Device for cooling oil for a turbine engine

Abstract

The invention relates to a device (11) for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a duct (12) for circulating a flow of cold air (F.sub.1), means (16) for injecting oil into the duct, and means (19) for extracting the oil mixed with the flow of cold air (F.sub.1), located in the duct (12), downstream from the injection means (16).

Claims

1. An oil cooling device for a turbine engine, the oil cooling device comprising: a duct for circulation of an air flow; means for injecting oil inside the duct; and means for extracting oil mixed with the air flow, situated in the duct, downstream of the injection means, wherein the air flow has a temperature cooler than the oil, wherein the means for extracting oil comprise a rotary oil separator, and wherein the duct is equipped with a turbine upstream of the means for injecting oil, the turbine comprising a shaft intended to be rotated by passage of the air flow through the turbine and rotationally coupled to the rotary oil separator.

2. The oil cooling device according to claim 1, wherein the means for injecting oil comprise an injection nozzle able to atomise the oil so as to form droplets of oil with dimensions between 1 and 5 ?m.

3. The oil cooling device according to claim 1, further comprising an oil inlet conduit connected to the means for injecting oil and an oil extraction conduit connected to the means for extracting oil, said oil inlet and extraction conduits being connected by a bypass conduit comprising at least one of a flap and a valve able to open in an event of overpressure at the oil inlet conduit.

4. The oil cooling device according to claim 1, wherein the means for extracting oil comprise a body made from metal foam.

5. A method for cooling oil in a turbine engine, by means of a device according to claim 1, comprising the steps of: circulating the air flow inside the duct, injecting oil into said duct using said means for injecting oil, so as to mix the oil and air and thus promote the cooling of the oil by the air, and separating the oil from the air so as to extract the oil contained in said mixture, using the means for extracting oil.

6. A turbine engine comprising, from upstream to downstream in a direction of flow of gases: a fan; a low-pressure compressor; a high-pressure compressor; a combustion chamber; a high-pressure turbine; a low-pressure turbine; and a gas exhaust pipe; an oil cooling device comprising a duct for circulation of an air flow, means for injecting oil inside the duct, and means for extracting oil mixed with the air flow, situated in the duct, downstream of the means for injecting oil; and means for taking of air in a zone situated downstream of the fan and upstream of the high-pressure compressor, able to supply the gas exhaust pipe with air issuing from said zone, wherein the air has a temperature cooler than the oil, and wherein the low-pressure compressor is rotationally coupled to the low-pressure turbine by means of a first shaft, the high-pressure compressor being rotationally coupled to the high-pressure turbine by means of a second shaft coaxial with the first shaft and mounted inside the latter, the upstream end of the first shaft being equipped with a bearing situated in an enclosure, the air issuing from the duct emerging in said enclosure.

Description

(1) The invention will be better understood and other details, features and advantages of the invention will emerge from a reading of the following description given by way of non-limitative example with reference to the accompanying drawings, in which:

(2) FIG. 1 is a view in axial section of a turbine engine of the prior art,

(3) FIG. 2 is a schematic view of an oil cooling device of a turbine engine, in accordance with the invention.

(4) FIG. 1 depicts an aircraft turbine engine 1 of the prior art, comprising, from upstream to downstream in the direction of flow of the gases, a fan 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, a low-pressure turbine 7, and a gas exhaust pipe (not shown).

(5) The low-pressure compressor 3 is rotationally coupled to the low-pressure turbine 7 by means of a first shaft 8, the high-pressure compressor 4 being rotationally coupled to the high-pressure turbine 6 by means of a second shaft (not shown) coaxial with the first shaft 8 and mounted inside the latter. The upstream end of the first shaft 8 is equipped with a bearing of the ball bearing type 9, situated in a ventilated enclosure 10.

(6) As indicated previously, the various components and items of equipment of the turbine engine 1 must be lubricated or cooled by means of an oil circuit, the heat generated and transported by the oil being discharged by means of an oil cooling device.

(7) FIG. 2 illustrates an oil cooling device 11 according to one embodiment of the invention, comprising a duct 12 for circulation of a cold air flow F.sub.1. The upstream end 13 of the duct 12 is supplied with cold air by means for taking off air in a zone situated downstream of the fan 2 and upstream of the high-pressure compressor 4. The downstream end of the 14 of the pipe 12 emerges in the ventilated enclosure 10.

(8) The duct 12 comprises, from upstream to downstream, in the direction of circulation of the cold air flow F.sub.1, a turbine 15, an oil injection nozzle 16 able to atomise droplets of oil 17 in the duct and thus to form an air/oil mixture 18, and a rotary oil separator 19 able to separate the oil 20 from said mixture 18. The oil separator 19 is rotated by a shaft 21 driven by the turbine 15. The oil separator 19 may comprise a body made from metal foam in order to further improve its efficiency.

(9) The device 11 according to the invention also comprises an oil inlet conduit 22 supplying the nozzle 16 and an oil extraction conduit 23 connected to the rotary oil separator 19, said oil inlet and extraction conduits 22, 23 being connected by a bypass conduit 24 comprising a non-return valve 25 or a valve able to open in the event of overpressure at the oil inlet conduit 22.

(10) It should be noted that such a device may be contained in a single item of equipment without any kinematic connection with the rest of the turbine 1, which facilitates installation thereof.

(11) The functioning of such a device 11 will now be described in detail.

(12) Air is taken off in the zone situated downstream of the fan 2 and upstream of the high-pressure compressor 4. This air is then expanded by passing through the turbine 15. The latter drives the shaft 21 as well as the rotary oil separator 19. The nozzle 16 atomises fine droplets of oil 17, the dimensions of which are for example between 1 and 5 ?m, in the air, so as to form a relatively homogeneous air/oil mixture 18. The oil droplets are then cooled by the air until they reach an exit temperature Ths theoretically equal to
(Th)s=[(Th)e?(Ta)e)]/[(Da.Math.(cp)a+Dh.Math.cph], with:

(13) (Th)s: Oil exit temperature

(14) (Th)e: Oil entry temperature

(15) (Ta)e: Air entry temperature

(16) Da: Mass flow rate of air

(17) (cp)a: Specific heat of the air

(18) Dh: Mass flow rate of oil

(19) (cp)h: Specific heat of the oil.

(20) A major part of the oil 20 is then extracted to the extraction conduit 23, by means of the rotary oil separator 19. A small part of the oil is however carried away with the air flow to the enclosure 10, where the oil can benefit from a second extraction pass, facilitating the grouping together of the droplets (increase in their size and trickling) by coalescence effect.

(21) Such a device 11 therefore makes it possible to effectively cool the oil used for the lubrication of the various components of the turbine engine 1 and also has relatively low mass and overall size, having regard to its performances.