FR3093765B1 - OPTIMIZED TURBOMACHINE AIR-OIL HEAT EXCHANGER SYSTEM - Google Patents

OPTIMIZED TURBOMACHINE AIR-OIL HEAT EXCHANGER SYSTEM Download PDF

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Publication number
FR3093765B1
FR3093765B1 FR1902532A FR1902532A FR3093765B1 FR 3093765 B1 FR3093765 B1 FR 3093765B1 FR 1902532 A FR1902532 A FR 1902532A FR 1902532 A FR1902532 A FR 1902532A FR 3093765 B1 FR3093765 B1 FR 3093765B1
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FR
France
Prior art keywords
heat exchanger
exchanger system
optimized
duct
turbomachine
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
FR1902532A
Other languages
French (fr)
Other versions
FR3093765A1 (en
Inventor
Gabriela Philippart
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
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 filed Critical Safran Aircraft Engines SAS
Priority to FR1902532A priority Critical patent/FR3093765B1/en
Publication of FR3093765A1 publication Critical patent/FR3093765A1/en
Application granted granted Critical
Publication of FR3093765B1 publication Critical patent/FR3093765B1/en
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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
    • F02C7/12—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
    • F02C7/14—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
    • 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
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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

Abstract

L'invention concerne un système échangeur de chaleur (17) d’une turbomachine (1) comprenant un compartiment moteur (14) dans lequel circule de l’huile (H), ce compartiment moteur (14) comprenant un carter (15) délimitant une veine secondaire (13) de la turbomachine (1), caractérisée en ce que le système échangeur de chaleur (17) comporte un conduit (18) qui est ménagé dans le compartiment moteur (14), ce conduit s’étendant depuis une ouverture d’aspiration (19) formée au niveau du carter (15) pour prélever de l’air (Fp) depuis la veine secondaire (13) pour circuler dans le conduit (18), le conduit étant délimité par au moins une paroi (27, 47) séparant l’air prélevée (Fp) de l’huile (H) pour établir un échange thermique entre l’air prélevé (Fp) et l’huile (H) à travers ladite au moins une paroi (27, 47). Figure pour l’abrégé : Figure 2The invention relates to a heat exchanger system (17) for a turbomachine (1) comprising an engine compartment (14) in which oil (H) circulates, this engine compartment (14) comprising a casing (15) delimiting a secondary stream (13) of the turbomachine (1), characterized in that the heat exchanger system (17) comprises a duct (18) which is formed in the engine compartment (14), this duct extending from an opening suction (19) formed at the level of the housing (15) to take air (Fp) from the secondary stream (13) to circulate in the duct (18), the duct being delimited by at least one wall (27 , 47) separating the air taken (Fp) from the oil (H) to establish a heat exchange between the air taken (Fp) and the oil (H) through said at least one wall (27, 47) . Figure for the abstract: Figure 2

FR1902532A 2019-03-12 2019-03-12 OPTIMIZED TURBOMACHINE AIR-OIL HEAT EXCHANGER SYSTEM Active FR3093765B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1902532A FR3093765B1 (en) 2019-03-12 2019-03-12 OPTIMIZED TURBOMACHINE AIR-OIL HEAT EXCHANGER SYSTEM

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1902532A FR3093765B1 (en) 2019-03-12 2019-03-12 OPTIMIZED TURBOMACHINE AIR-OIL HEAT EXCHANGER SYSTEM
FR1902532 2019-03-12

Publications (2)

Publication Number Publication Date
FR3093765A1 FR3093765A1 (en) 2020-09-18
FR3093765B1 true FR3093765B1 (en) 2021-05-14

Family

ID=66776635

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1902532A Active FR3093765B1 (en) 2019-03-12 2019-03-12 OPTIMIZED TURBOMACHINE AIR-OIL HEAT EXCHANGER SYSTEM

Country Status (1)

Country Link
FR (1) FR3093765B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2336525B1 (en) * 2009-12-21 2015-08-26 Techspace Aero S.A. Integration of an air-liquid heat exchanger on an engine
EP2472067B1 (en) * 2010-12-31 2013-09-25 Techspace Aero S.A. Integration of a surface heat exchanger with controlled air flow in an airplane engine
US10323540B2 (en) * 2015-12-07 2019-06-18 General Electric Company Gas turbine engine fluid cooling systems and methods of assembling the same
FR3044636B1 (en) * 2015-12-08 2019-08-30 Safran Aircraft Engines AIRCRAFT TURBOMACHINE EQUIPPED WITH AIR-OIL SURFACE HEAT EXCHANGER

Also Published As

Publication number Publication date
FR3093765A1 (en) 2020-09-18

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