RU2005123972A - Носовой обтекатель для турбомашины - Google Patents

Носовой обтекатель для турбомашины Download PDF

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Publication number
RU2005123972A
RU2005123972A RU2005123972/06A RU2005123972A RU2005123972A RU 2005123972 A RU2005123972 A RU 2005123972A RU 2005123972/06 A RU2005123972/06 A RU 2005123972/06A RU 2005123972 A RU2005123972 A RU 2005123972A RU 2005123972 A RU2005123972 A RU 2005123972A
Authority
RU
Russia
Prior art keywords
fairing
rotor blades
shaft
turbomachine
hydraulic fluid
Prior art date
Application number
RU2005123972/06A
Other languages
English (en)
Other versions
RU2358130C2 (ru
Inventor
Ианн ЛЕБРЕ (FR)
Ианн ЛЕБРЕ
Эдуар РАМСТЕЙН (FR)
Эдуар РАМСТЕЙН
Original Assignee
Снекма (Fr)
Снекма
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 (Fr), Снекма filed Critical Снекма (Fr)
Publication of RU2005123972A publication Critical patent/RU2005123972A/ru
Application granted granted Critical
Publication of RU2358130C2 publication Critical patent/RU2358130C2/ru

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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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/057—Control or regulation
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/406—Transmission of power through hydraulic systems
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/64—Hydraulic actuators
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

Claims (6)

1. Носовой обтекатель для турбомашины, такой как, в частности, турбореактивный двигатель, устанавливаемый на конце вала, несущего лопасти винта, и служащий для управления углом наклона поступающего воздушного потока на основаниях лопастей винта, причем обтекатель установлен на упомянутом валу с помощью средств управляемого осевого смещения, тем самым обеспечивая изменение осевого положения обтекателя относительно лопастей винта.
2. Обтекатель по п.1, который является смещаемым по оси между передним положением для обеспечения защиты от засасывания твердых веществ и частиц, и задним положением для оптимизирования углов наклона воздушного потока на основаниях лопастей винта.
3. Обтекатель по п.1, который соединен с упомянутым валом с помощью гидравлического привода, имеющего цилиндр, прикрепленный к концу вала, и имеющий поршневой шток, несущий обтекатель.
4. Обтекатель по п.3, в котором гидравлический привод соединен с ротационными средствами подачи гидравлической текучей среды.
5. Обтекатель по п.4, в котором средства подачи гидравлической текучей среды содержат источник гидравлической текучей среды под давлением и регулирующие средства для регулирования давления.
6. Турбомашина, такая как турбореактивный двигатель, включающая в себя носовой обтекатель по п.1.
RU2005123972A 2004-07-28 2005-07-27 Носовой обтекатель для турбомашины RU2358130C2 (ru)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0408338 2004-07-28
FR0408338A FR2873751B1 (fr) 2004-07-28 2004-07-28 Cone d'entree d'une turbomachine

Publications (2)

Publication Number Publication Date
RU2005123972A true RU2005123972A (ru) 2007-02-10
RU2358130C2 RU2358130C2 (ru) 2009-06-10

Family

ID=34947981

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2005123972A RU2358130C2 (ru) 2004-07-28 2005-07-27 Носовой обтекатель для турбомашины

Country Status (8)

Country Link
US (1) US7419364B2 (ru)
EP (1) EP1621744B1 (ru)
JP (1) JP2006037955A (ru)
CN (1) CN1755080B (ru)
CA (1) CA2513783C (ru)
DE (1) DE602005005903T2 (ru)
FR (1) FR2873751B1 (ru)
RU (1) RU2358130C2 (ru)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006044968A1 (de) * 2006-09-23 2008-04-03 Mtu Aero Engines Gmbh Eintrittskonus für ein Strahltriebwerk
FR2943726B1 (fr) * 2009-03-31 2014-04-25 Snecma Capot d'entree tournant pour turbomachine, comprenant une extremite avant excentree
US9115593B2 (en) 2012-04-02 2015-08-25 United Technologies Corporation Turbomachine thermal management
US9127566B2 (en) 2012-04-02 2015-09-08 United Technologies Corporation Turbomachine thermal management
US9062566B2 (en) 2012-04-02 2015-06-23 United Technologies Corporation Turbomachine thermal management
EP2964924B1 (en) * 2013-03-04 2019-05-15 United Technologies Corporation Gas turbine engine inlet
US9481448B2 (en) 2013-03-11 2016-11-01 Rolls-Royce Corporation Aerodynamic fairings secondarily attached to nosecone
CN104167209B (zh) * 2014-08-06 2017-06-13 华为软件技术有限公司 一种音频失真的检测方法及装置
US10054059B2 (en) * 2014-09-15 2018-08-21 United Technologies Corporation Nacelle and compressor inlet arrangements
GB2552503A (en) * 2016-07-26 2018-01-31 Rolls Royce Plc Gas turbine engine
DE102016118783A1 (de) 2016-10-04 2018-04-05 Rolls-Royce Deutschland Ltd & Co Kg Turbofan-Triebwerk für ein ziviles Überschallflugzeug
KR101864129B1 (ko) * 2016-10-21 2018-06-04 국방과학연구소 초음속 항공기 흡입구의 노즈콘 제어 장치 및 제어 방법
CN110594170B (zh) * 2019-08-30 2021-11-12 广州市昊志机电股份有限公司 离心式压缩机和氢燃料电池系统
EP4067236A1 (fr) * 2021-03-29 2022-10-05 Airbus Operations (S.A.S.) Systeme de propulsion electrique d'un aeronef

Family Cites Families (6)

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DE1144060B (de) * 1960-08-04 1963-02-21 Daimler Benz Ag Verbundtriebwerk fuer Flugzeuge
US3196598A (en) * 1962-10-31 1965-07-27 Walter T Olson Inlet deflector for jet engines
US3495605A (en) * 1965-09-29 1970-02-17 Boeing Co Annular internal compression supersonic air inlet
GB1427339A (en) * 1972-11-15 1976-03-10 Rolls Royce Gas turbine engine
DE3935313C1 (ru) * 1989-10-24 1991-06-06 Mtu Muenchen Gmbh
BR9702572A (pt) * 1997-07-04 1999-01-19 Tinoco Soares Eduardo Alves Aperfeiçoamento introduzido em elemento de proteção contra a ingestão de aves por turbinas de aeronaves

Also Published As

Publication number Publication date
CA2513783C (fr) 2013-07-09
EP1621744A1 (fr) 2006-02-01
US20060056977A1 (en) 2006-03-16
JP2006037955A (ja) 2006-02-09
FR2873751A1 (fr) 2006-02-03
CN1755080A (zh) 2006-04-05
FR2873751B1 (fr) 2006-09-29
DE602005005903T2 (de) 2009-06-04
US7419364B2 (en) 2008-09-02
DE602005005903D1 (de) 2008-05-21
EP1621744B1 (fr) 2008-04-09
CA2513783A1 (fr) 2006-01-28
CN1755080B (zh) 2010-05-12
RU2358130C2 (ru) 2009-06-10

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