Hydraulic and pneumatic control circuit having a fuel/air heat exchanger for a turbojet

Abstract

A hydraulic and pneumatic control circuit for a turbojet, a main hydraulic line having an oil/fuel heat exchanger with a function of transferring heat from the oil flowing in an oil circuit of the turbojet to the fuel flowing in the main hydraulic line, the circuit having a first hydraulic line for feeding fuel to a combustion chamber of the turbojet, a second hydraulic line for feeding fuel to one or more actuators for controlling variable geometry equipment, each actuator being fed with fuel via an electrohydraulic servovalve, a pneumatic line for feeding air to a pneumatic control member for bleed valves of a compressor and a blade tip clearance control valve of a turbine of the turbojet, and a fuel/air heat exchanger positioned on the second hydraulic line upstream from the hydraulic servovalve and on the pneumatic line upstream from the pneumatic control member.

Claims

1. A hydraulic and pneumatic control circuit for a turbojet, the hydraulic and pneumatic control circuit comprising: a main hydraulic line having an oil/fuel heat exchanger with a function of transferring heat from oil flowing in an oil circuit of the turbojet to fuel flowing in the main hydraulic line; a first hydraulic line for feeding the fuel to a combustion chamber of the turbojet; a second hydraulic line for feeding the fuel to one or more hydraulic actuators serving to control variable geometry equipment of the turbojet, each hydraulic actuator of the one or more hydraulic actuators being fed with the fuel via an electrohydraulic servovalve; a pneumatic line for feeding air to a pneumatic control member for bleed valves of a high pressure compressor of the turbojet and a blade tip clearance control valve of a turbine of the turbojet, the air flowing in the pneumatic line being bled from the high pressure compressor of the turbojet; and a fuel/air heat exchanger positioned on the second hydraulic line upstream from the electrohydraulic servovalve and on the pneumatic line upstream from the pneumatic control member in order to transfer heat from the air flowing in the pneumatic line to the fuel flowing in the second hydraulic line, wherein the oil/fuel heat exchanger does not have a function of transferring heat between the oil flowing in the oil circuit of the turbojet and the fuel flowing in the second hydraulic line, and wherein the pneumatic line further comprises, downstream from the fuel/air heat exchanger, a member for reducing a pressure of engine enclosures for a purpose of adjusting a flow rate of the air passing through the fuel/air heat exchanger, the member and the pneumatic control member being arranged parallel to each other downstream of the fuel/air heat exchanger.

2. The hydraulic and pneumatic circuit according to claim 1, wherein the member for reducing the pressure comprises a jet pump.

3. The hydraulic and pneumatic circuit according to claim 1, wherein the first and second hydraulic lines are connected to each other upstream from the combustion chamber and the one or more hydraulic actuators in order to form the main hydraulic line that also includes a positive displacement pump.

4. The hydraulic and pneumatic circuit according to claim 1, wherein the main hydraulic line further comprises a low-pressure pump positioned upstream from the oil/fuel heat exchanger and downstream from a fuel tank.

5. A turbojet comprising: a hydraulic and pneumatic control circuit including a main hydraulic line having an oil/fuel heat exchanger with a function of transferring heat from oil flowing in an oil circuit of the turbojet to fuel flowing in the main hydraulic line; a first hydraulic line for feeding the fuel to a combustion chamber of the turbojet; a second hydraulic line for feeding the fuel to one or more hydraulic actuators serving to control variable geometry equipment of the turbojet, each hydraulic actuator of the one or more hydraulic actuators being fed with the fuel via an electrohydraulic servovalve; a pneumatic line for feeding air to a pneumatic control member for bleed valves of a high pressure compressor of the turbojet and a blade tip clearance control valve of a turbine of the turbojet, the air flowing in the pneumatic line being bled from the high pressure compressor of the turbojet, and a fuel/air heat exchanger positioned on the second hydraulic line upstream from the electrohydraulic servovalve and on the pneumatic line upstream from the pneumatic control member in order to transfer heat from the air flowing in the pneumatic line to the fuel flowing in the second hydraulic line, wherein the oil/fuel heat exchanger does not have a function of transferring heat between the oil flowing in the oil circuit of the turbojet and the fuel flowing in the second hydraulic line, and wherein the pneumatic line further comprises, downstream from the fuel/air heat exchanger, a member for reducing a pressure of engine enclosures for a purpose of adjusting a flow rate of the air passing through the fuel/air heat exchanger, the member and the pneumatic control member being arranged parallel to each other downstream of the fuel/air heat exchanger.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Other characteristics and advantages of the present invention appear from the following description made with reference to the accompanying drawings which show an embodiment having no limiting character. In the figures:

(2) FIG. 1 is a diagrammatic view of a hydraulic control circuit of the invention; and

(3) FIG. 2 is a diagrammatic view of a pneumatic control circuit of the invention.

DETAILED DESCRIPTION OF THE INVENTION

(4) With reference to FIG. 1, there follows a description of the hydraulic control circuit of the invention for a turbojet.

(5) The hydraulic control circuit 2 has includes a main hydraulic line 4. From upstream to downstream in the flow direction of fuel, this control line comprises a low-pressure pump 6 connected upstream to a fuel tank 8, a main fuel filter 10, and a high-pressure positive displacement pump 12.

(6) Downstream from the high-pressure pump 12, the main hydraulic line splits into two distinct fuel lines, namely: a first hydraulic line 14 for feeding fuel to injector systems 16 for injecting fuel into a combustion chamber of the turbojet; and a second hydraulic line 18 for feeding fuel to one or more hydraulic actuators 20, 22 for controlling variable geometry equipment of the turbojet.

(7) More precisely, the first hydraulic line 14 includes a metering member 24 (referred to as a fuel metering valve (FMV)) for controlling the rate at which fuel is injected into the combustion chamber of the turbine engine via the fuel injector systems 16, and a high-pressure shutoff valve (HPSOV) 26 for shutting off the flow of fuel in the event of the turbine engine overspeeding. Each member 24 or 26 is actuated by a dedicated electrohydraulic servovalve (EHSV) 33.

(8) Excess fuel in the first hydraulic line is returned upstream from the main fuel filter 10 via a return loop 28 fed by a bypass valve 30.

(9) The second hydraulic line 18 also includes electrohydraulic servovalves 32, each of which is used for delivering a flow of fuel to one or the other of the chambers of a hydraulic actuator 20, 22.

(10) These servovalves 32 are controlled electrically by the ECU of the turbojet. Such a control unit is itself well known: it serves to control various pieces of equipment that are associated with the turbine engine. The fuel leaving the servovalves 32 returns to the main hydraulic line 4 between the main fuel filter 10 and the high-pressure pump 12 via a return loop 34.

(11) The hydraulic control circuit 2 also includes an oil/fuel heat exchanger 36 (referred to as a fuel cooled oil cooler (FCOC)) that has a main function of transferring heat for the purpose firstly of cooling the oil of the oil circuit of the turbojet under hot conditions, and secondly of heating the fuel under cold conditions.

(12) This main heat transfer function is performed by a fuel/oil heat exchanger 38 interposed in the main hydraulic line 4 between the low-pressure pump 6 and the main fuel filter 10 in order to cool the lubricating oil of the turbojet by exchanging heat with the fuel through a heat exchange surface between those two fluids, thereby having the consequence of heating the fuel and cooling the oil.

(13) It may be observed that in the invention the oil/fuel heat exchanger 36 does not have a servo fuel heater (SFH) function for heating the fuel flowing in the second hydraulic line 18 by means of the hot oil following in the oil circuit of the turbojet (not shown in the figures).

(14) Instead, the hydraulic control circuit 2 of the invention has a fuel/air heat exchanger 40 that is positioned in the second hydraulic line 18 upstream from the electrohydraulic servovalve 32 in order to transfer heat from the air flowing in the pneumatic line (described below) to the fuel flowing in the second hydraulic line.

(15) This fuel/air heat exchanger 40 is a cooler/heater that transfers heat from its hot source (specifically the air feeding this pneumatic control member) to its cold source (specifically the fuel feeding the electrohydraulic servovalves). It is referred to as a fuel cooled air cooler (FCAC).

(16) By way of example, this fuel/air heat exchanger 40 has one portion that is fed with fuel and another portion that is fed with air. Heat may be transferred between the air and the oil via an architecture of “plate” type or else of “tube” type, both of these architectures being well known and depending on the characteristics of the circuits in terms of flow rates and temperatures.

(17) With reference to FIG. 2, there follows a description of the pneumatic control circuit 42 of the turbojet of the invention. The term “hydraulic and pneumatic control circuit” is used to cover the combination of the hydraulic control circuit 2 and the pneumatic control circuit 42.

(18) This pneumatic control circuit 42 comprises in particular a pneumatic line 44 for feeding a pneumatic control member 46 with air, this member serving to control a plurality of bleed valves 48 of a compressor of the turbojet, and a valve 50 for adjusting blade tip clearance of a turbine of the turbojet.

(19) More precisely, the air flowing in the pneumatic line 44 is taken from a stage of the high-pressure compressor of the turbojet.

(20) Furthermore, the pneumatic control member 46 is controlled electrically by the ECU of the turbojet and contains a plurality of electrically controlled valves (not shown), each feeding one of the valves 48, 50, which valves present on/off type operation.

(21) In the invention, the above-described fuel/air heat exchanger 40 is also positioned on the pneumatic line 44 upstream from the pneumatic control member 46. Thus, this fuel/air heat exchanger 40 serves to cool the air taken from the high-pressure compressor of the turbojet before it is fed to the pneumatic control member 46, while also heating the fuel flowing in the second hydraulic line of the hydraulic circuit before it is fed to the electrohydraulic servovalves.

(22) The pneumatic line 44 of the pneumatic circuit preferably also includes, downstream from the fuel/air heat exchanger 40, a member 52 for reducing the pressure of engine enclosures in order to adjust the flow rate of air passing through the fuel/air heat exchanger.

(23) Typically, this pressure-reducing member 52 comprises a jet pump using a permanent flow for reducing the pressure of the engine enclosures, thereby making it easy to determine the design dimensions of the fuel/air heat exchanger.

(24) The oil circuit of the turbojet is not described herein. Typically, such an oil circuit serves mainly to cool and lubricate elements of the turbojet. When implementing the invention, the oil circuit differs from the prior art in that the oil/fuel heat exchanger does not have the SFH function of heating the fuel flowing in the second hydraulic line by means of the hot oil flowing in the oil circuit.