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
  • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
• • 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 turbomachine can be double-flow, in which case it comprises a primary stream and a secondary stream.
• the turbomachine can be triple flow, in which case it comprises a primary stream, a secondary stream and a tertiary stream.
• it may comprise one or more of the following characteristics, taken in isolation or according to all possible technical combinations:
• 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 stream
• 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 comprises a tertiary stream surface configured to be in a tertiary stream of the aircraft turbomachine;
• the heat exchanger is configured to partially obstruct the tertiary 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. 2 is a sectional view, along the axis, of another aircraft turbine engine comprising another 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 primary air flow in a primary stream 106 and a secondary air flow 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 vein 106.
• Figure 2 schematically illustrates the respective positions of the low 120 and high 130 pressure compressors, of the intermediate support casing 2, of the primary stream 106, and of a tertiary stream 108 in the case of a triple turbomachine flux.
• the system 1 comprises an intermediate support casing 2, for example as shown in Figure 1 or in Figure 2, and a heat exchanger 3 at least partially integrated into the casing of intermediate support 2.
• the heat exchanger 3 has at least one surface in the primary stream 106 and/or in the secondary stream 107 (FIG. 1) and/or in the tertiary stream 108 (FIG. 2).
• 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.
• 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 structural arms 184.
• 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 outer, in the secondary stream 107.
• the primary stream surface 31 is downstream of the blade furthest downstream of the low-pressure compressor 120, and upstream of the blade furthest upstream of the high pressure compressor 130.
• the heat exchanger 3 has a tertiary stream surface 33 in the tertiary stream 108. It partially obstructs the tertiary stream 108. It comprises fins 34 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)

Applications Claiming Priority (1)

Publications (1)

Family

ID=77300887

Family Applications (1)

Country Status (3)

Family Cites Families (4)

• 2021
  • 2021-07-22 CN CN202180100850.7A patent/CN117751233A/zh active Pending
  • 2021-07-22 WO PCT/EP2021/070617 patent/WO2023001379A1/fr active Application Filing
  • 2021-07-22 EP EP21752650.8A patent/EP4374056A1/fr active Pending

Also Published As

Similar Documents

Legal Events