EP4374057A1 - Système pour refroidir de l'huile dans une turbomachine d'aéronef - Google Patents

Système pour refroidir de l'huile dans une turbomachine d'aéronef

Info

Publication number
EP4374057A1
EP4374057A1 EP22737904.7A EP22737904A EP4374057A1 EP 4374057 A1 EP4374057 A1 EP 4374057A1 EP 22737904 A EP22737904 A EP 22737904A EP 4374057 A1 EP4374057 A1 EP 4374057A1
Authority
EP
European Patent Office
Prior art keywords
heat exchanger
turbine engine
pressure compressor
intermediate support
aircraft
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.)
Pending
Application number
EP22737904.7A
Other languages
German (de)
English (en)
French (fr)
Inventor
Xavier Vandenplas
Bruno Servais
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 Aero Boosters SA
Original Assignee
Safran Aero Boosters 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 Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP4374057A1 publication Critical patent/EP4374057A1/fr
Pending legal-status Critical Current

Links

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
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • 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

Definitions

  • the present invention relates to a system for cooling oil in an aircraft turbine engine.
  • An object of the invention is to improve the integration of a heat exchanger for cooling the oil in an aircraft turbomachine.
  • the invention proposes a system for cooling oil in an aircraft turbomachine, and comprising an intermediate support casing intended to be located between a low-pressure compressor and a high-pressure compressor of the turbomachine. aircraft, and a heat exchanger intended to cool the oil by heat exchange with air; the heat exchanger being at least partially integrated into the intermediate support casing.
  • the heat exchanger comprises a primary stream surface configured to be in a primary stream of the aircraft turbomachine;
  • the primary stream surface is configured to be between the most downstream vane of the low pressure compressor, and the most upstream vane of the high pressure compressor;
  • the heat exchanger is configured to partially obstruct the primary vein
  • the heat exchanger comprises a secondary stream surface configured to be in a secondary stream of the aircraft turbomachine
  • the heat exchanger is configured to extend radially between the primary stream and a secondary stream, and includes a secondary stream surface configured to be in a secondary stream of the aircraft turbomachine;
  • the heat exchanger is configured to partially obstruct the secondary vein
  • the heat exchanger is annular and is configured to extend around an axis of the aircraft turbine engine
  • the heat exchanger comprises fins configured to extend radially and parallel to the axis of the aircraft turbomachine
  • the heat exchanger is a part fixed to the intermediate support casing, or the heat exchanger and the intermediate support casing are of the same part.
  • the invention further provides an aircraft turbine engine comprising such a system, a low pressure compressor and a high pressure compressor, the intermediate support casing being located between the low pressure compressor and the high pressure compressor.
  • the invention further proposes an aircraft comprising such a turbomachine.
  • FIG. 1 is a sectional view, along the axis, of an aircraft turbine engine comprising an example of a system according to the invention.
  • FIG. 1 illustrates an example of an aircraft turbomachine 100 comprising a system 1 for cooling oil according to one embodiment of the invention.
  • the aircraft turbomachine 100 is a dual-flow axial turbomachine comprising successively along the engine axis X, a fan 110, a low pressure compressor 120, a high pressure compressor 130, a combustion chamber 160, a high pressure turbine 140 and a low pressure turbine 150.
  • the fan 110 makes it possible to generate a flow of primary air in a primary stream 106 and a flow of secondary air in a secondary stream 107.
  • the aircraft turbomachine 100 comprises an inlet support casing 181 located downstream of the fan 110.
  • the inlet support casing 181 is provided with an annular sleeve defining the primary stream 106 and arms 183 structural elements that extend radially inward across primary vein 106.
  • the aircraft turbomachine 100 comprises an intermediate support casing 2 between the low 120 and high 130 pressure compressors.
  • the intermediate support casing 2 comprises an annular sleeve preferably having a gooseneck profile and delimiting the primary stream 106 between the low 120 and high 130 pressure compressors. It is also provided with structural arms 184 extending radially through the primary stream 106.
  • the system 1 according to the invention comprises an intermediate support casing 2, for example as illustrated in FIG. heat exchanger 3 at least partially integrated into the intermediate support casing 2.
  • the heat exchanger 3 has at least one surface in the primary stream 106 and/or in the secondary stream 107 (FIG. 1).
  • the heat exchanger 3 comprises a fluid inlet allowing oil to enter therein and a fluid outlet allowing oil to exit therefrom.
  • the heat exchanger 3 can be annular around the axis X of the turbomachine. [0017] The heat exchanger 3 can be a part attached to the intermediate support casing 2 or be integral with the intermediate support casing 2.
  • the heat exchanger 3 can be axially at the same level as the arms 184 structural.
  • the heat exchanger 3 passes radially through the intermediate support casing 2 and has a primary vein surface 31, radially internal, in the primary vein 106, and a vein surface secondary 32, radially external, in the secondary vein 107.
  • the primary stream surface 31 is downstream of the most downstream blade of the low pressure compressor 120, and upstream of the most upstream blade of the high pressure compressor 130.
  • the heat exchanger 3 may comprise fins extending radially and parallel to the axis of the turbomachine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP22737904.7A 2021-07-22 2022-07-05 Système pour refroidir de l'huile dans une turbomachine d'aéronef Pending EP4374057A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
BE20215572A BE1029619B1 (fr) 2021-07-22 2021-07-22 Système pour refroidir de l'huile dans une turbomachine d'aéronef
PCT/EP2022/068529 WO2023001538A1 (fr) 2021-07-22 2022-07-05 Système pour refroidir de l'huile dans une turbomachine d'aéronef

Publications (1)

Publication Number Publication Date
EP4374057A1 true EP4374057A1 (fr) 2024-05-29

Family

ID=77338439

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22737904.7A Pending EP4374057A1 (fr) 2021-07-22 2022-07-05 Système pour refroidir de l'huile dans une turbomachine d'aéronef

Country Status (5)

Country Link
US (1) US20240328354A1 (zh)
EP (1) EP4374057A1 (zh)
CN (1) CN117751234A (zh)
BE (1) BE1029619B1 (zh)
WO (1) WO2023001538A1 (zh)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2075194B1 (fr) * 2007-12-27 2017-08-16 Techspace Aero Echangeur de chaleur air-huile pour turboréacteur, turboréacteur associé et utilisation dudit échangeur
FR3016956B1 (fr) * 2014-01-29 2019-04-19 Safran Aircraft Engines Echangeur de chaleur d'une turbomachine
US10107200B2 (en) * 2015-04-30 2018-10-23 General Electric Company Turbine engine thermal management
FR3046199B1 (fr) * 2015-12-23 2017-12-29 Snecma Turbomachine comprenant un echangeur air-huile surfacique integre a un compartiment inter-veines
BE1024935B1 (fr) * 2017-01-26 2018-08-27 Safran Aero Boosters S.A. Compresseur avec virole interne segmentee pour turbomachine axiale

Also Published As

Publication number Publication date
BE1029619A1 (fr) 2023-02-14
BE1029619B1 (fr) 2023-02-20
US20240328354A1 (en) 2024-10-03
CN117751234A (zh) 2024-03-22
WO2023001538A1 (fr) 2023-01-26

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