Cooling of the oil circuit of a turbine engine

Patent metadata

Field	Value
Publication number	US-2018094584-A1
Application number	US-201615563257-A
Country	US
Kind code	A1
Filing date	Apr 1, 2016
Priority date	Apr 3, 2015
Publication date	Apr 5, 2018
Grant date	—

Abstract

The invention relates to a turbine engine, such as a turbojet engine or a turboprop engine of an aeroplane, including at least one oil circuit ( 8 ) and cooling means ( 16 ) for cooling the oil of said circuit ( 8 ), the cooling means ( 16 ) including a refrigerant circuit ( 17 ) provided with a first heat exchanger ( 18 ) capable of exchanging heat between the refrigerant and the air and forming a condenser, a second heat exchanger ( 19 ) capable of exchanging heat between the refrigerant and the oil of the oil circuit and forming an evaporator, a pressure reducer ( 20 ), a compressor ( 21 ) and first regulator means ( 31 ) capable of regulating the pressure of the refrigerant entering the first exchanger ( 18 ).

First claim

1 . A turbine engine comprising:
at least one oil circuit and cooling means for cooling oil of said oil circuit, the cooling means including a refrigerant circuit provided with a first heat exchanger for exchanging heat between a refrigerant and air and forming a condenser, a second heat exchanger for exchanging heat between the refrigerant and the oil of the oil circuit and forming an evaporator, a pressure reducer mounted downstream from the first heat exchanger and upstream from the second heat exchanger, in a refrigerant flow direction, and a compressor mounted downstream from the second heat exchanger and upstream from the first heat exchanger, wherein the cooling means include first regulator means for regulating a pressure of the refrigerant entering the first heat exchanger.

2 . The turbine engine according to claim 1 , further comprising second regulator means for regulating a flow of refrigerant entering the first heat exchanger.

3 . The turbine engine according to claim 1 , wherein the compressor is a supercharger comprising rotors formed by rotary screws.

4 . The turbine engine according to claim 3 , wherein the first regulator means include a mobile slide having an adjustable position relative to the rotors of the compressor, the pressure of the refrigerant at an outlet of the compressor being dependent on the position of said slide, the first regulator means including means for controlling the position of said mobile slide.

5 . The turbine engine according to claim 3 , wherein the second regulator means include means for controlling a speed of rotation of the rotors of the compressor.

6 . The turbine engine according to claim 1 , wherein the compressor is a centrifugal compressor including a rotor, wherein a speed of rotation of the rotor determines a pressure of the refrigerant at an outlet of the compressor.

7 . The turbine engine according to claim 6 , wherein the first regulator means include means for controlling the speed of rotation of the rotor.

8 . The turbine engine according to claim 6 , wherein the second regulator means include a variable-section diaphragm located downstream from said centrifugal compressor, and means for controlling the variable-section diaphragm.

9 . The turbine engine according to claim 5 , wherein the means for controlling the speed of rotation of at least one rotor of the compressor comprise an electric motor controlled by a computer.

10 . The turbine engine according to claim 2 , comprising computing means for determining at least one of:
a necessary speed of rotation of the rotary screws of the supercharger; a necessary speed of rotation of a rotor of a centrifugal compressor; a necessary section of a variable-section diaphragm; and a necessary position of a mobile slide of a twin-screw supercharger, as a function of at least one of: at least one input parameter, including at least one of a temperature of the air outside the turbine engine, a characteristic of the compressor, a temperature of the oil at one point of the oil circuit, a speed of rotation of the rotor, a speed of rotation of the rotary screws of the compressor, a section of the variable-section diaphragm, and a position of the mobile slide; an oil temperature of oil in the oil circuit; and a mathematical model of the cooling means.

11 . A cooling system for cooling a fluid of a hot fluid circuit of an aircraft turbine engine comprising:
a refrigerant circuit having:
a first heat exchanger forming a condenser for exchanging heat between a refrigerant and air;
a second heat exchanger forming an evaporator for exchanging heat between the refrigerant and the fluid of the hot-fluid circuit;
a compressor mounted downstream from the second heat exchanger and upstream from the first heat exchanger, in a refrigerant flow direction; and
a pressure reducer mounted downstream from the first heat exchanger and upstream from the second heat exchanger; and
first regulator means for regulating a pressure of the refrigerant entering the first heat exchanger, the fluid of the hot fluid circuit being oil for lubricating systems of the aircraft turbine engine.

12 . (canceled)

13 . (canceled)

14 . The cooling system according to claim 11 , wherein the pressure reducer is built into a duct of the refrigerant circuit, said duct connecting the first heat exchanger to the second heat exchanger, and wherein the pressure reducer is formed by a local narrowing of a flow area of the duct.

Assignees

• Safran Aircraft Engines

Inventors

• Chalaud Sebastien

Classifications

• F04C18/16

  with helical teeth, e.g. chevron-shaped, screw type {(for non-parallel axes of movement F04C18/48)} · CPC title

• F04C25/00

  Adaptations of pumps for special use of pumps for elastic fluids · CPC title

• F04C28/125

  with sliding valves controlled by the use of fluid other than the working fluid · CPC title

• F04C2270/80

  Diagnostics · CPC title

• F04C23/005

  of dissimilar working principle · CPC title