UA85369C2 - Створка сопла авиационного турбинного двигателя и способ изготовления створки сопла (варианты) - Google Patents

Створка сопла авиационного турбинного двигателя и способ изготовления створки сопла (варианты)

Info

Publication number
UA85369C2
UA85369C2 UA20040503972A UA20040503972A UA85369C2 UA 85369 C2 UA85369 C2 UA 85369C2 UA 20040503972 A UA20040503972 A UA 20040503972A UA 20040503972 A UA20040503972 A UA 20040503972A UA 85369 C2 UA85369 C2 UA 85369C2
Authority
UA
Ukraine
Prior art keywords
fibres
nozzle flap
flap
wall
variants
Prior art date
Application number
UA20040503972A
Other languages
English (en)
Ukrainian (uk)
Inventor
Тіері Панку
Ерве Баре
Клод Корбін
Стефан БЛАНШАР
Original Assignee
Снекма Моторс
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 Моторс filed Critical Снекма Моторс
Publication of UA85369C2 publication Critical patent/UA85369C2/ru

Links

Classifications

    • A—HUMAN NECESSITIES
    • A21—BAKING; EDIBLE DOUGHS
    • A21B—BAKERS' OVENS; MACHINES OR EQUIPMENT FOR BAKING
    • A21B3/00—Parts or accessories of ovens
    • A21B3/13—Baking-tins; Baking forms
    • A21B3/137—Baking-tins; Baking forms with detachable side and bottom parts, e.g. springform
    • 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
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • A—HUMAN NECESSITIES
    • A21—BAKING; EDIBLE DOUGHS
    • A21B—BAKERS' OVENS; MACHINES OR EQUIPMENT FOR BAKING
    • A21B3/00—Parts or accessories of ovens
    • A21B3/13—Baking-tins; Baking forms
    • A21B3/133—Baking-tins; Baking forms for making bread
    • A21B3/134—Multiple bread pans
    • A—HUMAN NECESSITIES
    • A47—FURNITURE; DOMESTIC ARTICLES OR APPLIANCES; COFFEE MILLS; SPICE MILLS; SUCTION CLEANERS IN GENERAL
    • A47J—KITCHEN EQUIPMENT; COFFEE MILLS; SPICE MILLS; APPARATUS FOR MAKING BEVERAGES
    • A47J37/00—Baking; Roasting; Grilling; Frying
    • A47J37/06—Roasters; Grills; Sandwich grills
    • A47J37/0611—Roasters; Grills; Sandwich grills the food being cooked between two heating plates, e.g. waffle-irons
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments
    • 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)
  • Food Science & Technology (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Extrusion Moulding Of Plastics Or The Like (AREA)
  • Chemical Vapour Deposition (AREA)
  • Furnace Housings, Linings, Walls, And Ceilings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Laminated Bodies (AREA)
  • Wing Frames And Configurations (AREA)
  • Thermal Insulation (AREA)
  • Nonwoven Fabrics (AREA)

Abstract

Данное изобретение касается створки сопла с увеличенным сроком службы для авиационного газотурбинного двигателя. Такая створка отличается тем, что содержит корпус (10) в форме полого усеченного конуса, сплющенного в поперечном направлении, вдоль прямолинейных геометрических образующих линий (11). При этом корпус (10) образовывает тонкую стенку (12) практически постоянной толщины Е, стенка (12) имеет сплошную внутреннюю поверхность с радиусом кривизны, которая равняется по крайней мере 2Е, и выполнена из огнеупорного композитного материала, который состоит из усилительных волокон (18) из огнеупорного материала, встроенных в матрицу также из огнеупорного материала. При этом усилительные волокна (18) расположены в виде многочисленных слоев, наложенных один на другой, где волокна (18а) одного слоя скрещиваются с волокнами (18b) соседнего с ним слоя.
UA20040503972A 2003-05-26 2004-05-25 Створка сопла авиационного турбинного двигателя и способ изготовления створки сопла (варианты) UA85369C2 (ru)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0350177A FR2855557B1 (fr) 2003-05-26 2003-05-26 Volet de tuyere a duree de vie augmentee pour turbomoteurs d'avion.

Publications (1)

Publication Number Publication Date
UA85369C2 true UA85369C2 (ru) 2009-01-26

Family

ID=33104530

Family Applications (1)

Application Number Title Priority Date Filing Date
UA20040503972A UA85369C2 (ru) 2003-05-26 2004-05-25 Створка сопла авиационного турбинного двигателя и способ изготовления створки сопла (варианты)

Country Status (15)

Country Link
US (1) US6964169B2 (ru)
EP (1) EP1482158B1 (ru)
JP (1) JP4116984B2 (ru)
KR (1) KR101124011B1 (ru)
CN (1) CN100371580C (ru)
AU (1) AU2004202297B2 (ru)
BR (1) BRPI0401835B1 (ru)
CA (1) CA2467842C (ru)
DE (1) DE602004019013D1 (ru)
ES (1) ES2318240T3 (ru)
FR (1) FR2855557B1 (ru)
RU (1) RU2358136C2 (ru)
TW (1) TWI323714B (ru)
UA (1) UA85369C2 (ru)
ZA (1) ZA200403904B (ru)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2894500B1 (fr) * 2005-12-08 2009-07-10 Snecma Sa Assemblage par brasage d'une piece metallique avec une piece en materiau ceramique
FR2894499B1 (fr) * 2005-12-08 2011-04-01 Snecma Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c
FR2894498B1 (fr) * 2005-12-08 2009-07-10 Snecma Sa Assemblage par brasage entre une piece metallique a base de titane et une piece en materiau ceramique a base de carbure de silicium (sic) et/ou de carbone
US7617685B2 (en) * 2006-09-29 2009-11-17 United Technologies Corporation Quick change fastener system for attaching liner bracket to convergent flap and seal in turbine nozzle
US7685825B2 (en) * 2006-09-29 2010-03-30 United Technologies Corporation Axially split nozzle liner for convergent nozzle
FR2914707B1 (fr) * 2007-04-05 2009-10-30 Snecma Propulsion Solide Sa Procede d'assemblage avec recouvrement de deux pieces ayant des coefficients de dilatation differents et assemblage ainsi obtenu
US8043690B2 (en) * 2008-04-21 2011-10-25 The Boeing Company Exhaust washed structure and associated composite structure and method of fabrication
US9932845B2 (en) * 2011-06-30 2018-04-03 United Technologies Corporation Impingement cooled nozzle liner
FR2979575B1 (fr) * 2011-09-05 2013-09-20 Snecma Procede et dispositif de fabrication d'une piece cylindrique en materiau composite
US20140238027A1 (en) * 2012-12-21 2014-08-28 United Technologies Corporation Thermally compliant dual wall liner for a gas turbine engine
EP3097301B1 (en) * 2014-01-24 2018-05-02 United Technologies Corporation Divergent flap
US10352273B2 (en) 2016-11-08 2019-07-16 Rohr, Inc. Track beam with composite lug
CN107618654B (zh) * 2017-08-03 2021-03-30 南京航空航天大学 飞行器姿态控制系统及其控制方法、控制喷嘴
CN113530705A (zh) * 2021-08-18 2021-10-22 中国航发贵阳发动机设计研究所 一种航空发动机可调喷管外调节片收放限位装置

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4196856A (en) * 1977-11-25 1980-04-08 The Boeing Company Variable geometry convergent divergent exhaust nozzle
US4637550A (en) * 1985-10-01 1987-01-20 The United States Of America As Represented By The Secretary Of The Air Force Dual material exhaust nozzle flap
US5553455A (en) * 1987-12-21 1996-09-10 United Technologies Corporation Hybrid ceramic article
FR2637838B1 (fr) * 1988-10-14 1991-01-25 Europ Propulsion Procede de fabrication de pieces composites constituees d'un voile et d'un renfort
US5000386A (en) * 1989-07-03 1991-03-19 General Electric Company Exhaust flaps
FR2664585B1 (fr) * 1990-07-13 1993-08-06 Europ Propulsion Structures refractaires refroidies et procede pour leur fabrication.
US5992140A (en) * 1997-06-24 1999-11-30 Sikorsky Aircraft Corporation Exhaust nozzle for suppressing infrared radiation
FR2919897B1 (fr) * 2007-08-08 2014-08-22 Snecma Secteur de distributeur de turbine

Also Published As

Publication number Publication date
DE602004019013D1 (de) 2009-03-05
TW200505744A (en) 2005-02-16
CN100371580C (zh) 2008-02-27
JP4116984B2 (ja) 2008-07-09
US20050005608A1 (en) 2005-01-13
KR101124011B1 (ko) 2012-03-27
ZA200403904B (en) 2005-07-27
AU2004202297A1 (en) 2004-12-16
BRPI0401835A (pt) 2005-01-25
FR2855557B1 (fr) 2007-03-02
US6964169B2 (en) 2005-11-15
FR2855557A1 (fr) 2004-12-03
ES2318240T3 (es) 2009-05-01
AU2004202297B2 (en) 2009-07-30
RU2004116014A (ru) 2005-11-20
CA2467842C (en) 2012-01-24
CN1538051A (zh) 2004-10-20
EP1482158A1 (fr) 2004-12-01
RU2358136C2 (ru) 2009-06-10
JP2004353668A (ja) 2004-12-16
TWI323714B (en) 2010-04-21
BRPI0401835B1 (pt) 2014-04-29
EP1482158B1 (fr) 2009-01-14
KR20040101934A (ko) 2004-12-03
CA2467842A1 (en) 2004-11-26

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