Thermal management type combined power system, aircraft and control method

Abstract

The invention relates to the technical field of aircraft environment control systems, in particular to a thermal management type combined power system, an aircraft and a control method. According to the system, in a power assembly, a gas compressor, a combustion chamber and a gas turbine are sequentially connected; the air inlet part, the air compressor and the combustion chamber are sequentially communicated; in the refrigeration air supply assembly, a condenser is provided with a first channel and a second channel; an outlet of the gas compressor, the first channel, the first cooling turbine, the second channel, the second cooling turbine and the first heat exchanger are communicated in sequence; an outlet of the first heat exchanger communicates with outside atmosphere; an outlet of the first heat exchanger communicates with an inlet of the compressor; the gas compressor, the second cooling turbine and the second gas-liquid separator are communicated in sequence; the condenser is detachably connected with the first gas-liquid separator; the first cooling turbine, the second cooling turbine, the gas compressor and the gas turbine are all in coaxial transmission connection with the motor assembly. The valve assembly controls on-off of the pipeline. Therefore, the problem that the condenser is frozen and blocked when the aircraft is in air loop control cooling is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft environmental control systems, and in particular to a thermal management type combined power system, an aircraft and a control method. Background Art

[0002] The thermal management combined power system physically integrates and functionally combines the aircraft auxiliary / emergency power, environmental control and starting power generation systems, so that it has multiple functions such as ground engine starting, ground maintenance, air environmental control refrigeration and power generation, and air emergency power generation, etc., to replace traditional auxiliary power units, emergency power units, air cycle refrigeration units and evaporative cycle refrigeration units. However, the waste heat of aircraft, especially military fighters, has increased significantly. The current demand for aircraft cooling systems exceeds the original design, resulting in more engine bleed air, which will affect the performance and life of the engine to a certain extent. Therefore, the demand for a new and efficient thermal management combined power unit is becoming increasingly urgent. Summary of the invention

[0003] In order to solve the problem of freezing and blocking of the condenser when the aircraft is refrigerated in the air, the present invention provides a thermal management type combined power system, an aircraft and a control method.

[0004] In a first aspect, the present invention provides a thermal management type combined power system, the thermal management type combined power system comprising: A power assembly, the power assembly comprising a compressor, a combustion chamber, a gas turbine and an air intake; the compressor, the combustion chamber and the gas turbine are detachably connected in sequence; the compressor and the gas turbine are coaxially connected; the air intake is connected to the inlet of the compressor to form a first air intake path; the air intake is used to connect to the outside atmosphere; the outlet of the compressor is connected to the combustion chamber to form a first gas path; A motor assembly, the motor assembly comprising a starter-generator integrated motor, the starter-generator integrated motor is coaxially connected to the compressor; A refrigeration air supply component, the refrigeration air supply component comprises a condenser, a first gas-liquid separator, a first cooling turbine, a second cooling turbine, a second gas-liquid separator and a first heat exchanger; the condenser has a first channel and a second channel isolated from each other; the first channel and the second channel can perform heat exchange; the outlet of the compressor, the first channel, the first cooling turbine, the second channel, the second cooling turbine and the first heat exchanger are connected in sequence to form a refrigeration path; the outlet of the first heat exchanger is connected to the outside atmosphere to form an exhaust path; the outlet of the first heat exchanger is connected to the inlet of the compressor to form a return path; the outlet of the compressor is connected to the second cooling turbine to form a first air supply path; the outlet of the second cooling turbine is connected to the inlet of the second gas-liquid separator to form a second air supply path; the condenser is detachably connected to the first gas-liquid separator; the first gas-liquid separator can perform gas-liquid separation on the medium flowing through the condenser; the first cooling turbine and the second cooling turbine are both coaxially connected to the starting-in-one motor; A valve assembly controls the opening and closing of the first air intake path, the first gas path, the refrigeration path, the exhaust path, and the first air supply path.

[0005] In some embodiments, the refrigeration air supply component also includes a second heat exchanger; the second heat exchanger has a third channel and a fourth channel isolated from each other; the third channel and the fourth channel are capable of heat exchange; the outlet of the compressor is connected to the third channel; the third channel is respectively connected to the first channel and the second cooling turbine; the outlet of the first heat exchanger is connected to the fourth channel; the fourth channel is connected to the atmosphere to form the exhaust path; the fourth channel is connected to the inlet of the compressor to form the return path.

[0006] In some embodiments, the thermally managed combined power system further includes an engine assembly; The power assembly also includes a first air induction portion; the engine assembly, the first air induction portion and the combustion chamber are connected in sequence to form a second gas path; and the valve assembly controls the on-off of the second gas path.

[0007] In some embodiments, the power assembly further includes a second air inlet; the engine assembly, the second air inlet and the inlet of the compressor are sequentially connected to form a second air inlet path; the valve assembly controls the on-off of the second air inlet path; The second air intake path merges with the cooling path, or the second air intake path merges with the return path.

[0008] In some embodiments, the refrigeration air supply assembly further includes a heat dissipation channel, and the heat dissipation channel can exchange heat with the outside atmosphere; the outlet of the compressor is connected to the third channel through the heat dissipation channel.

[0009] In some embodiments, a heat exchange channel is integrally formed on the casing of the gas turbine; the first air induction portion is connected to the combustion chamber through the heat exchange channel; and the outlet of the compressor is connected to the combustion chamber through the heat exchange channel.

[0010] In a second aspect, the present invention provides an aircraft, comprising: a frame system; a thermal management type combined power system according to any one of the above embodiments; the thermal management type combined power system is detachably connected to the frame system.

[0011] In a third aspect, the present invention provides an aircraft control method, the aircraft control method is applied to the aircraft described in the second aspect, the aircraft control method comprising: Step S10, wherein step S10 includes steps S11 to S15; Step S11, based on the aircraft being in a ground maintenance state or a first flight state, obtaining a first working instruction of the aircraft; the first flight state includes that the flight altitude of the aircraft is lower than a preset altitude; Step S12, based on the first working instruction including gas supply and power generation, opening the first air intake path and the first gas path until the speed of the gas turbine reaches a first preset speed; Step S13, based on the rotation speed of the gas turbine reaching the first preset rotation speed, opening the first gas supply path and the second gas supply path, and controlling the starter-generator integrated motor to switch to a generator working state; Step S14, based on the first working instruction including power generation, refrigeration and gas supply, opening the first air intake path and the first gas path until the speed of the gas turbine reaches the rated working speed; Step S15, based on the rotation speed of the gas turbine reaching the rated operating speed, the refrigeration path, the exhaust path and the second air supply path are opened, and the starting-generating integrated motor is controlled to be in a power generation state.

[0012] In some embodiments, the aircraft control method further includes step S20, and step S20 includes steps S21 to S25; Step S21, based on the aircraft being in a second flight state, obtaining a second working instruction of the aircraft; the second flight state includes that the flight altitude of the aircraft is higher than the preset altitude; Step S22, based on the second working instruction including power generation and gas supply, opening the second gas path; until the speed of the gas turbine reaches a second preset speed; Step S23, based on the rotation speed of the gas turbine reaching the second preset rotation speed, the first air intake path, the first air supply path and the second air supply path are opened, and the starting and generating integrated motor is controlled to switch to a generator working state; Step S24, based on the second working instruction including power generation, gas supply and refrigeration, opening the second gas path; until the speed of the gas turbine reaches a third preset speed; Step S25, based on the rotation speed of the gas turbine reaching a third preset rotation speed, the second air intake path, the cooling path, the return path and the second air supply path are opened, and the starting-and-generating integrated motor is controlled to switch to a generator working state.

[0013] In some embodiments, the step S20 further includes steps S26 to S27; Step S26, based on the second working instruction including cooling and gas supply, opening the second gas path; until the speed of the gas turbine reaches a fourth preset speed; Step S27, based on the rotation speed of the gas turbine reaching a fourth preset rotation speed, the second air intake path, the cooling path, the return path and the second air supply path are opened, and the starting-in-one motor is controlled to switch to an electric motor working state.

[0014] In order to solve the problem of freezing and blocking of the condenser when the aircraft is refrigerated in the air, the present invention has the following advantages: The outlet of the compressor, the first channel, the first cooling turbine, the second channel, the second cooling turbine, and the first heat exchanger are connected in sequence to form a refrigeration path to achieve two-stage refrigeration. The two-stage turbine expansion refrigeration of the first cooling turbine and the second cooling turbine can effectively improve the expansion ratio and improve the refrigeration capacity of the aircraft. The air discharged from the compressor passes through the first channel of the condenser before passing through the first cooling turbine for refrigeration. The air passes through the second channel of the condenser after passing through the first cooling turbine for the first stage of refrigeration. The first channel and the second channel perform heat exchange, thereby utilizing the cold air discharged from the first cooling turbine to absorb part of the heat of the air before the inlet of the first cooling turbine, thereby condensing and cooling the air before the inlet of the first cooling turbine in advance, reducing the refrigeration actuation requirements of the first cooling turbine, and both the first channel and the second channel can use the first gas-liquid separator to separate moisture, thereby improving the dryness of the air, thereby improving the air supply and refrigeration effect. Since the refrigerated gas is cooled in two stages, the temperature of the gas discharged from the first cooling turbine can be higher than 0°C, so it is not easy to freeze when the gas enters the condenser. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1A schematic diagram of a thermal management combined power system according to an embodiment is shown; Figure 2 A schematic flow chart of an aircraft control method according to an embodiment is shown.

[0016] Figure numerals: 10 power assembly; 11 compressor; 12 combustion chamber; 13 gas turbine; 14 air intake; 15 first air inlet; 16 second air inlet; 17 heat exchange channel; 20 motor assembly; 30 refrigeration air supply assembly; 31 condenser; 32 first gas-liquid separator; 33 first cooling turbine; 34 second cooling turbine; 35 second gas-liquid separator; 36 first heat exchanger; 37 second heat exchanger; 38 heat dissipation channel; 40 valve assembly; 50 engine assembly. DETAILED DESCRIPTION

[0017] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and thus implement the present disclosure, rather than implying any limitation on the scope of the present disclosure.

[0018] As used herein, the term "including" and its variants are to be interpreted as open-ended terms meaning "including but not limited to". The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment". The term "another embodiment" is to be interpreted as "at least one other embodiment". The orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal" and the like is based on the orientation or position relationship shown in the accompanying drawings. These terms are mainly for better describing the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation. In addition, in addition to being used to indicate an orientation or position relationship, some of the above terms may also be used to indicate other meanings, such as the term "upper" may also be used to indicate a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances. In addition, the terms "install", "set", "provided with", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be an internal connection between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances. In addition, the terms "first", "second", etc. are mainly used to distinguish different devices, elements or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, elements or components. Unless otherwise specified, "plurality" means two or more.

[0019] In this embodiment, the existing system has poor gas-liquid separation effect when cooling the aircraft, and the exhaust pressure of the cooling turbine is higher than the required pressure of the cabin, resulting in incomplete expansion of the air and large pressure energy loss, which ultimately leads to insufficient cooling efficiency. To this end, this embodiment discloses a thermal management type combined power system. Figure 1 As shown, the thermal management type combined power system includes a power assembly 10 , a motor assembly 20 , a refrigeration air supply assembly 30 , and a valve assembly 40 .

[0020] The power assembly 10 includes a compressor 11, a combustion chamber 12, a gas turbine 13 and an air intake 14; the compressor 11, the combustion chamber 12 and the gas turbine 13 are detachably connected in sequence; the compressor 11 and the gas turbine 13 are coaxially connected; the air intake 14 is connected to the inlet of the compressor 11 to form a first air intake path; the air intake 14 is used to connect to the outside atmosphere; so that the air supplied by the air intake 14 can be compressed by the compressor 11 and used as a refrigerant or combustion aid. The outlet of the compressor 11 is connected to the combustion chamber 12 to form a first gas path; so that when the aircraft is on the ground or at low altitude, the gas turbine 13 can be operated through the first air intake path and the first gas path.

[0021] The motor assembly 20 includes a starter-generator motor, which is coaxially connected to the compressor 11; the starter-generator motor is switched to a generator mode, and the gas turbine 13 can drive the starter-generator motor to rotate and generate electricity. When flying at high altitudes, in order to reduce the amount of gas entering the combustion chamber 12, the engine can be used to extract electric power to drive the starter-generator motor to operate, so that the starter-generator motor is switched to an electric motor mode, thereby providing power compensation for the rotation of the gas turbine 13 and improving the economy of the flight.

[0022] The refrigeration air supply assembly 30 includes a condenser 31, a first gas-liquid separator 32, a first cooling turbine 33, a second cooling turbine 34, a second gas-liquid separator 35 and a first heat exchanger 36; the condenser 31 has a first channel and a second channel isolated from each other; the first channel and the second channel can perform heat exchange; the outlet of the compressor 11, the first channel, the first cooling turbine 33, the second channel, the second cooling turbine 34, and the first heat exchanger 36 are connected in sequence to form a refrigeration path; the refrigerant can take away the heat exchanged by the first heat exchanger 36 through the refrigeration path, thereby cooling the onboard equipment. The outlet of the first heat exchanger 36 is connected to the outside atmosphere to form an exhaust path, so that the refrigerant can discharge heat. The outlet of the first heat exchanger 36 is connected to the inlet of the compressor 11 to form a return path, so that when the aircraft is in a state of thin air at high altitude, the air and engine gas consumption is reduced and the air is recycled. The outlet of the compressor 11 is connected to the second cooling turbine 34 to form a first air supply path, so that air with a suitable temperature can be supplied to the aircraft cabin. The outlet of the second cooling turbine 34 is connected to the inlet of the second gas-liquid separator 35 to form a second air supply path; thereby, the water content in the air supplied to the aircraft cabin can be reduced. The condenser 31 is detachably connected to the first gas-liquid separator 32; the first gas-liquid separator 32 can perform gas-liquid separation on the medium flowing through the condenser 31, thereby reducing pipeline redundancy and achieving the purpose of lightweighting the aircraft. The first cooling turbine 33 and the second cooling turbine 34 are both coaxially connected to the starting motor; the starting motor drives the first cooling turbine 33 and the second cooling turbine 34 to rotate so as to reduce the temperature of the air flowing through the first cooling turbine 33 and the second cooling turbine 34.

[0023] The valve assembly 40 controls the on-off of the first air intake path, the first fuel gas path, the refrigeration path, the exhaust path, and the first air supply path, so as to meet the air supply requirements of the aircraft under different working conditions.

[0024] Through the above configuration, the first channel and the second channel are set in the condenser 31, so that the air can flow through the condenser 31 and the first gas-liquid separator 32 twice through the refrigeration path, thereby improving the gas-liquid separation effect, reducing the water content in the air, and reducing the risk of freezing at the inlet of the second cooling turbine 34. The two-stage refrigeration of the first cooling turbine 33 and the second cooling turbine 34 ensures that the temperature of the air discharged from the first cooling turbine 33 is still above 0°C. At this time, the risk of freezing at the inlet of the condenser 31 is low. After the second gas-liquid separation to reduce the water content, the air enters the second cooling turbine 34 and is cooled to below 0°C, thereby improving the expansion ratio of the air, reducing the pressure energy loss, and thus improving the refrigeration efficiency.

[0025] In this embodiment, if Figure 1 As shown, the refrigeration air supply component 30 also includes a second heat exchanger 37; the second heat exchanger 37 has a third channel and a fourth channel isolated from each other; the third channel and the fourth channel can perform heat exchange; the outlet of the compressor 11 is connected to the third channel; the third channel is respectively connected to the first channel and the second cooling turbine 34; the outlet of the first heat exchanger 36 is connected to the fourth channel; the fourth channel is connected to the atmosphere to form an exhaust path; the fourth channel is connected to the inlet of the compressor 11 to form a return path.

[0026] Through the above arrangement, the refrigerant (air) flowing out of the outlet of the compressor 11 in the refrigeration path first flows into the second heat exchanger 37, so that the remaining cold air discharged from the first heat exchanger 36 can be used in the second heat exchanger 37 through the fourth channel to cool the higher temperature air flowing to the refrigeration path or the first air supply path, thereby reducing the refrigeration requirements of the condenser 31, the first cooling turbine 33 and the second cooling turbine 34, thereby reducing energy consumption and improving energy utilization.

[0027] In this embodiment, if Figure 1 As shown, the thermal management type combined power system also includes an engine assembly 50; the power assembly 10 also includes a first air induction part 15; the engine assembly 50, the first air induction part 15 and the combustion chamber 12 are connected in sequence to form a second gas path; the valve assembly 40 controls the on and off of the second gas path.

[0028] When the aircraft climbs to a high altitude during flight, the air is relatively thin, and the air introduced into the compressor 11 from the air intake 14 is difficult to meet the gas volume for cooling and air supply. Providing a second gas path allows the combustion chamber 12 to introduce gas from the engine assembly 50 to assist combustion, thereby allowing the gas turbine 13 to operate normally.

[0029] In this embodiment, if Figure 1 As shown, the power assembly 10 further includes a second air inlet 16; the engine assembly 50, the second air inlet 16 and the inlet of the compressor 11 are sequentially connected to form a second air inlet path; the valve assembly 40 controls the on-off of the second air inlet path; The second air intake path merges with the cooling path, or the second air intake path merges with the return path.

[0030] By arranging the second air intake path to merge with the refrigeration path or the second air intake path to merge with the return path, the gas supplied by the engine assembly 50 can be cooled by using the residual coldness of the air in the refrigeration path or the converging path before entering the inlet of the compressor 11, thereby improving energy utilization, reducing the temperature of the air entering the inlet of the compressor 11, and avoiding damage to the compressor 11. The design of the second air bleed portion 16 ensures that the gas volume requirements for refrigeration and air supply can still be met when the aircraft is flying at high altitude.

[0031] In this embodiment, if Figure 1 As shown, the refrigeration air supply assembly 30 also includes a heat dissipation channel 38, which can exchange heat with the outside atmosphere; the outlet of the compressor 11 is connected to the third channel through the heat dissipation channel 38.

[0032] The heat dissipation channel 38 can be located on the outer shell of the aircraft to achieve heat exchange with the outside atmosphere, so that the air exhausted by the compressor 11 can enter the second heat exchanger 37 for cooling after preliminary heat dissipation through the heat dissipation channel 38, thereby further reducing the refrigeration requirements of the condenser 31, the first cooling turbine 33, and the second cooling turbine 34, and reducing energy consumption.

[0033] In this embodiment, if Figure 1 As shown, a heat exchange channel 17 is integrally formed on the casing of the gas turbine 13 ; the first air induction portion 15 is connected to the combustion chamber 12 through the heat exchange channel 17 ; and the outlet of the compressor 11 is connected to the combustion chamber 12 through the heat exchange channel 17 .

[0034] Through the above-mentioned arrangement, the air supplied to the combustion chamber 12 can flow through the heat exchange channel 17, so that the waste heat generated by the work of the gas turbine 13 can be used to preliminarily heat the gas introduced into the engine component 50 or the air compressed by the compressor 11, thereby improving energy utilization. At the same time, the heat exchange channel 17 is designed as a conformal integrated design of the gas turbine 13 casing, which can also play a role in lightweighting.

[0035] In this embodiment, an aircraft is disclosed, the aircraft comprising: a frame system; a thermal management type combined power system of any one of the above embodiments; the thermal management type combined power system and the frame system are detachably connected. The aircraft may be a drone, a civil airliner, a fighter jet, etc.

[0036] In this embodiment, this embodiment discloses an aircraft control method applied to the above embodiment. Figure 2 As shown, the aircraft control method includes: Step S10, step S10 includes steps S11 to S15; Step S11, based on the aircraft being in a ground maintenance state or a first flight state, obtaining a first working instruction of the aircraft; the first flight state includes the aircraft's flight altitude being lower than a preset altitude; at this time, it is easier for the aircraft to obtain air.

[0037] Step S12, based on the first working instruction including gas supply and power generation, the first air intake path and the first gas path are opened until the speed of the gas turbine 13 reaches the first preset speed; the first preset speed may be 95% of the rated working speed of the gas turbine 13. The air intake part 14 cooperates with the compressor 11 to supply gas to the combustion chamber 12 through the first air intake path and the first gas path to assist combustion. At this time, the starter motor can drive the belt to rotate.

[0038] Step S13, based on the rotation speed of the gas turbine 13 reaching the first preset rotation speed, the first air supply path and the second air supply path are opened, and the starter-generator integrated motor is controlled to switch to the generator working state; at this time, the gas turbine 13 works to drive the starter-generator integrated motor to generate electricity. The air compressed by the compressor 11 is supplied to the aircraft cabin and other air-consuming equipment through the first air supply path and the second air supply path.

[0039] Step S14, based on the first working instruction including power generation, refrigeration and gas supply, the first air intake path and the first gas path are opened until the speed of the gas turbine 13 reaches the rated working speed; Step S15, based on the speed of the gas turbine 13 reaching the rated operating speed, the refrigeration path, the exhaust path and the second air supply path are turned on, and the starter-generator is controlled to be in the power generation state. The air compressed by the compressor 11 realizes the refrigeration function through the refrigeration path and the exhaust path, specifically, the heat of the equipment load is absorbed through the first heat exchanger 36. The gas compressed by the compressor 11 is supplied to the aircraft cabin or other gas-using equipment through the refrigeration path and the second air supply path.

[0040] In other embodiments, the thermal management type combined power system may also only supply air. Specifically, the air compressed by the compressor 11 supplies air to the aircraft cabin or other air-consuming equipment through the first air supply path and the second air supply path, and supplies air to the combustion chamber 12 through the first fuel gas path.

[0041] Through the above control, the aircraft can adjust the air supply mode, the integrated air supply and power generation mode, or the integrated function of air supply, power generation and refrigeration of the thermal management combined power system under different working conditions, so as to meet the use requirements of the aircraft.

[0042] In this embodiment, the aircraft control method further includes step S20, and step S20 includes steps S21 to S25; Step S21, based on the aircraft being in a second flight state, obtaining a second working instruction of the aircraft; the second flight state includes the aircraft's flight altitude being higher than a preset altitude; at this time, the aircraft is in a high-altitude state and the air is relatively thin.

[0043] Step S22, based on the second working instruction including power generation and gas supply, the second gas path is opened until the speed of the gas turbine 13 reaches a second preset speed; the second preset speed may be 75% of the rated working speed of the gas turbine 13. The gas turbine 13 is driven to rotate by bleed air from the engine assembly 50.

[0044] Step S23, based on the speed of the gas turbine 13 reaching the second preset speed, the first air intake path, the first air supply path and the second air supply path are opened, and the starter-generator motor is controlled to switch to the generator working state. When the speed of the gas turbine 13 reaches the second preset speed, the thermal management type combined power system has the ability to generate electricity and supply air. At this time, the gas exhausted by the compressor 11 is supplied to the air-using equipment such as the cabin of the aircraft through the first air supply path and the second air supply path.

[0045] Step S24, based on the second working instruction including power generation, gas supply and refrigeration, the second gas path is opened until the speed of the gas turbine 13 reaches a third preset speed; the third preset speed may be 85% of the rated working speed of the gas turbine 13. When the speed of the gas turbine 13 reaches the third preset speed, the thermal management type combined power system has the ability to generate power, supply gas and refrigerate.

[0046] Step S25, based on the speed of the gas turbine 13 reaching the third preset speed, the second air intake path, the cooling path, the return path and the second air supply path are opened, and the starting and generating integrated motor is controlled to switch to the generator working state. The return path can reduce the gas consumption and achieve the purpose of recycling.

[0047] In other embodiments, when the aircraft opens the second air intake path, the cooling path, the return path and the second air supply path, if it is in a low-altitude state, the induction part can be opened to supply air, thereby reducing the amount of gas introduced from the engine assembly 50 to ensure normal operation of the engine.

[0048] In this embodiment, step S20 also includes steps S26 to S27; Step S26, based on the second working instruction including cooling and air supply, the second gas path is opened until the speed of the gas turbine 13 reaches a fourth preset speed; the fourth preset speed may be 75% of the rated working speed of the gas turbine 13. When the speed of the gas turbine 13 reaches the fourth preset speed, the thermal management type combined power system has the ability of cooling and air supply.

[0049] Step S27, based on the rotation speed of the gas turbine 13 reaching the fourth preset rotation speed, the second air intake path, the cooling path, the return path and the second air supply path are opened, and the starting-generating integrated motor is controlled to switch to the electric motor working state.

[0050] The reflux path can be used to recycle the gas discharged from the refrigeration path, thereby reducing gas consumption. The air flowing through the second gas path can absorb the waste heat of the gas turbine 13 and then enter the combustion chamber 12 for combustion, thereby improving the combustion efficiency in the combustion chamber 12 and improving energy utilization.

[0051] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present disclosure, and in actual applications, various changes may be made thereto in form and detail without departing from the scope of the present disclosure.

Claims

1. A thermal management combined power system, characterized in that: The thermal management combined power system comprises: A power assembly, the power assembly comprising a compressor, a combustion chamber, a gas turbine and an air intake; the compressor, the combustion chamber and the gas turbine are detachably connected in sequence; the compressor and the gas turbine are coaxially connected; the air intake is connected to the inlet of the compressor to form a first air intake path; the air intake is used to connect to the outside atmosphere; the outlet of the compressor is connected to the combustion chamber to form a first gas path; A motor assembly, the motor assembly comprising a starter-generator integrated motor, the starter-generator integrated motor is coaxially connected to the compressor; A refrigeration air supply component, the refrigeration air supply component comprises a condenser, a first gas-liquid separator, a first cooling turbine, a second cooling turbine, a second gas-liquid separator and a first heat exchanger; the condenser has a first channel and a second channel isolated from each other; the first channel and the second channel can perform heat exchange; the outlet of the compressor, the first channel, the first cooling turbine, the second channel, the second cooling turbine and the first heat exchanger are connected in sequence to form a refrigeration path; the outlet of the first heat exchanger is connected to the outside atmosphere to form an exhaust path; the outlet of the first heat exchanger is connected to the inlet of the compressor to form a return path; the outlet of the compressor is connected to the second cooling turbine to form a first air supply path; the outlet of the second cooling turbine is connected to the inlet of the second gas-liquid separator to form a second air supply path; the condenser is detachably connected to the first gas-liquid separator; the first gas-liquid separator can perform gas-liquid separation on the medium flowing through the condenser; the first cooling turbine and the second cooling turbine are both coaxially connected to the starting-in-one motor; A valve assembly controls the opening and closing of the first air intake path, the first gas path, the refrigeration path, the exhaust path, and the first air supply path.

2. A thermal management combined power system according to claim 1, characterized in that: The refrigeration air supply component also includes a second heat exchanger; the second heat exchanger has a third channel and a fourth channel isolated from each other; the third channel and the fourth channel are capable of heat exchange; the outlet of the compressor is connected to the third channel; the third channel is respectively connected to the first channel and the second cooling turbine; the outlet of the first heat exchanger is connected to the fourth channel; the fourth channel is connected to the atmosphere to form the exhaust path; the fourth channel is connected to the inlet of the compressor to form the return path.

3. A thermal management combined power system according to claim 2, characterized in that: The thermal management combined power system also includes an engine assembly; The power assembly also includes a first air induction portion; the engine assembly, the first air induction portion and the combustion chamber are connected in sequence to form a second gas path; and the valve assembly controls the on-off of the second gas path.

4. A thermal management combined power system according to claim 3, characterized in that: The power assembly further includes a second air inlet; the engine assembly, the second air inlet and the inlet of the compressor are sequentially connected to form a second air inlet path; the valve assembly controls the on-off of the second air inlet path; The second air intake path merges with the cooling path, or the second air intake path merges with the return path.

5. A thermal management combined power system according to claim 2, characterized in that: The refrigeration air supply component also includes a heat dissipation channel, which can exchange heat with the outside atmosphere; the outlet of the compressor is connected to the third channel through the heat dissipation channel.

6. A thermal management combined power system according to claim 3, characterized in that: A heat exchange flow channel is integrally formed on the outer shell of the gas turbine; the first air induction portion is connected to the combustion chamber through the heat exchange flow channel; and the outlet of the compressor is connected to the combustion chamber through the heat exchange flow channel.

7. An aircraft, characterized in that: The aircraft comprises: Rack systems; A thermal management combined power system as described in any one of claims 1-6; the thermal management combined power system is detachably connected to the rack system.

8. An aircraft control method, applied to an aircraft as claimed in claim 7, characterized in that: The aircraft control method comprises: Step S10, wherein step S10 includes steps S11 to S15; Step S11, based on the aircraft being in a ground maintenance state or a first flight state, obtaining a first working instruction of the aircraft; the first flight state includes that the flight altitude of the aircraft is lower than a preset altitude; Step S12, based on the first working instruction including gas supply and power generation, opening the first air intake path and the first gas path until the speed of the gas turbine reaches a first preset speed; Step S13, based on the rotation speed of the gas turbine reaching the first preset rotation speed, opening the first gas supply path and the second gas supply path, and controlling the starter-generator integrated motor to switch to a generator working state; Step S14, based on the first working instruction including power generation, refrigeration and gas supply, opening the first air intake path and the first gas path until the speed of the gas turbine reaches the rated working speed; Step S15, based on the rotation speed of the gas turbine reaching the rated operating speed, the refrigeration path, the exhaust path and the second air supply path are opened, and the starting-generating integrated motor is controlled to be in a power generation state.

9. The aircraft control method according to claim 8, characterized in that: The aircraft control method further includes step S20, wherein step S20 includes steps S21 to S25; Step S21, based on the aircraft being in a second flight state, obtaining a second working instruction of the aircraft; the second flight state includes that the flight altitude of the aircraft is higher than the preset altitude; Step S22, based on the second working instruction including power generation and gas supply, opening the second gas path; until the speed of the gas turbine reaches a second preset speed; Step S23, based on the rotation speed of the gas turbine reaching the second preset rotation speed, the first air intake path, the first air supply path and the second air supply path are opened, and the starting and generating integrated motor is controlled to switch to a generator working state; Step S24, based on the second working instruction including power generation, gas supply and refrigeration, opening the second gas path; until the speed of the gas turbine reaches a third preset speed; Step S25, based on the rotation speed of the gas turbine reaching a third preset rotation speed, the second air intake path, the cooling path, the return path and the second air supply path are opened, and the starting-and-generating integrated motor is controlled to switch to a generator working state.

10. The aircraft control method according to claim 9, characterized in that: The step S20 also includes steps S26 to S27; Step S26, based on the second working instruction including cooling and gas supply, opening the second gas path; until the speed of the gas turbine reaches a fourth preset speed; Step S27, based on the rotation speed of the gas turbine reaching a fourth preset rotation speed, the second air intake path, the cooling path, the return path and the second air supply path are opened, and the starting-in-one motor is controlled to switch to an electric motor working state.

Images