Combined engine air inlet sealing and environmental control integrated thermal management system and method

Abstract

According to the combined engine air inlet sealing and environmental control integrated thermal management system, an air inlet channel is connected with an engine compartment, the engine compartment is provided with an engine compartment ventilation flow path, and the combined engine air inlet sealing and environmental control integrated thermal management system comprises a first control valve, a second control valve, a third control valve and a fourth control valve, an inlet of the air-fuel heat exchanger is connected with an outlet of the first control valve; and a medium-pressure inlet of the air wave pressure divider is connected with an outlet of the air and fuel oil heat exchanger, and a low-pressure outlet of the air wave pressure divider is connected with the engine compartment ventilation flow path. According to the embodiment of the invention, the first control valve, the air fuel heat exchanger and the air wave pressure divider are integrated, so that effective connection and heat management of the air inlet channel and the power cabin are realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to an integrated thermal management system and method for combined engine air intake sealing and environmental control. Background Art

[0002] The turbine-based combined cycle engine (hereinafter referred to as the combined engine) has the characteristics of conventional horizontal take-off and landing, reusability, wide application, good safety, and the ability to use ordinary fuels. It has become one of the future development directions of aerospace vehicle power devices recognized by countries around the world.

[0003] The two engines of the combined engine share one air intake duct. By installing an adjustable adjustment plate (hereinafter referred to as the "intake adjustment plate") in the air intake duct, the intake volume of the two engine channels is adjusted to achieve the conversion of the three working modes. In the mode where the ramjet engine works alone, the air intake adjustment plate is actuated to completely close the turbine engine channel. However, due to the gap between the adjustment plate and the air intake duct casing, some airflow will still leak into the turbine engine that has stopped working. The working Ma of the ramjet engine is usually above 3. At this time, the total intake temperature is as high as 600K or more. The leakage of high-temperature gas will cause the residual lubricating oil in the turbine engine to coke, which will cause the turbine engine to be unable to restart in the air. The air intake adjustment plate needs to be sealed to prevent the leakage of high-temperature airflow into the turbine engine.

[0004] The seals commonly used in aircraft engines are divided into non-contact seals and contact seals. The leakage of non-contact seals alone is relatively large. Since ramjet engines do not have pressurized components, the air flow pressure in the intake duct is the highest pressure in the entire machine, and it is difficult to obtain a high-pressure sealing air source, so there is also a lack of active air supply and sealing conditions. Contact seals usually use structures such as C-type metal sealing plates, but since the combined engine needs to actuate the intake adjustment plate, the friction generated by the contact seal will cause additional loads on the actuator, and the sealing plate is prone to wear or deformation during reciprocating motion, resulting in reduced sealing performance or even failure. Efficient sealing of adjustable components is a key issue that needs to be solved in combined engines.

[0005] At the same time, the heat load of the combined engine when running at high Mach numbers is much higher than that of a conventional engine. However, due to material limitations of electronic components, sealing devices, etc., it is difficult to improve the temperature resistance of some engine accessories. Therefore, it is necessary to control the ambient temperature of the engine compartment to provide suitable working conditions for the accessories. The total intake temperature above Mach 3 has exceeded the temperature resistance of most accessories, and the intake duct bleed air cannot be directly used for cooling and ventilation of the power compartment. The usual practice is to use the fuel heat sink carried by the engine to pre-cool the bleed air before ventilating and cooling the power compartment. Summary of the invention

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

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

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

[0009] Furthermore, the air inlet duct includes a turbine engine flow path, a ramjet engine flow path and an air inlet adjustment plate, the air inlet adjustment plate is hinged to the air inlet duct, and the air inlet adjustment plate can control the opening of the turbine engine flow path and the ramjet engine flow path.

[0010] Furthermore, an air inlet casing air bleed hole is provided on the side wall of the air inlet duct corresponding to the turbine engine flow path, and the high-pressure outlet of the air wave pressure divider is connected to the air inlet casing air bleed hole, and when the air inlet adjustment plate closes the turbine engine flow path, the air inlet adjustment plate corresponds to the position of the air inlet casing air bleed hole and forms an active air supply seal.

[0011] Furthermore, a second control valve is provided on the connecting pipeline between the high-pressure outlet of the gas wave pressure divider and the air inlet casing air bleed hole.

[0012] Furthermore, an air intake adjustment plate grate structure and an air intake adjustment plate sealed air collecting chamber are provided at the end of the air intake adjustment plate. The air intake adjustment plate sealed air collecting chamber is located in the middle of the end of the air intake adjustment plate, and the air intake adjustment plate grate structure is provided on the periphery of the air intake adjustment plate sealed air collecting chamber.

[0013] The present invention also provides a method for integrated thermal management of combined engine air intake seal and environmental control, which is performed using the above-mentioned integrated thermal management system for combined engine air intake seal and environmental control.

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

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

[0016] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted by the present invention include at least: The air wave pressure divider equipment 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 air wave pressure divider can be further reduced, thereby obtaining higher pressure high-pressure exhaust and lower temperature low-pressure exhaust.

[0017] The non-contact air intake regulating plate sealing solution with active air supply greatly reduces leakage compared with non-contact sealing without air supply, and significantly improves reliability compared with contact sealing solutions.

[0018] Compared with the solution of using heat exchanger pre-cooling alone, the addition of a first-stage pre-cooling can provide a lower temperature gas source, effectively expanding the applicable envelope of the thermal management solution. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0020] Figure 1 It is the structural diagram of the air inlet and the regulating plate; FIG2 is a structural diagram of the grate teeth on the side wall of the air intake adjustment plate; Figure 3 It is a cross-sectional view of the air intake casing and the air intake adjustment plate; Figure 4 It is a schematic diagram of the flow path of the air intake adjustment plate collecting cavity.

[0021] The reference numerals in the figure are: 1. air intake adjustment plate; 2. air bleed hole; 3. rotation axis of the air intake adjustment plate; 4. air intake duct air scoop; 5. first control valve; 6. air-fuel heat exchanger; 7. air wave pressure divider; 8. power compartment partition; 9. power compartment skin; 10. comb tooth structure; 11. air collecting cavity; 12. second control valve. DETAILED DESCRIPTION

[0022] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0023] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0024] like Figures 1 to 4 As shown, an embodiment of the present invention provides an integrated thermal management system for 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, including: a first control valve 5, an air-fuel heat exchanger 6, and an air wave pressure divider 7. The inlet of the first control valve 5 is in communication with the air 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 air wave pressure divider 7 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 power compartment ventilation flow path.

[0025] The embodiment of the present invention realizes effective connection and thermal management between the air intake duct and the power cabin by integrating the first control valve 5, the air-fuel heat exchanger 6 and the air wave pressure divider 7. The air wave pressure divider 7 divides the medium-pressure gas into two outputs, high pressure and low pressure: the high pressure is used for sealing the air intake adjustment plate 1 to reduce leakage; the low pressure is used for cooling the power cabin and is discharged through the power cabin ventilation flow path E. This design improves the thermal management efficiency and engine reliability, while reducing energy consumption and maintenance costs.

[0026] The first control valve 5 is arranged as close to the inlet duct A as possible, and is kept closed in both the turbine engine single working mode and the turbine ramjet joint working mode, and is only opened in the ramjet engine single mode to realize the inlet duct air bleed function.

[0027] An inlet duct bleed air scoop 4 is provided in the inlet duct A, and the inlet of the first control valve 5 is connected to the inlet duct bleed air scoop 4. An inlet duct bleed air scoop 4 is provided in the inlet duct A, and its function is to guide the airflow into the inlet duct, ensure the air flow required by the engine, and maintain stable and reliable operation in the entire flight range of the aircraft and under various working conditions. The inlet of the first control valve 5 is connected to the inlet duct bleed air scoop 4. Such a design allows the air flow in the inlet duct to be precisely controlled to adapt to different flight conditions and engine requirements. This configuration helps to improve the total pressure recovery coefficient of the inlet duct, reduce the energy loss of the airflow when decelerating and pressurizing in the inlet duct, and thus improve the intake efficiency. At the same time, this connection method also helps to ensure that the inlet duct outlet flow field is uniform and less distorted, and provides good airflow quality, which is crucial to the performance of the engine and the aerodynamic layout of the aircraft.

[0028] The air inlet duct includes a turbine engine flow path, a ramjet engine flow path and an air inlet adjustment plate 1, which is hinged to the air inlet duct and rotates around the air inlet adjustment plate rotation axis 3, and the air inlet adjustment plate 1 can control the opening of the turbine engine flow path and the ramjet engine flow path.

[0029] The air intake adjustment plate 1 is hinged to the air intake duct, and can flexibly control the opening of the turbine engine flow path and the ramjet engine flow path. This design allows the intake volume to be accurately adjusted according to the flight conditions and engine operating mode, and the airflow distribution is optimized, thereby improving the engine efficiency and performance. At the same time, this flexible airflow control also helps to achieve the best thrust output in different flight phases, enhance the maneuverability and adaptability of the aircraft, and ensure that the best aerodynamic performance and engine response can be maintained in various flight conditions.

[0030] An air inlet casing air bleed hole 2 is arranged on the side wall of the air inlet duct corresponding to the flow path of the turbine engine. The high-pressure outlet of the air wave divider 7 is connected to the air inlet casing air bleed hole 2. When the air inlet adjustment plate 1 closes the flow path of the turbine engine, 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.

[0031] The main beneficial effect of this design is that it can actively provide sealing airflow when needed to maintain the seal between the air intake adjustment plate 1 and the turbine engine flow path, prevent high-pressure airflow leakage, thereby protecting the interior of the turbine engine from damage by high-temperature gas and improving the reliability and life of the engine. At the same time, compared with traditional contact seals, this active air supply sealing method reduces friction and wear, reduces maintenance costs, and improves sealing efficiency.

[0032] A second control valve 12 is provided on the connecting pipeline between the high-pressure outlet of the air wave divider 7 and the air intake hole 2 of the air intake casing. The main function of this design is to control the flow and pressure of the high-pressure gas flowing to the air intake hole 2 of the air intake casing 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 adjustment plate 1 and the air intake hole 2 of the air intake casing can be effectively managed to ensure that a reliable active air supply seal is formed when needed. Such a design improves the flexibility and response speed of the system, helps to optimize engine performance, reduce the risk of air leakage, and protect the turbine engine from damage by high-temperature gas, thereby enhancing the reliability and efficiency of the entire air intake system.

[0033] The annular channel formed by the power compartment bulkhead 8, the power compartment skin 9 and the engine body is the power compartment. Air is drawn in through an opening in the power compartment bulkhead. The low-pressure exhaust nozzle of the air wave divider 7 is connected to the opening of the power compartment bulkhead through a pipeline. The low-pressure exhaust flow path G cooled by the air wave divider serves as the ventilation and cooling air source for the power compartment. The power compartment ventilation flow path E is discharged through the opening in the skin or from the engine nozzle, cooling the engine accessories along the way.

[0034] The second control valve 12 is arranged as close to the inlet duct A as possible, and is kept closed in both the turbine engine single working mode and the turbine ramjet joint working mode to prevent the gas in the inlet duct A from flowing back into the gas wave divider and then into the engine compartment. The second control valve 12 is opened in the ramjet engine single mode to realize the air supply function of the sealed chamber.

[0035] The pressurizing effect of the high-pressure output nozzle of the air wave pressure divider 7 can make up for the air flow loss inside the heat exchanger. The low-temperature air at the heat exchanger outlet can be pressurized to a level slightly higher than the inlet duct back pressure. The temperature rise caused by the pressurization is less than the temperature drop caused by the cooling of the heat exchanger. The air flow temperature at the high-pressure outlet of the air wave pressure divider is still lower than the inlet duct bleed temperature. As the sealing air source for the inlet regulating plate, it can, on the one hand, prevent the inlet duct airflow from entering the sealing cavity. On the other hand, it can cool down part of the high-temperature gas entering the sealing cavity through mixing, thereby achieving efficient sealing.

[0036] The air wave pressure divider 7 is a structure that is two-dimensionally unfolded along the rotation axis. The wave rotor rotates under the drive of the medium-pressure intake air. The wave rotor is divided by partitions to form circumferentially uniformly distributed flow channels. The design indicators of the air wave pressure divider are obtained according to the engine requirements. The main indicators include the high-pressure exhaust gas boost ratio, the low-pressure exhaust gas temperature drop, and the high- and low-pressure exhaust gas flow ratio. The air wave pressure divider scheme is selected according to the main design indicators.

[0037] The end of the air intake adjustment plate 1 is provided with an air intake adjustment plate grate structure 10 and an air intake adjustment plate sealed air collecting chamber 11. 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 arranged on the periphery of the air intake adjustment plate sealed air collecting chamber 11.

[0038] The design of the intake regulating plate grate structure 10 and the intake regulating plate sealing gas collecting cavity 11 at the end of the intake regulating plate 1 enables the regulating plate to form an effective sealing space through the gas collecting cavity 11 when closing the turbine engine flow path, and the grate structure 10 surrounds the outer periphery of the gas collecting cavity 11, thereby enhancing the sealing effect and preventing leakage of high-pressure airflow. This structure not only improves the sealing performance of the intake duct and reduces the risk of hot gas damaging the inside of the turbine engine, but also optimizes the working conditions of the engine by precisely controlling the airflow, thereby improving the efficiency and reliability of the entire aircraft engine.

[0039] The sealed air supply path of the air intake adjustment plate 1 is shown in the attached Figure 4 As shown, the sealing principle is that high-pressure sealing air is supplied into the sealing chamber to establish a sealing chamber pressure slightly higher than the back pressure of the inlet duct. The flow direction of the sealing airflow is discharged from the sealing chamber into the turbine engine channel B and the ramjet engine channel C. The number of comb teeth, gap, number of air supply pipes and other parameters can be designed according to actual needs.

[0040] It should be noted that the flow paths in this scheme are: air inlet A, turbine engine flow path B, ramjet engine flow path C, air inlet adjustment plate seal supply air path D, power compartment ventilation flow path E, air inlet scoop draught path F and air wave divider low-pressure exhaust flow path G.

[0041] The present invention also provides a combined engine air intake seal and environmental control integrated thermal management method, which is implemented by using a combined engine air intake seal and environmental control integrated thermal management system. The combined engine air intake seal and environmental control integrated thermal management method includes: 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 work; 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 work.

[0042] When the first control valve 5 and the second control valve 12 are both opened, the ram air enters the first control valve 5 through the inlet 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 divider 7. The high-pressure air is introduced into the inlet casing air bleed 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.

[0043] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A thermal management system for combined 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); The medium-pressure inlet of the air wave pressure divider (7) 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.

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: 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 hinged 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.

4. The integrated thermal management system for combined engine air intake sealing and environmental control according to claim 3, characterized in that: 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.

5. The integrated thermal management system for combined engine air intake sealing and environmental control according to claim 4, 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).

6. The integrated thermal management system for combined engine air intake sealing and environmental control according to claim 5, 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).

7. 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 6, 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.

8. The integrated thermal management method for combined engine intake seal and environmental control according to claim 7, 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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