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CN-121986210-A - Aircraft turbine engine comprising a heat pump

CN121986210ACN 121986210 ACN121986210 ACN 121986210ACN-121986210-A

Abstract

An aircraft turbine engine comprising a heat pump (14) intended to cool oil, the heat pump (14) comprising a closed circuit (19) in which a heat transfer fluid circulates, the circuit (19) comprising-a common part (20) comprising a first expansion valve (21), an evaporator (22) exchanging heat with the oil, and a first compressor (23), -a first and a second branch (24, 25) mounted in parallel to each other, the first branch (24) comprising a first condenser (26) and the second branch (25) comprising a second condenser (28), the first compressor (23) being configured to adjust the pressure of the heat transfer fluid at the inlet of the first condenser (26) according to a first set point, the second compressor (30) being configured to adjust the pressure of the heat transfer fluid at the inlet of the second condenser (28) according to a second set point.

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 heat pump (14) configured to cool oil used in the turbine engine (1), the heat pump (14) comprising a closed circuit (19) in which a heat transfer fluid circulates, the circuit (19) comprising: -a common part (20) comprising a first expansion valve (21), an evaporator (22) exchanging heat with the oil to be cooled, and a first compressor (23); -a first and a second branch (24, 25) mounted in parallel to each other, the first branch (24) comprising a first condenser (26) exchanging heat with a first cold source (27), the second branch (25) comprising a second condenser (28) exchanging heat with a second cold source (29); characterized in that the first compressor (23) is configured to regulate the pressure of the heat transfer fluid at the inlet of the first condenser (26) according to a first setpoint, the second branch (25) comprises a second compressor (30) arranged upstream of the second condenser (28), the second compressor (30) is configured to regulate the pressure of the heat transfer fluid at the inlet of the second condenser (28) according to a second setpoint.
  2. 2. The turbine engine (1) according to claim 1, characterized in that the first cold source (27) is a fuel or air flow configured to supply a combustion chamber (10) of a gas generator (4) of the turbine engine (1).
  3. 3. The turbine engine (1) according to any one of the preceding claims, characterized in that the second cold source (29) is a fuel or air flow configured to supply a combustion chamber (10) of a gas generator (4) of the turbine engine (1), and in that the fluid of the second cold source (29) is different from the fluid of the first cold source (27).
  4. 4. Turbine engine (1) according to any one of the preceding claims, wherein the inlet of the branch (24, 25) is connected to the outlet of the common part (20) via a control valve (32) having three passages.
  5. 5. Turbine engine (1) according to the preceding claim, wherein the valve (32) is configured to have at least a first position in which the valve (32) enables the heat transfer fluid to enter into the first and second branches (24, 25).
  6. 6. The turbine engine (1) according to the preceding claim, characterized in that the valve (32) is further configured to have at least one of the following positions: -a second position in which the valve (32) prevents the heat transfer fluid from passing through; -a third position in which the valve (32) enables the heat transfer fluid to pass through the first branch (24) only; -a fourth position in which the valve (32) enables the heat transfer fluid to pass through the second branch (25) only.
  7. 7. Turbine engine (1) according to any one of claims 4 to 6, wherein the valve (32) is controlled by a control system (33) depending on the temperature of the oil to be cooled.
  8. 8. Turbine engine (1) according to any one of the preceding claims, wherein the second branch (25) comprises a second expansion valve (34) arranged downstream of the second condenser (28).
  9. 9. Turbine engine (1) according to any of the preceding claims, wherein the first set point is determined from the temperature of the first cold source (27) and the second set point is determined from the temperature of the second cold source (29).
  10. 10. Turbine engine (1) according to any of the preceding claims, wherein the oil to be cooled comes from an oil system (15) comprising a lubrication circuit configured to lubricate movable elements of the turbine engine (1) and/or a cooling circuit configured to cool at least one generator (31) of the turbine engine (1).

Description

Aircraft turbine engine comprising a heat pump Technical Field The present invention relates to an aircraft turbine engine comprising a heat pump. 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.). 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 speed reducer (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, rejecting heat to a cold source (e.g., an air stream). The compressor compresses the heat transfer fluid (gaseous) to increase its pressure (and thus its temperature) before passing through the condenser. The expansion valve expands the heat transfer fluid (liquid) to reduce its pressure (and thus its temperature) before it passes through the evaporator. To improve its performance, engine manufacturers point out that it may be interesting to integrate a second condenser into the circuit of the heat pump, which second condenser will then exchange heat with a second cold source (e.g. fuel). However, engine manufacturers have found a barrier to integrating the second condenser. This is because the temperatures of the two cold sources are different, which means that the temperature of the heat transfer fluid at the inlet of each of the condensers must be different to achieve optimal heat exchange at each of the condensers. However, a circuit with a single compressor means that the temperature of the heat transfer fluid at the inlet of the condenser is the same, which means that the heat exchange at both the first condenser (heat transfer fluid/first cold source) and the second condenser (heat transfer fluid/second cold source) may not be optimal. It should be noted that the temperature of the heat transfer fluid at the inlet of the condenser is directly related to the pressure of the heat transfer fluid discharged by the compressor. The sub-optimal heat exchange at the condenser inevitably means that an excessively large condenser is installed, which is undesirable from the point of view of the overall size and weight of the heat pump. It is therefore an object of the present invention to provide a simple, effective and economical solution to the above mentioned problems. Disclosure of Invention The present invention thus proposes a turbine engine for an aircraft, the turbine engine comprising a heat pump configured to cool oil used in the turbine engine, the heat pump comprising a closed circuit in which a heat transfer fluid circulates, the circuit comprising: -a common part comprising a first expansion valve, an evaporator exchanging heat with the oil to be cooled, and a first compressor; -a first branch and a second branch, the first branch and the second branch being mounted in parallel to each other, the first branch comprising a first condenser exchanging heat with a first cold source, the second branch comprising a second condenser exchanging heat with a second cold source; wherein the first compressor is configured to regulate the pressure of the heat transfer fluid at the inlet of the first condenser in accordance with a first set point, and the second branch comprises a second compressor disposed upstream of the second condenser, the second compressor being configured to regulate the pressure of the heat transfer fluid at the inlet of the second condenser in accordance with a second set point. The first compressor is now dedicated to the first condenser to regulate the pressure (and thus the temperature) of the heat transfer fluid at