FR3103221B1 - SURFACE AIR-OIL HEAT EXCHANGER FOR DOUBLE-FLOW TURBOMACHINE COMPRISING FINS WITH A LEADING EDGE OFFSET DOWNSTREAM IN AN AXIAL AIR FLOW DIRECTION - Google Patents

SURFACE AIR-OIL HEAT EXCHANGER FOR DOUBLE-FLOW TURBOMACHINE COMPRISING FINS WITH A LEADING EDGE OFFSET DOWNSTREAM IN AN AXIAL AIR FLOW DIRECTION Download PDF

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Publication number
FR3103221B1
FR3103221B1 FR1912731A FR1912731A FR3103221B1 FR 3103221 B1 FR3103221 B1 FR 3103221B1 FR 1912731 A FR1912731 A FR 1912731A FR 1912731 A FR1912731 A FR 1912731A FR 3103221 B1 FR3103221 B1 FR 3103221B1
Authority
FR
France
Prior art keywords
fins
turbomachine
heat exchanger
leading edge
double
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
FR1912731A
Other languages
French (fr)
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FR3103221A1 (en
Inventor
Xavier Garnaud
Alexandre Couilleaux
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
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Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1912731A priority Critical patent/FR3103221B1/en
Publication of FR3103221A1 publication Critical patent/FR3103221A1/en
Application granted granted Critical
Publication of FR3103221B1 publication Critical patent/FR3103221B1/en
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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
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/115—Heating the by-pass flow by means of indirect heat exchange
    • 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

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)

Abstract

L’invention concerne un échangeur de chaleur air-huile surfacique (10) pour turbomachine à double flux, comprenant :- une paroi annulaire comprenant une première surface annulaire destinée à recevoir de la chaleur provenant d’huile d’un circuit d’huile de la turbomachine, et une deuxième surface (14) annulaire opposée destinée à délimiter radialement une veine secondaire de la turbomachine,- une pluralité d’ailettes (12) s’étendant radialement depuis la deuxième surface (14) et réparties en une rangée circonférentielle, chacune des ailettes (12) s’étendant, d’amont en aval dans une direction axiale d’écoulement de l’air, entre un bord d’attaque (16) et un bord de fuite (17), les bords d’attaque (16) d’ailettes (12) d’un ensemble de référence (12R) étant alignés circonférentiellement entre eux et les bords d’attaque (16) d’ailettes (12) d’un premier ensemble (121) étant alignés circonférentiellement entre eux et décalés axialement vers l’aval par rapport aux bords d’attaque (16) des ailettes (12) de l’ensemble de référence (12R). Figure pour l’abrégé : Figure 4The invention relates to a surface air-oil heat exchanger (10) for a turbofan engine, comprising:- an annular wall comprising a first annular surface intended to receive heat coming from oil from a the turbomachine, and a second opposite annular surface (14) intended to radially delimit a secondary stream of the turbomachine,- a plurality of fins (12) extending radially from the second surface (14) and distributed in a circumferential row, each of the fins (12) extending, from upstream to downstream in an axial airflow direction, between a leading edge (16) and a trailing edge (17), the leading edges (16) of fins (12) of a reference set (12R) being aligned circumferentially between them and the leading edges (16) of fins (12) of a first set (121) being aligned circumferentially between them and offset axially downstream relative to the leading edges (16) of the wings ettes (12) of the reference set (12R). Figure for abstract: Figure 4

FR1912731A 2019-11-14 2019-11-14 SURFACE AIR-OIL HEAT EXCHANGER FOR DOUBLE-FLOW TURBOMACHINE COMPRISING FINS WITH A LEADING EDGE OFFSET DOWNSTREAM IN AN AXIAL AIR FLOW DIRECTION Active FR3103221B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1912731A FR3103221B1 (en) 2019-11-14 2019-11-14 SURFACE AIR-OIL HEAT EXCHANGER FOR DOUBLE-FLOW TURBOMACHINE COMPRISING FINS WITH A LEADING EDGE OFFSET DOWNSTREAM IN AN AXIAL AIR FLOW DIRECTION

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1912731A FR3103221B1 (en) 2019-11-14 2019-11-14 SURFACE AIR-OIL HEAT EXCHANGER FOR DOUBLE-FLOW TURBOMACHINE COMPRISING FINS WITH A LEADING EDGE OFFSET DOWNSTREAM IN AN AXIAL AIR FLOW DIRECTION
FR1912731 2019-11-14

Publications (2)

Publication Number Publication Date
FR3103221A1 FR3103221A1 (en) 2021-05-21
FR3103221B1 true FR3103221B1 (en) 2022-06-17

Family

ID=69468876

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1912731A Active FR3103221B1 (en) 2019-11-14 2019-11-14 SURFACE AIR-OIL HEAT EXCHANGER FOR DOUBLE-FLOW TURBOMACHINE COMPRISING FINS WITH A LEADING EDGE OFFSET DOWNSTREAM IN AN AXIAL AIR FLOW DIRECTION

Country Status (1)

Country Link
FR (1) FR3103221B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE1030462B1 (en) * 2022-04-20 2023-11-20 Safran Aero Boosters AIR-OIL HEAT EXCHANGER

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001332883A (en) * 2000-05-22 2001-11-30 Mitsubishi Electric Corp On-vehicle cooling device with no refrigerant
US9051943B2 (en) * 2010-11-04 2015-06-09 Hamilton Sundstrand Corporation Gas turbine engine heat exchanger fins with periodic gaps
FR3015654B1 (en) * 2013-12-23 2015-12-04 Snecma HEAT EXCHANGER OF A TURBOMACHINE
FR3047270B1 (en) * 2016-01-29 2019-03-29 Safran Aircraft Engines SURFACE HEAT EXCHANGER AND ACOUSTIC TREATMENT

Also Published As

Publication number Publication date
FR3103221A1 (en) 2021-05-21

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