques Roche
Original Assignee
Snecma Moteurs
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 Snecma Moteurs filed Critical Snecma Moteurs
Publication of BRPI0401807A publication Critical patent/BRPI0401807A/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • 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
    • F02K1/80—Couplings or connections
    • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
    • 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
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/02—Sealings between relatively-stationary surfaces
    • F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
    • F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
    • F16J15/0887—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing the sealing effect being obtained by elastic deformation of the packing
    • 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
    • F05D2260/10—Particular cycles
    • 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)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

"TURBOMáQUINA DE AVIAçãO". A invenção se refere a uma turbomáquina de aviação que compreende a jusante da turbina uma câmara de pós-combustão (2) prolongada por pelo menos uma tubeira (7), a dita câmara sendo delimitada radialmente por uma camisa de proteção térmica (3) disposta no interior de um cárter (4), o dito cárter e a dita camisa definido um canal anular (5) no qual circula em funcionamento um fluxo secundário, um diafragma anular (6) solidário do dito cárter (4) sendo disposto na extremidade a jusante do dito canal (5), a dita tubeira (7) compreendendo uma pluralidade de postigos (8) articulados na extremidade a montante do dito cárter (4), cada postigo sendo equipado em sua face interior com uma placa de proteção térmica (10) que delimita com o dito postigo uma passagem (11) destinada a ser alimentada por um ar de resfriamento fornecido pelo dito diafragma (6), caracterizada pelo fato de que a alimentação com ar de resfriamento das ditas passagens (11) é assegurada por um conduto anular delimitado exteriormente por uma primeira junta anular (30) flexível retida, em funcionamento, em apoio deslizante sobre a face interna a jusante do cárter (4) e sobre a face interna a montante dos postigos (8) sob a ação da pressão do fluxo secundário, e delimitado interiormente por uma segunda junta anular flexível (40) da qual a extremidade a montante (40a) é fixada na zona radialmente interior do diafragma (6) e da qual a extremidade a jusante (30c) está em apoio deslizante sobre a face interna a montante das placas de proteção (10).
BR0401807-9A 2003-05-27 2004-05-24 Turbomáquina de aviação BRPI0401807A (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0306390A FR2855559B1 (fr) 2003-05-27 2003-05-27 Systeme d'etancheite du flux secondaire a l'entree d'une tuyere d'une turbomachine avec chambre de post-combustion

Publications (1)

Publication Number Publication Date
BRPI0401807A true BRPI0401807A (pt) 2005-01-18

Family

ID=32982397

Family Applications (1)

Application Number Title Priority Date Filing Date
BR0401807-9A BRPI0401807A (pt) 2003-05-27 2004-05-24 Turbomáquina de aviação

Country Status (18)

Country Link
US (1) US6966189B2 (pt)
EP (1) EP1482127B1 (pt)
JP (1) JP4146389B2 (pt)
KR (1) KR20040102334A (pt)
CN (1) CN100346066C (pt)
AT (1) ATE333570T1 (pt)
AU (1) AU2004202177A1 (pt)
BR (1) BRPI0401807A (pt)
CA (1) CA2469853A1 (pt)
DE (1) DE602004001546T2 (pt)
ES (1) ES2270305T3 (pt)
FR (1) FR2855559B1 (pt)
IL (1) IL162142A (pt)
NZ (1) NZ533014A (pt)
PL (1) PL1482127T3 (pt)
RU (1) RU2342551C2 (pt)
UA (1) UA81234C2 (pt)
ZA (1) ZA200403929B (pt)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6799739B1 (en) 2003-11-24 2004-10-05 The Boeing Company Aircraft control surface drive system and associated methods
US7611099B2 (en) * 2005-09-07 2009-11-03 The Boeing Company Seal assemblies for use with drooped spoilers and other control surfaces on aircraft
US7624567B2 (en) * 2005-09-20 2009-12-01 United Technologies Corporation Convergent divergent nozzle with interlocking divergent flaps
FR2903151B1 (fr) * 2006-06-29 2011-10-28 Snecma Dispositif de ventilation d'un carter d'echappement dans une turbomachine
US8069648B2 (en) * 2008-07-03 2011-12-06 United Technologies Corporation Impingement cooling for turbofan exhaust assembly
GB0908370D0 (en) * 2009-05-15 2009-06-24 Airbus Uk Ltd A hinge sealing element and an assembly including said element
US9932845B2 (en) * 2011-06-30 2018-04-03 United Technologies Corporation Impingement cooled nozzle liner
US9341120B2 (en) * 2012-02-10 2016-05-17 United Technologies Corporation Channeled spring seal for sealing an air gap between moving plates
RU2516751C1 (ru) * 2013-04-11 2014-05-20 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Поворотное осесимметричное сопло турбореактивного двигателя
FR3009029B1 (fr) * 2013-07-26 2018-03-23 Astrium Sas Tuyere d'ejection de gaz de combustion d'un moteur fusee pourvue d'un dispositif d'etancheite entre une partie fixe et une partie mobile de la tuyere
FR3047768B1 (fr) * 2016-02-17 2019-02-01 Safran Power Units Dispositif de liaison et d'etancheite entre deux modules d'un conduit d'echappement d'une turbomachine
RU2656172C1 (ru) * 2017-04-20 2018-05-31 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Устройство для сочленения наружной поверхности поворотного реактивного сопла двигателя и мотогондолы самолёта
RU2647018C1 (ru) * 2017-04-26 2018-03-13 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Устройство для сочленения наружной поверхности поворотного реактивного сопла турбореактивного двигателя и мотогондолы самолета
US10513939B2 (en) * 2017-09-13 2019-12-24 United Technologies Corporation Seal interface with a deflection control feature
FR3072908B1 (fr) * 2017-10-26 2021-02-26 Safran Nacelles Ensemble propulsif pour aeronef
RU2729591C1 (ru) * 2019-08-01 2020-08-11 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Поворотное осесимметричное сопло турбореактивного двигателя
FR3136516B1 (fr) * 2022-06-14 2024-08-02 Safran Nacelles Ensemble pour turbomachine
CN115143847B (zh) * 2022-07-28 2024-07-19 西安现代控制技术研究所 一种远程弹箭弹尾防热密封复合结构

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3972475A (en) * 1975-07-31 1976-08-03 United Technologies Corporation Nozzle construction providing for thermal growth
US4043509A (en) * 1976-05-13 1977-08-23 General Electric Company Actuation system for a gas turbine engine exhaust device
US4645217A (en) * 1985-11-29 1987-02-24 United Technologies Corporation Finger seal assembly
US5101624A (en) * 1989-09-07 1992-04-07 General Electric Company Exhaust nozzle hinge
FR2670177B1 (fr) * 1990-12-05 1993-01-22 Snecma Joint d'etancheite entre l'arriere du fuselage d'un avion et les volets exterieurs de son turboreacteur.
US5150839A (en) * 1991-03-14 1992-09-29 General Electric Company Nozzle load management
US5143292A (en) * 1991-05-09 1992-09-01 General Electric Company Cooled leaf seal
DE4408260A1 (de) * 1994-03-11 1995-09-21 Mtu Muenchen Gmbh Dichtung
US5522546A (en) * 1994-08-19 1996-06-04 General Electric Company Variable exhaust nozzle seal
US5560198A (en) * 1995-05-25 1996-10-01 United Technologies Corporation Cooled gas turbine engine augmentor fingerseal assembly
US5897120A (en) * 1997-04-15 1999-04-27 General Electric Company Outer flap elastic seal assembly
JP3600912B2 (ja) * 2001-09-12 2004-12-15 川崎重工業株式会社 燃焼器ライナのシール構造
CA2460598C (en) * 2001-10-23 2012-12-18 The Nordam Group, Inc. Confluent variable exhaust nozzle
FR2835288B1 (fr) * 2002-01-31 2006-04-28 Snecma Moteurs Systeme de refroidissement pour une tuyere de post-combustion de turbomachine

Also Published As

Publication number Publication date
CN100346066C (zh) 2007-10-31
KR20040102334A (ko) 2004-12-04
IL162142A (en) 2007-05-15
UA81234C2 (en) 2007-12-25
CA2469853A1 (fr) 2004-11-27
EP1482127A1 (fr) 2004-12-01
RU2342551C2 (ru) 2008-12-27
US20050005607A1 (en) 2005-01-13
US6966189B2 (en) 2005-11-22
NZ533014A (en) 2004-09-24
IL162142A0 (en) 2005-11-20
FR2855559A1 (fr) 2004-12-03
FR2855559B1 (fr) 2005-07-15
ES2270305T3 (es) 2007-04-01
JP2004353667A (ja) 2004-12-16
CN1573054A (zh) 2005-02-02
DE602004001546T2 (de) 2007-06-21
AU2004202177A1 (en) 2005-12-08
EP1482127B1 (fr) 2006-07-19
ZA200403929B (en) 2005-05-20
RU2004116112A (ru) 2006-01-10
DE602004001546D1 (de) 2006-08-31
JP4146389B2 (ja) 2008-09-10
ATE333570T1 (de) 2006-08-15
PL1482127T3 (pl) 2006-12-29

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Legal Events

Date Code Title Description
B25D Requested change of name of applicant approved

Owner name: SNECMA (FR)

Free format text: ALTERADO DE: SNECMA MOTEURS

B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE AS 6A, 7A E 8A ANUIDADES.

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: REFERENTE AO DESPACHO 8.6 PUBLICADO NA RPI 2160 DE 29/05/2012.