BR112014019985A8 - Nacela de motor de turbina e conjunto de propulsão de aeronave compreendendo um motor de turbina alojado no interior de uma nacela - Google Patents

Nacela de motor de turbina e conjunto de propulsão de aeronave compreendendo um motor de turbina alojado no interior de uma nacela

Info

Publication number
BR112014019985A8
BR112014019985A8 BR112014019985A BR112014019985A BR112014019985A8 BR 112014019985 A8 BR112014019985 A8 BR 112014019985A8 BR 112014019985 A BR112014019985 A BR 112014019985A BR 112014019985 A BR112014019985 A BR 112014019985A BR 112014019985 A8 BR112014019985 A8 BR 112014019985A8
Authority
BR
Brazil
Prior art keywords
turbine engine
nacelle
nacella
housed inside
propulsion assembly
Prior art date
Application number
BR112014019985A
Other languages
English (en)
Other versions
BR112014019985A2 (pt
Inventor
Caruel Pierre
Zaganelli Franck
Gonidec Patrick
Kerbler Olivier
Original Assignee
Aircelle Sa
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 Aircelle Sa filed Critical Aircelle Sa
Publication of BR112014019985A2 publication Critical patent/BR112014019985A2/pt
Publication of BR112014019985A8 publication Critical patent/BR112014019985A8/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
    • B64D15/04—Hot gas application
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B64D33/10—Radiator arrangement
    • 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
    • F02C7/047—Heating to prevent icing
    • 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
    • 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
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

NACELA DE MOTOR DE TURBINA E CONJUNTO DE PROPULSÃO DE AERONAVE COMPREENDENDO UM MOTOR DE TURBINA ALOJADO NO INTERIOR DE UMA NACELA. A presente invenção se refere a uma nacela (1) de um motor de turbina (2) compreendendo pelo menos uma capota externa (3) definindo uma superfície aerodinâmica externa e pelo menos uma capota interna (4) definindo uma superfície de fluxo aerodinâmica interna, estas superfícies sendo conectadas a montante por uma parede de borda principal que forma uma aba de entrada de ar (6), dita nacela de motor de turbina compreendendo pelo menos um permutador de calor (10) associado com pelo menos um duto de fluxo (13), formando pelo menos um circuito de recirculação através do permutador e compreendendo pelo menos uma zona de circulação (13a) se estendendo pelo menos parcialmente ao longo da capota externa em contato com pelo menos uma parede da dita capota externa de modo a permitir a troca de calor por condução com o ar de fora da nacela.
BR112014019985A 2012-03-02 2013-02-13 Nacela de motor de turbina e conjunto de propulsão de aeronave compreendendo um motor de turbina alojado no interior de uma nacela BR112014019985A8 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1251942A FR2987602B1 (fr) 2012-03-02 2012-03-02 Nacelle de turbomoteur equipe d'un echangeur de chaleur
PCT/FR2013/050290 WO2013128093A1 (fr) 2012-03-02 2013-02-13 Nacelle de turbomoteur équipé d'un échangeur de chaleur

Publications (2)

Publication Number Publication Date
BR112014019985A2 BR112014019985A2 (pt) 2017-06-20
BR112014019985A8 true BR112014019985A8 (pt) 2017-07-11

Family

ID=47843332

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112014019985A BR112014019985A8 (pt) 2012-03-02 2013-02-13 Nacela de motor de turbina e conjunto de propulsão de aeronave compreendendo um motor de turbina alojado no interior de uma nacela

Country Status (8)

Country Link
US (1) US10294822B2 (pt)
EP (1) EP2819921B1 (pt)
CN (1) CN104136322B (pt)
BR (1) BR112014019985A8 (pt)
CA (1) CA2865479A1 (pt)
FR (1) FR2987602B1 (pt)
RU (1) RU2014139477A (pt)
WO (1) WO2013128093A1 (pt)

Families Citing this family (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010051517A1 (de) * 2010-11-16 2012-05-16 Airbus Operations Gmbh Flugzeugaußenhautwärmetauscher, Flugzeugkühlsystem und Verfahren zum Betreiben eines Flugzeugaußenhautwärmetauschers
US9765694B2 (en) * 2012-08-07 2017-09-19 Unison Industries, Llc Gas turbine engine heat exchangers and methods of assembling the same
US9157446B2 (en) 2013-01-31 2015-10-13 Danfoss A/S Centrifugal compressor with extended operating range
EP2961965A4 (en) * 2013-02-26 2016-12-07 United Technologies Corp PLURIETAGED AIR FLOW MANAGEMENT
FR3007738B1 (fr) * 2013-06-28 2015-07-31 Aircelle Sa Dispositif de degivrage et de conditionnement pour aeronef
US9382911B2 (en) 2013-11-14 2016-07-05 Danfoss A/S Two-stage centrifugal compressor with extended range and capacity control features
CN104675524B (zh) * 2013-11-27 2017-01-18 中航商用航空发动机有限责任公司 分流环、发动机防冰装置以及涡扇发动机
FR3018503B1 (fr) * 2014-03-13 2017-10-13 Snecma Nacelle comprenant un echangeur pour refroidir un flux d'air
CN105089802B (zh) * 2014-05-22 2017-02-01 中航商用航空发动机有限责任公司 一种航空燃气轮机用防冰装置及方法
FR3027624B1 (fr) * 2014-10-27 2019-04-19 Safran Aircraft Engines Circuit de degivrage d'une levre d'entree d'air d'un ensemble propulsif d'aeronef
EP3018304B1 (en) 2014-11-06 2020-10-14 United Technologies Corporation Thermal management system for a gas turbine engine
US20160160758A1 (en) * 2014-12-08 2016-06-09 United Technologies Corporation Gas turbine engine nacelle anti-icing system
DE102015203218A1 (de) * 2015-02-23 2016-08-25 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinentriebwerk mit Ölkühler in der Triebwerksverkleidung
ITUB20151085A1 (it) 2015-05-28 2016-11-28 Alenia Aermacchi Spa Gondola per motore aeronautico con sistema antighiaccio utilizzante un fluido bifase.
US10144521B2 (en) * 2015-08-04 2018-12-04 Hamilton Sundstrand Corporation Electric compressor for use with a wing anti-ice system
FR3041703B1 (fr) * 2015-09-29 2019-08-16 Safran Nacelles Dispositif de degivrage pour levre d’entree d’air de nacelle de turboreacteur d’aeronef
CN105599906A (zh) * 2016-01-28 2016-05-25 南京航空航天大学 采用回路型热管的航空发动机整流帽罩防冰装置及方法
CN109072930B (zh) 2016-02-04 2021-08-13 丹佛斯公司 离心压缩机和操作离心压缩机的方法
US10315754B2 (en) 2016-06-10 2019-06-11 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10823061B2 (en) * 2016-07-15 2020-11-03 General Electric Company Engine air inlet having a double-panel heated wall
FR3054204B1 (fr) 2016-07-20 2020-01-24 Safran Nacelles Nacelle de turbomoteur comportant un dispositif de refroidissement
FR3054856B1 (fr) * 2016-08-03 2018-09-07 Airbus Operations Sas Turbomachine comportant un systeme de gestion thermique
US10443497B2 (en) * 2016-08-10 2019-10-15 Rolls-Royce Corporation Ice protection system for gas turbine engines
US11105340B2 (en) * 2016-08-19 2021-08-31 General Electric Company Thermal management system for an electric propulsion engine
US11060457B2 (en) * 2016-12-02 2021-07-13 Pratt & Whitney Canada Corp. Cooling system and method for gas turbine engine
US20180171871A1 (en) * 2016-12-15 2018-06-21 Pratt & Whitney Canada Corp. Surface Cooler with Flow Recirculation
CN107100738A (zh) * 2016-12-19 2017-08-29 浙江科技学院 一种蜗扇发动机的防结冰装置
US20180229850A1 (en) * 2017-02-15 2018-08-16 Pratt & Whitney Canada Corp. Anti-icing system for gas turbine engine
FR3065490B1 (fr) * 2017-04-24 2019-07-12 Safran Aircraft Engines Ensemble propulsif pour aeronef comportant des echangeurs de chaleur air-liquide
FR3072421B1 (fr) * 2017-10-18 2019-09-27 Airbus Operations Levre d'entree d'air d'un moteur d'aeronef comportant un systeme de degivrage
FR3072649B1 (fr) * 2017-10-20 2019-11-08 Airbus Operations Systeme de protection contre le givre pour nacelle de moteur d'aeronef
US11292604B2 (en) * 2017-10-23 2022-04-05 Pratt & Whitney Canada Corp. Integrated heat management for hybrid propulsion
US10683076B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
US11293293B2 (en) 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
CN110159358B (zh) * 2018-02-14 2022-02-08 中国航发商用航空发动机有限责任公司 级间机匣
US11035295B2 (en) * 2018-04-18 2021-06-15 Lockheed Martin Corporation Engine nacelle heat exchanger
US11111025B2 (en) * 2018-06-22 2021-09-07 Coflow Jet, LLC Fluid systems that prevent the formation of ice
CN109229339A (zh) * 2018-08-30 2019-01-18 哈尔滨飞机工业集团有限责任公司 一种直升机动力舱前部整流罩
FR3088961A1 (fr) * 2018-11-22 2020-05-29 Airbus Operations (S.A.S.) Turbomachine équipée d’un système de dégivrage de l’entrée d’air.
EP3666655B1 (en) * 2018-12-14 2021-07-14 Airbus Operations (S.A.S.) Aircraft propulsion system including a heat exchanger system
FR3094749B1 (fr) * 2019-04-03 2021-11-19 Safran Nacelles Système de refroidissement de turboréacteur pour aéronef
US11384687B2 (en) * 2019-04-04 2022-07-12 Pratt & Whitney Canada Corp. Anti-icing system for gas turbine engine
GB2600584B (en) 2019-07-23 2024-03-06 Coflow Jet Llc Fluid systems and methods that address flow separation
US10730635B1 (en) 2019-08-23 2020-08-04 Raytheon Technologies Corporation Engine wing
FR3100228B1 (fr) * 2019-08-30 2022-10-28 Airbus Operations Sas Système électropneumatique de protection contre le givre pour aéronef, et ensemble propulsif et aéronef pourvus d’un tel système.
US11326519B2 (en) 2020-02-25 2022-05-10 General Electric Company Frame for a heat engine
FR3107563A1 (fr) * 2020-02-25 2021-08-27 Airbus Operations Ensemble propulsif pour aeronef comportant un systeme de ventilation
US11255264B2 (en) 2020-02-25 2022-02-22 General Electric Company Frame for a heat engine
US11560843B2 (en) 2020-02-25 2023-01-24 General Electric Company Frame for a heat engine
US11300049B2 (en) * 2020-03-09 2022-04-12 Rolls-Royce North American Technologies Inc. Inlet guide vane draw heat exchanger system
CN111591452B (zh) * 2020-04-03 2021-11-26 湖北吉利太力飞车有限公司 垂起飞行器的通风装置及控制方法
CN111577466A (zh) * 2020-06-22 2020-08-25 中国航空发动机研究院 航空发动机防冰引气预热与涡轮冷却引气预冷系统
CN112455693A (zh) * 2020-12-02 2021-03-09 唐建平 一种航空航天用换气装置
US11415051B2 (en) 2020-12-22 2022-08-16 General Electric Company System for lubricating components of a gas turbine engine including a lubricant bypass conduit
CN112758312A (zh) * 2020-12-30 2021-05-07 阿坝师范学院 一种高原用多旋翼无人机
CN114151149B (zh) * 2021-10-20 2023-06-30 中国航发四川燃气涡轮研究院 一种燃气涡轮发动机燃滑油热管理与防冰综合控制系统
FR3130893B1 (fr) 2021-12-21 2023-11-17 Safran Système de refroidissement d’un liquide de lubrification d’une turbomachine d’aéronef
FR3139116A1 (fr) * 2022-08-30 2024-03-01 Airbus Operations Nacelle d’un moteur d’aéronef comportant un échangeur de chaleur amélioré
US20240190573A1 (en) * 2022-12-13 2024-06-13 Pratt & Whitney Canada Corp. Aircraft thermal anti-icing system

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2820601A (en) * 1953-03-09 1958-01-21 Northrop Aircraft Inc Movable wing tip
US3981466A (en) * 1974-12-23 1976-09-21 The Boeing Company Integrated thermal anti-icing and environmental control system
US4482114A (en) * 1981-01-26 1984-11-13 The Boeing Company Integrated thermal anti-icing and environmental control system
US4782658A (en) * 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
US5683062A (en) * 1995-02-27 1997-11-04 General Electric Company Aircraft anti-insect system
US6371411B1 (en) * 1999-11-23 2002-04-16 The Boeing Company Method and apparatus for aircraft inlet ice protection
US6688558B2 (en) * 1999-11-23 2004-02-10 The Boeing Company Method and apparatus for aircraft inlet ice protection
GB0311663D0 (en) * 2003-05-21 2003-06-25 Rolls Royce Plc Aeroengine intake
US7454894B2 (en) * 2004-12-07 2008-11-25 United Technologies Corporation Supplemental oil cooler airflow for gas turbine engine
US7823374B2 (en) * 2006-08-31 2010-11-02 General Electric Company Heat transfer system and method for turbine engine using heat pipes
US7845159B2 (en) * 2006-08-31 2010-12-07 General Electric Company Heat pipe-based cooling apparatus and method for turbine engine

Also Published As

Publication number Publication date
US10294822B2 (en) 2019-05-21
EP2819921B1 (fr) 2018-10-24
BR112014019985A2 (pt) 2017-06-20
FR2987602B1 (fr) 2014-02-28
CN104136322A (zh) 2014-11-05
EP2819921A1 (fr) 2015-01-07
CA2865479A1 (fr) 2013-09-06
US20140369812A1 (en) 2014-12-18
CN104136322B (zh) 2016-05-18
WO2013128093A1 (fr) 2013-09-06
RU2014139477A (ru) 2016-04-27
FR2987602A1 (fr) 2013-09-06

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