A combined engine intake sealing and environmental control integrated thermal management system and method

Abstract

The present invention provides a combined engine intake air sealing and environmental control integrated thermal management system and method. In the combined engine intake air sealing and environmental control integrated thermal management system, an intake duct is connected to a power cabin, and the power cabin is provided with a power cabin ventilation flow path, including: a first control valve, an inlet of which is communicated with the intake duct; an air-fuel heat exchanger, an inlet of which is connected to an outlet of the first control valve; a gas wave divider, a medium-pressure inlet of which is connected to an outlet of the air-fuel heat exchanger, and a low-pressure outlet of the gas wave divider is connected to the power cabin ventilation flow path. By integrating the first control valve, the air-fuel heat exchanger and the gas wave divider, the embodiments of the present invention realize the effective connection and thermal management between the intake duct and the power cabin.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and particularly relates to a combined engine intake sealing and environmental control integrated thermal management system and method. Background Art

[0002] A turbofan-based combined cycle engine (hereinafter referred to as a combined engine) has the characteristics of conventional horizontal takeoff and landing, reusability, wide application, good safety, and the ability to use ordinary fuel, and has become one of the future development directions of power devices for aerospace vehicles recognized by countries around the world.

[0003] The two engines of the combined engine share one intake duct, and the intake air volume of the two engine channels is regulated by installing an actuating regulating plate (hereinafter referred to as the "intake regulating plate") in the intake duct to achieve the conversion of three working modes. In the mode where the ramjet engine works alone, the intake regulating plate actuates to a position where the turbine engine channel is completely closed. However, due to the gap between the regulating plate and the intake duct casing, some airflows will still leak into the internal part of the turbine engine that has stopped working. The working Mach number of the ramjet engine is usually above 3, and at this time, the total intake air temperature is as high as above 600K. The leakage of high-temperature gas will cause the residual lubricating oil inside the turbine engine to coke, and further lead to the inability of the turbine engine to restart in the air. It is necessary to seal the intake duct regulating plate to prevent high-temperature airflows from leaking into the turbine engine.

[0004] The commonly used seals for aeroengines are divided into non-contact seals and contact seals. The leakage amount of using non-contact seals alone is relatively large. Since the ramjet engine has no supercharging components, the airflow pressure in the intake duct is the highest pressure in the whole engine, and it is difficult to obtain a high-pressure sealing air source. Therefore, there are also no conditions for active air supply sealing. Contact seals usually adopt structures such as C-shaped metal sealing sheets. However, for the combined engine, since the intake regulating plate needs to actuate, the friction force generated by the contact seal will cause an additional load on the actuating cylinder, and the sealing sheet is prone to wear or deformation during reciprocating motion, resulting in a decrease or even failure of the sealing performance. The efficient sealing of adjustable components is a key problem that needs to be solved for the combined engine.

[0005] At the same time, the thermal load of the combined engine during high Mach number operation is much higher than that of conventional engines. However, due to material limitations, the temperature resistance levels of some engine components and accessories such as electronic components and sealing devices are difficult to improve. Therefore, it is necessary to control the temperature of the engine compartment to provide suitable working conditions for the components and accessories. The total intake air temperature above Ma3 has exceeded the temperature resistance levels of most components and accessories, and the bleed air from the intake duct cannot be directly used for the cooling and ventilation of the power compartment. The usual method is to pre-cool the bleed air using the fuel heat sink carried by the engine and then perform ventilation cooling of the power compartment. Summary of the Invention

[0006] In view of this, the present invention provides a combined engine intake air sealing and environmental control integrated thermal management system and method to solve the problem of air intake regulating plate leakage.

[0007] The present invention provides the following technical solutions: A combined engine intake air sealing and environmental control integrated thermal management system, where the intake duct is connected to the power cabin, and the power cabin is provided with a power cabin ventilation flow path, including: a first control valve, the inlet of which is communicated with the intake duct; an air-fuel heat exchanger, the inlet of which is connected to the outlet of the first control valve; a gas wave divider, the medium-pressure inlet of which is connected to the outlet of the air-fuel heat exchanger, and the low-pressure outlet of the gas wave divider is connected to the power cabin ventilation flow path.

[0008] Further, an intake duct air extraction air scoop is arranged in the intake duct, and the inlet of the first control valve is connected to the intake duct air extraction air scoop.

[0009] Further, the intake duct includes a turbine engine flow path, a ramjet engine flow path, and an air intake regulating plate. The air intake regulating plate is hinged to the intake duct, and the air intake regulating plate can control the opening degrees of the turbine engine flow path and the ramjet engine flow path.

[0010] Further, an intake duct casing air extraction hole is arranged on the side wall of the intake duct corresponding to the turbine engine flow path. The high-pressure outlet of the gas wave divider is connected to the intake duct casing air extraction hole, and when the air intake regulating plate closes the turbine engine flow path, the air intake regulating plate corresponds to the position of the intake duct casing air extraction hole and forms an active air supply seal.

[0011] Further, a second control valve is arranged on the connecting pipeline between the high-pressure outlet of the gas wave divider and the intake duct casing air extraction hole.

[0012] Further, the end of the air intake regulating plate is provided with an air intake regulating plate labyrinth structure and an air intake regulating plate sealing air collecting cavity. The air intake regulating plate sealing air collecting cavity is located in the middle of the end of the air intake regulating plate, and the air intake regulating plate labyrinth structure is arranged on the periphery of the air intake regulating plate sealing air collecting cavity.

[0013] The present invention also provides a combined engine intake air sealing and environmental control integrated thermal management method, which is carried out by using the above combined engine intake air sealing and environmental control integrated thermal management system.

[0014] Further, the combined engine intake air sealing and environmental control integrated thermal management method includes: when the air intake regulating plate does not close the turbine engine flow path, both the first control valve and the second control valve are closed, and the air-fuel heat exchanger and the gas wave divider do not work; when the air intake regulating plate completely closes the turbine engine flow path, both the first control valve and the second control valve are opened, and the air-fuel heat exchanger and the gas wave divider work.

[0015] Further, when both the first control valve and the second control valve are opened, ram air enters the first control valve through the inlet duct air intake scoop, and high-pressure air and low-temperature and low-pressure air are generated through the action of the air-fuel heat exchanger and the gas wave pressure divider. The high-pressure air is introduced to the inlet duct casing air intake hole through the second control valve, and the low-temperature and low-pressure air is introduced into the power cabin ventilation flow path to cool the accessories in the power cabin.

[0016] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the present invention at least include:

[0017] The gas wave pressure dividing device can achieve the separation of high- and low-pressure airflows without relying on external energy input. By utilizing the extremely low ambient pressure during high-altitude flight, the low-pressure exhaust pressure of the gas wave pressure divider can be further reduced, thereby obtaining high-pressure exhaust with higher pressure and low-pressure exhaust with lower temperature.

[0018] The non-contact intake air regulating plate sealing scheme with active air supply significantly reduces the leakage compared with the non-contact sealing without air supply, and significantly improves the reliability compared with the contact sealing scheme.

[0019] Compared with the scheme of using only the heat exchanger for precooling, an additional stage of precooling is added, which can provide a gas source with a lower temperature and effectively expand the applicable envelope of the thermal management scheme. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0021] Figure 1 is a structural diagram of the inlet duct and the regulating plate;

[0022] FIG. 2 is a structural diagram of the labyrinth teeth on the side wall surface of the intake air regulating plate;

[0023] Figure 3 is a cross-sectional view of the inlet duct casing and the intake air regulating plate;

[0024] Figure 4 is a schematic flow path diagram of the air collecting cavity of the intake air regulating plate.

[0025] Reference numerals in the drawings: 1. Intake air regulating plate; 2. Air intake hole; 3. Axis of rotation of the intake air regulating plate; 4. Inlet duct air intake scoop; 5. First control valve; 6. Air-fuel heat exchanger; 7. Gas wave pressure divider; 8. Power cabin partition; 9. Power cabin skin; 10. Labyrinth tooth structure; 11. Air collecting cavity; 12. Second control valve. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0027] The following specific examples illustrate the implementation manners of the present application. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope of protection of the present application.

[0028] As Figures 1 to 4 shown, an embodiment of the present invention provides a combined engine intake air sealing and environmental control integrated thermal management system. The intake duct is connected to the power cabin, and the power cabin is provided with a power cabin ventilation flow path, including: a first control valve 5, an air-fuel heat exchanger 6, and a gas wave divider 7. The inlet of the first control valve 5 is communicated with the intake duct; the inlet of the air-fuel heat exchanger 6 is connected to the outlet of the first control valve 5; the medium-pressure inlet of the gas wave divider 7 is connected to the outlet of the air-fuel heat exchanger 6, and the low-pressure outlet of the gas wave divider 7 is connected to the power cabin ventilation flow path.

[0029] The embodiment of the present invention realizes the effective connection and thermal management between the intake duct and the power cabin by integrating the first control valve 5, the air-fuel heat exchanger 6, and the gas wave divider 7. Among them, the gas wave divider 7 divides the medium-pressure gas into two paths of high-pressure and low-pressure outputs: the high-pressure is used for the sealing of the intake regulating plate 1 to reduce leakage; the low-pressure is used for the cooling of the power cabin and is discharged through the power cabin ventilation flow path E. This design improves the thermal management efficiency and the reliability of the engine, and at the same time reduces the energy consumption and maintenance cost.

[0030] The first control valve 5 is preferably arranged as close as possible to the intake duct A. It remains closed in both the single working mode of the turbine engine and the combined working mode of the turbine and ramjet, and is only opened in the single mode of the ramjet engine to realize the function of bleeding air from the intake duct.

[0031] An air intake duct A is provided with an air intake duct bleed air scoop 4, and the inlet of the first control valve 5 is connected to the air intake duct bleed air scoop 4. An air intake duct bleed air scoop 4 is provided in the air intake duct A, and its function is to guide the air flow into the air intake duct, ensure the air flow required for the engine, and maintain stable and reliable operation within the entire flight range of the aircraft and various operating conditions. The inlet of the first control valve 5 is connected to the air intake duct bleed air scoop 4, and such a design allows for precise control of the air flow in the air intake duct to adapt to different flight states and engine requirements. This configuration helps to improve the total pressure recovery coefficient of the air intake duct, reduce the energy loss during the deceleration and pressurization of the air flow in the air intake duct, thereby improving the intake efficiency. At the same time, this connection method also helps to ensure a uniform and low-distortion flow field at the outlet of the air intake duct, providing good air flow quality, which is crucial for the performance of the engine and the aerodynamic layout of the aircraft.

[0032] The air intake duct includes a turbojet engine flow path, a ramjet engine flow path, and an intake regulating plate 1. The intake regulating plate 1 is hinged to the air intake duct and rotates around the intake regulating plate rotation axis 3, and the intake regulating plate 1 can control the opening degrees of the turbojet engine flow path and the ramjet engine flow path.

[0033] The intake regulating plate 1 is hinged to the air intake duct and can flexibly control the opening degrees of the turbojet engine flow path and the ramjet engine flow path. This design allows for precise adjustment of the intake air volume according to flight conditions and engine operating modes, optimizing the air flow distribution, thereby improving the engine efficiency and performance. At the same time, this flexible air flow control also helps to achieve the best thrust output during different flight phases, enhance the maneuverability and adaptability of the aircraft, and ensure the best aerodynamic performance and engine response under various flight states.

[0034] An air intake duct casing air intake hole 2 is provided on the side wall of the air intake duct corresponding to the turbojet engine flow path. The high-pressure outlet of the shock wave divider 7 is connected to the air intake duct casing air intake hole 2, and when the intake regulating plate 1 closes the turbojet engine flow path, the intake regulating plate 1 corresponds to the position of the air intake duct casing air intake hole 2 and forms an active air supply seal.

[0035] The main beneficial effect of this design is that it can actively provide sealing air flow when needed to maintain the seal between the intake regulating plate 1 and the turbojet engine flow path, prevent high-pressure air leakage, thereby protecting the interior of the turbojet engine from damage by high-temperature gases, and improving the reliability and life of the engine. At the same time, this active air supply sealing method reduces friction and wear compared to traditional contact seals, reduces maintenance costs, and improves the sealing efficiency.

[0036] A second control valve 12 is provided on the connecting pipeline between the high-pressure outlet of the gas wave divider 7 and the air intake port of the air intake casing 2. The main function of this design is to control the flow rate and pressure of the high-pressure gas flowing to the air intake port of the air intake casing 2 to adapt to different working modes and flight conditions. By precisely controlling the opening and closing of the second control valve 12, the sealing effect between the air intake regulating plate 1 and the air intake port of the air intake casing 2 can be effectively managed, ensuring the formation of a reliable active air supply seal when needed. Such a design improves the flexibility and response speed of the system, helps optimize the engine performance, reduces the risk of air leakage, and protects the turbine engine from high-temperature gas damage, thus enhancing the reliability and efficiency of the entire air intake system.

[0037] The annular channel formed by the power cabin partition 8 and the power cabin skin 9 around the engine body is the power cabin. Air is drawn through an opening in the power cabin partition. The low-pressure exhaust nozzle of the gas wave divider 7 is connected to the opening in the power cabin partition through a pipeline. The low-pressure exhaust flow path G cooled by the gas wave divider serves as the ventilation and cooling air source for the power cabin. The power cabin ventilation flow path E is discharged through an opening in the skin or at the engine nozzle, cooling the engine and its accessories along the way.

[0038] The second control valve 12 is preferably arranged as close as possible to the air intake A and remains closed in both the single working mode of the turbine engine and the combined working mode of the turbine and ramjet. This prevents the gas in the air intake A from flowing back into the gas wave divider and then into the engine cabin. In the single mode of the ramjet engine, it is opened to achieve the air supply function for the sealing cavity.

[0039] The pressurizing effect of the high-pressure output nozzle of the gas wave divider 7 can compensate for the air flow loss inside the heat exchanger, and can pressurize the low-temperature air at the outlet of the heat exchanger to slightly higher than the air intake back pressure. The temperature rise brought by pressurization is less than the cooling temperature drop of the heat exchanger. The air flow temperature at the high-pressure outlet of the gas wave divider is still lower than the air intake bleed temperature. As the air source for sealing the air intake regulating plate, on the one hand, it can prevent the air flow in the air intake from entering the sealing cavity, and on the other hand, it can cool down some of the high-temperature gas entering the sealing cavity through mixing to achieve efficient sealing.

[0040] The gas wave divider 7 has a two-dimensional structure expanded along the rotation axis. The wave rotor rotates driven by medium-pressure intake air. The wave rotor is divided by partitions to form circumferentially uniformly distributed flow channels. According to the engine requirements, the design indexes of the gas wave divider are obtained. The main indexes include the high-pressure exhaust pressure ratio, the low-pressure exhaust temperature drop, and the high-low pressure exhaust flow ratio. The gas wave divider scheme is selected according to the main design indexes.

[0041] The end of the air intake regulating plate 1 is provided with an air intake regulating plate labyrinth structure 10 and an air intake regulating plate sealing air collecting cavity 11. The air intake regulating plate sealing air collecting cavity 11 is located in the middle of the end of the air intake regulating plate 1, and the air intake regulating plate labyrinth structure 10 is arranged on the outer periphery of the air intake regulating plate sealing air collecting cavity 11.

[0042] The design of the labyrinth structure 10 at the end of the intake air regulating plate 1 and the intake air regulating plate sealed air collecting cavity 11 enables the regulating plate to form an effective sealed space through the air collecting cavity 11 when closing the flow path of the turbine engine. The labyrinth structure 10 surrounds the outer periphery of the air collecting cavity 11, enhancing the sealing effect and preventing the leakage of high-pressure air flow. This structure not only improves the sealing performance of the intake duct, reduces the risk of damage to the interior of the turbine engine by hot gases, but also optimizes the operating conditions of the engine by precisely controlling the air flow, improving the efficiency and reliability of the entire aeroengine.

[0043] The sealed air supply flow path of the intake air regulating plate 1 is as shown in the appendix Figure 4 As shown. The principle of sealing is that high-pressure sealed air is supplied into the sealed cavity to establish a cavity pressure in the sealed cavity slightly higher than the back pressure of the intake duct. The flow direction of the sealed air flow is from the sealed cavity into the turbine engine passage B and the ramjet engine passage C. Parameters such as the number of labyrinth teeth, clearance, and the number of air supply pipes can be designed according to actual requirements.

[0044] It should be noted that each flow path in this solution is respectively: intake duct A, turbine engine flow path B, ramjet engine flow path C, intake air regulating plate sealed air supply flow path D, power cabin ventilation flow path E, intake duct air scoop induced air flow path F, and gas wave divider low-pressure exhaust flow path G.

[0045] The present invention also provides a combined engine intake air sealing and environmental control integrated thermal management method, which is carried out by using a combined engine intake air sealing and environmental control integrated thermal management system. The combined engine intake air sealing and environmental control integrated thermal management method includes:

[0046] When the intake air regulating plate 1 does not close the turbine engine flow path, both the first control valve 5 and the second control valve 12 are closed, and the air-fuel heat exchanger 6 and the gas wave divider 7 do not work;

[0047] When the intake air regulating plate 1 completely closes the turbine engine flow path, both the first control valve 5 and the second control valve 12 are opened, and the air-fuel heat exchanger 6 and the gas wave divider 7 work.

[0048] When both the first control valve 5 and the second control valve 12 are opened, the ram air enters the first control valve 5 through the intake duct air scoop 4, and high-pressure air and low-temperature and low-pressure air are generated through the action of the air-fuel heat exchanger 6 and the gas wave divider 7. The high-pressure air is introduced to the intake duct casing air intake hole 2 through the second control valve 12, and the low-temperature and low-pressure air is introduced into the power cabin ventilation flow path to cool the accessories in the power cabin.

[0049] As described above, it is only the specific implementation manner of the present application. However, the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A thermal management system combining engine air intake sealing and environmental control, wherein the air intake duct is connected to the power compartment, and the power compartment is provided with a power compartment ventilation flow path, characterized in that: include: a first control valve (5), an inlet of which is in communication with the air inlet passage; an air-fuel heat exchanger (6), the inlet of which is connected to the outlet of the first control valve (5); An air wave pressure divider (7), wherein the medium-pressure inlet is connected to the outlet of the air-fuel heat exchanger (6), and the low-pressure outlet of the air wave pressure divider (7) is connected to the ventilation flow path of the power cabin; The air inlet duct comprises a turbine engine flow path, a ramjet engine flow path and an air inlet adjustment plate (1), the air inlet adjustment plate (1) being hingedly connected to the air inlet duct, and the air inlet adjustment plate (1) being capable of controlling the opening of the turbine engine flow path and the ramjet engine flow path; An air inlet casing air bleed hole (2) is provided on a side wall of the air inlet corresponding to the turbine engine flow path, a high-pressure outlet of the air wave divider (7) is connected to the air inlet casing air bleed hole (2), and when the air inlet adjustment plate (1) closes the turbine engine flow path, the air inlet adjustment plate (1) corresponds to the position of the air inlet casing air bleed hole (2) and forms an active air supply seal.

2. The integrated thermal management system for combined engine air intake sealing and environmental control according to claim 1, characterized in that: An air intake duct scoop (4) is provided in the air intake duct, and an inlet of the first control valve (5) is connected to the air intake duct scoop (4).

3. The integrated thermal management system for combined engine air intake sealing and environmental control according to claim 1, characterized in that: A second control valve (12) is provided on the connecting pipeline between the high-pressure outlet of the air wave pressure divider (7) and the air inlet casing air bleed hole (2).

4. The integrated thermal management system for combined engine air intake sealing and environmental control according to claim 3, characterized in that: An air intake adjustment plate grate structure (10) and an air intake adjustment plate sealed air collecting chamber (11) are provided at the end of the air intake adjustment plate (1); the air intake adjustment plate sealed air collecting chamber (11) is located in the middle of the end of the air intake adjustment plate (1), and the air intake adjustment plate grate structure (10) is provided on the periphery of the air intake adjustment plate sealed air collecting chamber (11).

5. A method for integrated thermal management of combined engine air intake seal and environmental control, using the integrated thermal management system of combined engine air intake seal and environmental control according to any one of claims 1 to 4, characterized in that: The integrated thermal management method for combined engine intake sealing and environmental control comprises: When the air intake regulating plate (1) does not close the turbine engine flow path, the first control valve (5) and the second control valve (12) are both closed, and the air-fuel heat exchanger (6) and the air wave pressure divider (7) do not operate; When the air intake adjustment plate (1) completely closes the turbine engine flow path, the first control valve (5) and the second control valve (12) are both opened, and the air-fuel heat exchanger (6) and the air wave pressure divider (7) operate.

6. The integrated thermal management method for combined engine intake seal and environmental control according to claim 5, characterized in that: When both the first control valve (5) and the second control valve (12) are opened, the ram air enters the first control valve (5) through the air intake duct bleed air scoop (4), and generates high-pressure air and low-temperature low-pressure air through the action of the air-fuel heat exchanger (6) and the air wave pressure divider (7). The high-pressure air is introduced into the air intake duct casing bleed air hole (2) through the second control valve (12), and the low-temperature low-pressure air is introduced into the power compartment ventilation flow path to cool the accessories in the power compartment.

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