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CN-121986211-A - Aircraft turbine engine comprising a heat pump

CN121986211ACN 121986211 ACN121986211 ACN 121986211ACN-121986211-A

Abstract

An aircraft turbine engine comprising-a fuel supply system (12) for supplying fuel to a combustion chamber of the turbine engine, -a heat pump (15) comprising a closed circuit (20) in which a heat transfer fluid circulates, the circuit (20) comprising an evaporator (21) configured to exchange heat with oil of the turbine engine, a first condenser (22) configured to exchange heat with the fuel of the supply system (12), a second condenser (23) mounted in parallel with the first condenser (22) and configured to exchange heat with a cold source (24) different from the fuel, an expansion valve (25) configured to expand the heat transfer fluid before it enters the evaporator (21), a compressor (26) configured to compress the heat transfer fluid before it enters the condensers (22, 23), and a metering device (27) configured to regulate the flow of the heat transfer fluid into the first condenser (22).

Inventors

  • Fabian Irina Lhasa Tower
  • Fran ç ois Luc Michele. Rousseau
  • Mohammed Lamine butaleb

Assignees

  • 赛峰飞机发动机公司

Dates

Publication Date
20260505
Application Date
20241008
Priority Date
20231013

Claims (10)

  1. 1. A turbine engine (1) for an aircraft (2), the turbine engine comprising: -a system (12) for supplying fuel to a combustion chamber (10) of the turbine engine (1); -a heat pump (15) comprising a closed circuit (20) in which a heat transfer fluid circulates, the circuit (20) comprising an evaporator (21) configured to exchange heat with the oil of the turbine engine (1), a first condenser (22) configured to exchange heat with the fuel of the supply system (12), a second condenser (23) mounted in parallel with the first condenser (22) and configured to exchange heat with a cold source (24) different from the fuel, an expansion valve (25) configured to expand the heat transfer fluid before entering the evaporator (21), a compressor (26) configured to compress the heat transfer fluid before the heat transfer fluid enters the condensers (22, 23), and a metering device (27) configured to regulate the flow of the heat transfer fluid entering the first condenser (22).
  2. 2. Turbine engine (1) according to the preceding claim, wherein said metering device (27) is electrically controlled by a control system (30).
  3. 3. Turbine engine (1) according to the preceding claim, wherein the supply system (12) comprises a fuel circuit in heat exchange with the first condenser (22) and a fuel temperature sensor (31) located in the fuel circuit downstream of the first condenser (22) and electrically connected to the control system (30).
  4. 4. Turbine engine (1) according to any one of the preceding claims, wherein the first condenser (22) forms part of a first branch (32) of the circuit (20), the second condenser (23) forms part of a second branch (33) of the circuit (20), the circuit (20) comprising a common part (34) comprising at least the evaporator (21), the inputs of the branches (32, 33) being each connected to an output path of the metering device (27), the output of the common part (34) being connected to an input path of the metering device (27).
  5. 5. A turbine engine (1) according to any one of claims 1 to 3, characterized in that the first condenser (22) and the metering device (27) form part of a first branch (32) of the circuit (20), the second condenser (23) forms part of a second branch (33) of the circuit (20), the circuit (20) comprises a common part (34) comprising at least the evaporator (21), the inputs of the branches (32, 33) being connected to the output of the common part (34) via a junction (35).
  6. 6. Turbine engine (1) according to claim 4 or 5, characterized in that said common portion (34) comprises, from upstream to downstream, said expansion valve (25), said evaporator (21) and said compressor (26).
  7. 7. Turbine engine (1) according to any of the preceding claims, wherein the cold source (24) is an air stream.
  8. 8. Method for regulating the temperature of fuel of a supply system (12) of a combustion chamber (10) of a turbine engine (1) according to any one of the preceding claims, the method comprising the steps of: a) The temperature of the fuel leaving the first condenser (22) is regulated by regulating the flow of heat transfer fluid entering the first condenser (22) via the metering device (27).
  9. 9. The method according to the preceding claim, characterized in that the metering device (27) is electrically controlled by a control system (30) as a function of a setpoint.
  10. 10. The method according to the preceding claim, characterized in that a setpoint for controlling the metering device (27) is determined by the control system (30) on the basis of the temperature and a critical temperature of the fuel located downstream of the first condenser (22) in a fuel circuit in heat exchange with the first condenser (22), above which the fuel cokes.

Description

Aircraft turbine engine comprising a heat pump Technical Field The present invention relates to an aircraft turbine engine comprising a heat pump, and to a method for regulating the temperature of fuel of a supply system of a combustion chamber of such a turbine engine. Background Dual flow turbine engines typically include a fan driven by a power turbine and a gas generator that generates gas for driving the power turbine. The gas generator includes at least one compressor, a combustor, and at least one turbine. The fan generates an air flow that is divided into a main flow configured to supply the gas generator and a secondary flow that contributes primarily to the thrust provided by the turbine engine. The turbine engine also comprises various oil circuits, the function of which is for example to lubricate the movable elements of the turbine engine (bearings, toothed wheels, etc.) and/or to cool the electric motor of the turbine engine. In order for the oil to fully perform its function, it is critical to maintain the temperature of the oil within a given range, in particular using a cooling system. Engine manufacturers are currently facing significant challenges. In fact, the new turbine engine architecture incorporates more oil circuits, mainly due to the inclusion of a reduction gear (between the power turbine and the fan) and/or the increased use of a generator to enhance the hybrid nature of the turbine engine. These additional oil circuits inevitably mean an increase in the thermal power to be dissipated, and it is therefore necessary to look at the existing cooling system. To meet this need, it is known in document FR2993610A1 in the name of the applicant to cool the oil with a heat pump. Heat pumps of this type comprise a closed circuit in which a heat transfer fluid circulates, which circuit comprises in particular an evaporator, a condenser, a compressor and an expansion valve. More specifically, the evaporator evaporates the heat transfer fluid by taking heat from the oil (heat source). The condenser condenses the heat transfer fluid, releasing heat into the air stream (cold source). The compressor compresses the heat transfer fluid (gaseous) to increase its pressure before it passes through the condenser. The expansion valve expands the heat transfer fluid (liquid) to reduce its pressure before it passes through the evaporator. In the above documents, the heat pump is used only for cooling the oil. However, engine manufacturers point out that it may be advantageous to use the heat pump for other functions (e.g., heating fuel before it is injected into the combustion chamber). It has been found that the temperature of the injected fuel is a key parameter to improve the efficiency of the combustion chamber and to minimize the specific consumption of the turbine engine. It has been found that the higher the temperature of the injected fuel, the better the efficiency and fuel consumption. However, it has also been found that the temperature of the injected fuel must not exceed a critical temperature (e.g., 150 degrees) above which coking of the fuel may occur. In practice, above the critical temperature, the fuel oxidizes and cokes. Coking of the fuel results in the appearance of black deposits in the various equipment of the supply system (in particular the injectors), which deposits accumulate over time and lead to gradual clogging. Such clogging inevitably degrades the injection system and thus the homogeneity of the fuel and more generally the performance of the combustion chamber and the turbine engine. Generally, existing supply systems do not include any dedicated fuel heating equipment, as engine manufacturers prioritize other functions, particularly deicing of fuel. Engine manufacturers also note that the equipment of the heat pump (evaporator, condenser or condensers, etc.) is sized to cope with the worst case scenario, i.e. where the oil has a large amount of thermal power to dissipate (e.g. high operating speed in combination with high external temperature) and the air stream (cold source) has a high temperature. In practice, however, the device is only operated at maximum power from time to time. Thus, engine manufacturers point out that it may be beneficial to use the power of the available equipment for other purposes (especially to preheat the fuel prior to injection into the combustion chamber). It is therefore an object of the present invention to optimize a heat pump such that the heat pump not only enables cooling of the oil, but also enables heating of the fuel before it is injected into the combustion chamber. Disclosure of Invention The present invention thus proposes an aircraft turbine engine comprising: -a system for supplying fuel to a combustion chamber of a turbine engine; A heat pump comprising a closed circuit in which a heat transfer fluid circulates, the circuit comprising an evaporator configured to exchange heat with oil of the turbine engine, a first condenser