BR112012016552A2 - sistema de hélice de contra-rotação para um motor de turbina de aeronave - Google Patents

sistema de hélice de contra-rotação para um motor de turbina de aeronave

Info

Publication number
BR112012016552A2
BR112012016552A2 BR112012016552A BR112012016552A BR112012016552A2 BR 112012016552 A2 BR112012016552 A2 BR 112012016552A2 BR 112012016552 A BR112012016552 A BR 112012016552A BR 112012016552 A BR112012016552 A BR 112012016552A BR 112012016552 A2 BR112012016552 A2 BR 112012016552A2
Authority
BR
Brazil
Prior art keywords
counter
propeller
turbine engine
aircraft turbine
rotor
Prior art date
Application number
BR112012016552A
Other languages
English (en)
Inventor
Wouter Balk
Original Assignee
Snecma
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 filed Critical Snecma
Publication of BR112012016552A2 publication Critical patent/BR112012016552A2/pt

Links

Classifications

    • 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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B64C11/48—Units of two or more coaxial propellers
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
    • 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
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2260/98—Lubrication
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Retarders (AREA)
  • General Details Of Gearings (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Transmission Devices (AREA)

Abstract

sistema de hélice de contra-rotação para um motor de turbina de aeronave. a invenão se refere a um sistema de hélice de contra-rotação para um motor de turbina de aeronave, incluindo uma turbina de energia livre, incluindo um primeiro rotor e um segundo rotor contra-rotacionado em relação ao dito primeiro rotor, uma primeira hélice de contra-rotação (11) e uma segunda hélice de contra-rotação (12) para ser rodada em torno de um eixo longitudinal do sistema de hélice rotativo a uma estator do dito sistema, e um dispositivo mecânico de transmissão (20), em que o dito sistema é caracterizado pelo fato de o sistema de transmissão mecânica (20) ser fornecido entre a primeira hélice (11) e a segunda hélice (12).
BR112012016552A 2010-01-08 2011-01-07 sistema de hélice de contra-rotação para um motor de turbina de aeronave BR112012016552A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1000074A FR2955085B1 (fr) 2010-01-08 2010-01-08 Systeme d'helices contrarotatives pour turbomachine d'aeronef
PCT/EP2011/050147 WO2011083137A1 (fr) 2010-01-08 2011-01-07 Système d'hélices contrarotatives pour turbomachine d'aéronef

Publications (1)

Publication Number Publication Date
BR112012016552A2 true BR112012016552A2 (pt) 2016-04-26

Family

ID=42562786

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012016552A BR112012016552A2 (pt) 2010-01-08 2011-01-07 sistema de hélice de contra-rotação para um motor de turbina de aeronave

Country Status (9)

Country Link
US (1) US9611809B2 (pt)
EP (1) EP2521851B1 (pt)
JP (1) JP5620519B2 (pt)
CN (1) CN102686864B (pt)
BR (1) BR112012016552A2 (pt)
CA (1) CA2786130A1 (pt)
FR (1) FR2955085B1 (pt)
RU (1) RU2551143C2 (pt)
WO (1) WO2011083137A1 (pt)

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US8246292B1 (en) * 2012-01-31 2012-08-21 United Technologies Corporation Low noise turbine for geared turbofan engine
US9028200B2 (en) 2012-02-29 2015-05-12 United Technologies Corporation Counter rotating low pressure turbine with splitter gear system
US20130219859A1 (en) * 2012-02-29 2013-08-29 Gabriel L. Suciu Counter rotating low pressure compressor and turbine each having a gear system
US9080512B2 (en) * 2012-02-29 2015-07-14 United Technologies Corporation Counter-rotating low pressure turbine with gear system mounted to mid turbine frame
EP2989300B1 (en) * 2013-04-22 2021-10-20 Raytheon Technologies Corporation Low loss bearing drain
US9701395B2 (en) 2014-01-06 2017-07-11 United Technologies Corporation Contra-rotating open rotor distributed propulsion system
FR3020658B1 (fr) 2014-04-30 2020-05-15 Safran Aircraft Engines Capot de recuperation d'huile de lubrification pour un equipement de turbomachine
FR3039227B1 (fr) * 2015-07-22 2019-12-27 Safran Aircraft Engines Aeronef comprenant un propulseur arriere carene avec stator d’entree a volets mobiles
PL226824B1 (pl) * 2015-09-07 2017-09-29 Gen Electric Układ isposób regulacji skoku smigła
FR3041933B1 (fr) 2015-10-05 2018-07-13 Safran Aircraft Engines Aeronef avec un ensemble propulsif comprenant un doublet d'helices a l'arriere du fuselage
CN108082500A (zh) * 2018-01-29 2018-05-29 吉林大学 一种固定翼式混合动力飞行器驱动装置及驱动方法
GB201900609D0 (en) * 2019-01-16 2019-03-06 Rolls Royce Plc Mounting apparatus for gas turbine engine
CN110185760B (zh) * 2019-04-30 2020-10-02 中国航发南方工业有限公司 涡桨发动机的星形减速器
GB201910009D0 (en) * 2019-07-12 2019-08-28 Rolls Royce Plc Gas turbine engine electrical generator
GB201910011D0 (en) * 2019-07-12 2019-08-28 Rolls Royce Plc Gas turbine engine electrical generator
IT201900014724A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.
FR3104212B1 (fr) * 2019-12-10 2021-11-19 Safran Aircraft Engines Turbomachine a turbine contrarotative pour un aeronef
US11486312B2 (en) * 2020-08-04 2022-11-01 Ge Avio S.R.L. Gearbox efficiency rating for turbomachine engines
US11473507B2 (en) * 2020-08-04 2022-10-18 Ge Avio S.R.L. Gearbox efficiency rating for turbomachine engines
US20220042464A1 (en) * 2020-08-04 2022-02-10 Ge Avio S.R.L. Gearbox efficiency rating for turbomachine engines
US11365688B2 (en) 2020-08-04 2022-06-21 G.E. Avio S.r.l. Gearbox efficiency rating for turbomachine engines
US11401829B2 (en) 2020-08-04 2022-08-02 Ge Avio S.R.L. Gearbox efficiency rating for turbomachine engines
FR3125797B1 (fr) 2021-07-29 2025-09-26 Safran Aircraft Engines Propulseur pour un aéronef
IT202200001613A1 (it) 2022-01-31 2023-07-31 Gen Electric Valutazione di efficienza motoristica complessiva per motori a turbomacchina
US12428962B1 (en) 2024-06-14 2025-09-30 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes
US12560125B2 (en) 2024-06-14 2026-02-24 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes

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Also Published As

Publication number Publication date
FR2955085A1 (fr) 2011-07-15
EP2521851B1 (fr) 2013-11-13
JP5620519B2 (ja) 2014-11-05
WO2011083137A1 (fr) 2011-07-14
RU2551143C2 (ru) 2015-05-20
CN102686864A (zh) 2012-09-19
US9611809B2 (en) 2017-04-04
EP2521851A1 (fr) 2012-11-14
CA2786130A1 (fr) 2011-07-14
US20120288358A1 (en) 2012-11-15
JP2013516572A (ja) 2013-05-13
CN102686864B (zh) 2015-09-09
RU2012133966A (ru) 2014-02-20
FR2955085B1 (fr) 2011-12-23

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Legal Events

Date Code Title Description
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]
B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]