FR3050763B1 - Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur - Google Patents

Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur Download PDF

Info

Publication number
FR3050763B1
FR3050763B1 FR1653817A FR1653817A FR3050763B1 FR 3050763 B1 FR3050763 B1 FR 3050763B1 FR 1653817 A FR1653817 A FR 1653817A FR 1653817 A FR1653817 A FR 1653817A FR 3050763 B1 FR3050763 B1 FR 3050763B1
Authority
FR
France
Prior art keywords
hot air
air
heat exchanger
turbomachine
circulation device
Prior art date
Legal status (The legal status 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 status listed.)
Active
Application number
FR1653817A
Other languages
English (en)
Other versions
FR3050763A1 (fr
Inventor
Albert Beutin Bruno
Nuria Llamas Castro
Maria NATAL
Manuela Ramos Bruna
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
SNECMA SAS
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 Safran Aircraft Engines SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1653817A priority Critical patent/FR3050763B1/fr
Priority to US15/498,970 priority patent/US10634050B2/en
Publication of FR3050763A1 publication Critical patent/FR3050763A1/fr
Application granted granted Critical
Publication of FR3050763B1 publication Critical patent/FR3050763B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine 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
    • F02C7/04—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
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • 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
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low solidity propeller
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/325—Application in turbines in gas turbines to drive unshrouded, high solidity propeller
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/44—Movement of components by counter rotation
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'objet principal de l'invention est un dispositif (1) de circulation d'air pour turbomachine (10), comportant un circuit d'acheminement d'air (2, 4b, 9, 4a, 3), adapté pour acheminer de l'air chaud (A1) prélevé sur la turbomachine (10) jusqu'à une partie à réchauffer (38), comprenant un premier tronçon, solidaire en rotation d'une partie rotative (31, 24) et comprenant au moins un conduit d'acheminement (3, 9) d'air chaud (A2), et un dispositif de passage d'air chaud (4a, 4b), comportant un compartiment annulaire solidaire en rotation du premier tronçon, caractérisé en ce que le compartiment annulaire comprend un échangeur de chaleur en contact avec l'air extérieur, et en ce que le dispositif de passage d'air chaud (4a, 4b) comprend un système de dérivation d'air chaud pour dévier l'air entrant dans le dispositif et le faire circuler le long de l'échangeur de chaleur quand la température de cet air entrant dépasse un seuil prédéterminé.
FR1653817A 2016-04-28 2016-04-28 Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur Active FR3050763B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1653817A FR3050763B1 (fr) 2016-04-28 2016-04-28 Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur
US15/498,970 US10634050B2 (en) 2016-04-28 2017-04-27 Air circulation device for a turbomachine comprising a hot air bypass system to a heat exchanger

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1653817A FR3050763B1 (fr) 2016-04-28 2016-04-28 Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur
FR1653817 2016-04-28

Publications (2)

Publication Number Publication Date
FR3050763A1 FR3050763A1 (fr) 2017-11-03
FR3050763B1 true FR3050763B1 (fr) 2018-04-13

Family

ID=56119663

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1653817A Active FR3050763B1 (fr) 2016-04-28 2016-04-28 Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur

Country Status (2)

Country Link
US (1) US10634050B2 (fr)
FR (1) FR3050763B1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10267334B2 (en) * 2016-08-01 2019-04-23 United Technologies Corporation Annular heatshield
US10578498B2 (en) * 2017-06-22 2020-03-03 Unison Industries, Llc Air temperature sensor
FR3084699B1 (fr) * 2018-07-31 2020-09-25 Safran Aircraft Engines Echangeur thermique pour turbomachine et procede de fabrication associe
FR3084698B1 (fr) * 2018-07-31 2020-07-24 Safran Aircraft Engines Echangeur thermique pour turbomachine
US11577844B2 (en) 2020-03-12 2023-02-14 Rohr, Inc. Variable diameter piccolo tube for anti-icing system
FR3108656B1 (fr) * 2020-03-24 2022-03-04 Safran Aircraft Engines Dispositif de refroidissement et de pressurisation d'une turbine de turbomachine.
DE102021116507A1 (de) * 2021-06-25 2022-12-29 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinentriebwerk
CN113565631A (zh) * 2021-08-17 2021-10-29 中国航发贵阳发动机设计研究所 一种航空发动机引气自动控制装置

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2668596A (en) * 1947-07-04 1954-02-09 Rotol Ltd Anthcing and intake means for turbine-propeller units
US2681191A (en) * 1947-08-18 1954-06-15 Rotol Ltd Airscrew-driving gas turbine engine power plant with anti-icing means for the airscrews
US4936748A (en) * 1988-11-28 1990-06-26 General Electric Company Auxiliary power source in an unducted fan gas turbine engine
US5841079A (en) 1997-11-03 1998-11-24 Northrop Grumman Corporation Combined acoustic and anti-ice engine inlet liner
GB2413366B (en) * 2004-04-24 2006-09-13 Rolls Royce Plc Engine.
FR2941492B1 (fr) 2009-01-23 2011-09-09 Snecma Turbomachine a turbine de puissance equipee d'un generateur electronique de puissance centre sur l'axe de la turbomachine
FR2941494B1 (fr) * 2009-01-23 2011-08-26 Snecma Turbomachine a turbine de puissance equipee d'un generateur electrique de puissance
FR2951502B1 (fr) 2009-10-15 2013-08-02 Snecma Architecture de turbomachine ameliorant l'admission d'air
US9243563B2 (en) * 2012-01-25 2016-01-26 Honeywell International Inc. Gas turbine engine in-board cooled cooling air system
WO2014051678A1 (fr) * 2012-09-28 2014-04-03 United Technologies Corporation Système de gestion thermique de moteur à turbine à gaz pour échangeur thermique utilisant un écoulement dérivé
FR3018857B1 (fr) * 2014-03-21 2016-05-06 Snecma Circuit de refroidissement d'air chaud sous pression d'une turbomachine d'aeronef comportant un echangeur de chaleur pour refroidir l'air
FR3021628B1 (fr) * 2014-06-03 2017-12-22 Snecma Dispositif de degivrage et/ou d'antigivrage de recepteur de turbomachine comportant des moyens de passage d'air chaud entre deux parties de recepteur de turbomachine

Also Published As

Publication number Publication date
FR3050763A1 (fr) 2017-11-03
US10634050B2 (en) 2020-04-28
US20170314465A1 (en) 2017-11-02

Similar Documents

Publication Publication Date Title
FR3050763B1 (fr) Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur
RU2010102057A (ru) Турбореактивный двигатель для летательного аппарата
EP2157016A3 (fr) Système de refroidissement d'équipements électriques ou électroniques d'un aéronef
WO2015112215A3 (fr) Système d'injection de carburnat refroidi pour moteur à turbine à gaz
WO2016099662A3 (fr) Ensemble de composants de moteur
EP2815979A3 (fr) Système de chauffage de l'habitacle d'un aéronef muni d'un échangeur thermique annulaire autour de la tuyère d'échappement
FR3034129B1 (fr) Aube mobile de turbine a conception amelioree pour turbomachine d'aeronef
RU2015138982A (ru) Установка для терморегулирования обоймы направляющих лопаток и способ управления зазорами
JP2018519491A5 (fr)
FR3087420B1 (fr) Nacelle de moteur d’aeronef comprenant un systeme de protection contre le givre.
FR3037639B1 (fr) Dispositif de gestion thermique
FR2985978A1 (fr) Installation a traitement thermique de fluide pour giravion, associant un systeme de refroidissement d'un groupe de motorisation et un systeme de chauffage de l'habitacle
WO2021034359A3 (fr) Système multi-mode de rejet de chaleur
FR3054204B1 (fr) Nacelle de turbomoteur comportant un dispositif de refroidissement
SE542203C2 (en) A vehicle with a fan arrangement
FR3072449B1 (fr) Dispositif autonome de mesure des caracteristiques d'un fluide circulant dans un conduit et systeme de commande de la ventilation, de la climatisation et/ou du chauffage utilisant un tel dispositif
FR3068305B1 (fr) Dispositif de regulation d'un flux d'air pour une entree d'air d'un vehicule automobile
WO2016197902A1 (fr) Dispositif de chauffage d'eau équilibré en gaz
FR3087419B1 (fr) Nacelle de moteur d’aeronef comprenant un systeme de protection contre le givre.
US10060332B2 (en) Cooling apparatus for internal combustion engine
FR3077604B1 (fr) Systeme de refroidissement d'air moteur a deux etages de refroidissement et comprenant au moins un echangeur cylindrique
EP3349556A3 (fr) Canal d'entrée d'air comportant un élément de refroidissement thermoélectrique
WO2018128684A3 (fr) Moteur à turbine et son procédé de refroidissement
SE1450726A1 (sv) Arrangemang för uppvärmning av ett utrymme i ett fordon
JP6293685B2 (ja) 強制給排気式暖房装置

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20171103

PLFP Fee payment

Year of fee payment: 3

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20180809

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

PLFP Fee payment

Year of fee payment: 9