Binary strong precooling air inlet system with runner switching function and power device

Abstract

The invention discloses a binary strong pre-cooling air inlet system with a flow channel switching function and a power device, and belongs to the field of hypersonic flight vehicle power devices. The device comprises a binary air inlet channel, a strong pre-cooling section with a flow channel switching function, an inlet transition section and a power device. A pre-cooling channel is closed under the low Mach number through a two-dimensional flow channel switching function based on rotation adjustment, so that air flow bypasses a strong pre-cooler and directly enters a turbine engine, and the total air inlet pressure loss is reduced; and the pre-cooling channel is opened under the high Mach number, so that the airflow flows through the strong pre-cooler to be pre-cooled, the service life of engine parts is prolonged, the performance of the engine is improved, and the low Mach number performance and the high Mach number performance of the strong pre-cooling turbine engine are both considered.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of hypersonic vehicle power devices, and relates to a binary strong pre-cooling inlet system with a flow passage switching function and a power device. BACKGROUND

[0002] In order to realize horizontal take-off and landing of a hypersonic vehicle, a turbine-based combined cycle engine is used, which is powered by a turbine engine at a low speed and propelled by a ramjet at a high speed. In order to realize the connection of the turbine ramjet, the turbine engine needs to work at least at Ma=3, while the working upper limit of the traditional turbine engine is basically Ma≤2. In order to solve the adverse effects of high-temperature air intake on the working performance, materials and structure of the turbine engine, considering the technical difficulty, development cycle and cost, the current fast and feasible way is to install a pre-cooling device in front of the traditional turbine engine to form a pre-cooled turbine engine. At present, the pre-cooled turbine engine mainly includes a jet pre-cooled turbine engine and a strong pre-cooled turbine engine.

[0003] The turbine-based combined cycle engine used by the horizontal take-off and landing hypersonic vehicle is formed by combining a turbine engine and a ramjet, wherein the turbine engine needs to work at least at Ma3 to realize the connection of the turbine engine. According to the current technical level, the working upper limit of the traditional turbine engine basically does not exceed Ma2, and there is a problem of rapid decay of engine thrust when the working Mach number approaches the upper limit. By increasing a strong pre-cooling device in front of the traditional turbine engine to form a strong pre-cooled turbine engine, the adverse effects of high-temperature air intake at high Mach numbers can be solved, but there is a large total pressure loss when the airflow flows through the strong pre-cooler at low Mach numbers, which will cause the problem of large low-Mach-number thrust loss of the propulsion system based on the strong pre-cooled turbine engine. Therefore, a binary strong pre-cooling inlet system with a flow passage switching function and a power device need to be designed, which makes the airflow bypass the strong pre-cooler and directly enters the turbine engine at low Mach numbers to reduce the inlet total pressure loss, and pre-cools the airflow at high Mach numbers to prolong the service life of the engine components and improve the engine performance.

[0004] The application solves the problems of narrow working boundary, rapid decay of high-Mach-number thrust of the propulsion system based on the traditional turbine engine and large low-Mach-number thrust loss of the propulsion system based on the strong pre-cooled turbine engine. SUMMARY

[0005] The object of the present invention is to provide a binary strong pre-cooling intake system and a power device with a flow channel switching function. The binary flow channel switching function based on rotation adjustment closes the pre-cooling channel at low Mach numbers to allow the airflow to bypass the strong pre-cooler and directly enter the turbine engine to reduce the total pressure loss of the intake air. At high Mach numbers, the pre-cooling channel is opened to allow the airflow to flow through the strong pre-cooler to pre-cool the airflow, thereby extending the service life of engine components and improving engine performance, thereby taking into account both the low Mach number and high Mach number performance of the strong pre-cooling turbine engine.

[0006] The technical solution of the present invention:

[0007] A binary strong pre-cooling air intake system with a flow channel switching function and a power device, comprising a binary air intake 1, a strong pre-cooling section 2 with a flow channel switching function, an intake transition section 3, and a power device 4, specifically:

[0008] The dual air inlet 1 includes an air inlet compression section 1-1, an air inlet expansion section 1-3, and an air inlet straightening section 1-4. In order to improve the starting performance of the air inlet under low Mach number flight conditions, multiple air inlet bleed grooves 1-2 are arranged on the multi-stage compression surface of the air inlet compression section 1-1; the air inlet bleed grooves 1-2 are connected to the air inlet compression section 1-1.

[0009] The forced pre-cooling section 2 with flow channel switching function consists of a binary uniform straight section 2-1, a binary convergent section 2-2, a rectangular forced pre-cooler 2-3, and a binary adjustment plate 2-4. The rectangular forced pre-cooler 2-3 is positioned obliquely within the binary uniform straight section 2-1 and fixed to the walls of the binary uniform straight section 2-1 at its side ends. The front section of the binary adjustment plate 2-4 is hinged to the rear end of the rectangular forced pre-cooler 2-3, allowing for rotational adjustment within the binary convergent section 2-2. Dynamic sealing is provided between the binary convergent section 2-2's side walls to reduce airflow leakage. In the high Mach number pre-cooling state, the binary adjusting plate 2-4 is rotated clockwise to adjust the rear end of the binary adjusting plate 2-4 to contact the lower wall of the binary convergent section 2-2, so that the airflow entering the binary straight section 2-1 flows through the rectangular strong pre-cooler 2-3 and then enters the pre-cooling channel 2-2-1 formed by the binary adjusting plate 2-4 and the upper wall of the binary convergent section 2-2; while in the low Mach number non-pre-cooling state, the binary adjusting plate 2-4 is rotated counterclockwise to adjust the rear end of the binary adjusting plate 2-4 to contact the upper wall of the binary convergent section 2-2, so that the airflow entering the binary straight section 2-1 directly enters the non-pre-cooling channel 2-2-2 formed by the binary adjusting plate 2-4 and the lower wall of the binary convergent section 2-2.

[0010] Furthermore, an air inlet, an air outlet, a cooling medium inlet, and a cooling medium outlet are provided on the rectangular strong precooler 2-3. The air inlet is provided on the side of the rectangular strong precooler 2-3 close to the lower wall of the binary equal straight section 2-1, and the air outlet is provided on the side of the rectangular strong precooler 2-3 close to the upper wall of the binary equal straight section 2-1.

[0011] Furthermore, the heat exchange core inside the rectangular strong precooler 2-3 is not limited to various forms such as round tubes and plate fins.

[0012] The power unit 4 is a conventional turbine engine, comprising a turbine core 4-1, an afterburner 4-2, and an axisymmetric convergent-divergent nozzle 4-3.

[0013] The strong pre-cooling section 2 with flow channel switching function is fixedly connected to the binary air inlet 1 through the rear end of the air inlet straightening section 1-4 and the front end of the binary straight section 2-1. The strong pre-cooling section 2 with flow channel switching function is fixedly connected to the forward transition section 3 through the rear end of the binary convergent section 2-2 and the front end of the forward transition section 3; and the forward transition section 3 is connected to the power unit 4 through the rear end of the forward transition section 3 and the front end of the turbine core engine 4-1, and the connection adopted needs to use a method such as socketing that can compensate for the thermal expansion of the structure.

[0014] The forward transition section 3 is used to transition the square section of the strong pre-cooling section 2 with a flow channel switching function to the cylindrical section of the power device 4.

[0015] The beneficial effects of the present invention are as follows: the present invention can realize the switching function of the upper and lower parallel channels of the binary strong pre-cooling intake system through a flow channel switching mechanism based on rotation adjustment, and has the ability to close the pre-cooling channel at low Mach number to allow the airflow to bypass the strong pre-cooler and directly enter the turbine engine to reduce the total intake pressure loss, and open the pre-cooling channel at high Mach number to allow the airflow to flow through the strong pre-cooler to pre-cool the airflow to extend the service life of engine components and improve engine performance. It can take into account the low Mach number and high Mach number performance of the strong pre-cooling turbine engine, so that the strong pre-cooling turbine engine has better wide speed range performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Structure diagram of dual strong pre-cooling air intake system and power unit;

[0017] Figure 2 Dual air intake structure diagram;

[0018] Figure 3 Cross-sectional view of the strong pre-cooling section structure with flow channel switching function;

[0019] Figure 4 Schematic diagram of airflow before and after flow channel switching, where (a) is the high Mach number pre-cooling state and (b) is the low Mach number non-pre-cooling state;

[0020] Figure 5 Power unit structure diagram.

[0021] In the figure: 1 binary inlet channel, 2 strong pre-cooling section with flow channel switching function, 3 inlet-to-propulsion transition section, 4 power device, 1-1 inlet channel compression section, 1-3 inlet channel expansion section, 1-2 inlet channel air release groove, 1-4 inlet channel rectification section, 2-1 binary straight section, 2-2 binary convergent section, 2-3 rectangular strong pre-cooler, 2-4 binary adjusting plate, 4-1 turbine core engine, 4-2 afterburner, 4-3 axisymmetric convergent-divergent nozzle. DETAILED DESCRIPTION

[0022] A binary strong pre-cooling inlet system with flow channel switching function and a power device, comprising a binary inlet channel 1, a strong pre-cooling section 2 with flow channel switching function, an inlet-to-propulsion transition section 3, and a power device 4, specifically:

[0023] The binary inlet channel 1 comprises an inlet channel compression section 1-1, an inlet channel expansion section 1-3, and an inlet channel rectification section 1-4. To improve the starting performance of the inlet channel under low Mach number flight conditions, a plurality of inlet channel air release grooves 1-2 are arranged on the multi-stage compression surface of the inlet channel compression section 1-1. The inlet channel air release grooves 1-2 are in communication with the inlet channel compression section 1-1.

[0024] The strong pre-cooling section 2 with flow channel switching function comprises a binary straight section 2-1, a binary convergent section 2-2, a rectangular strong pre-cooler 2-3, and a binary adjusting plate 2-4. The rectangular strong pre-cooler 2-3 is obliquely arranged in the binary straight section 2-1 and fixed on the side walls of the binary straight section 2-1 through the side ends. The front section of the binary adjusting plate 2-4 is hingedly connected to the rear end of the rectangular strong pre-cooler 2-3, can be rotated for adjustment in the binary convergent section 2-2, and performs dynamic sealing between the side walls of the binary convergent section 2-2 to reduce air leakage. In the high Mach number pre-cooling state, the binary adjusting plate 2-4 is rotated clockwise, the rear end of the binary adjusting plate 2-4 is adjusted to be in contact with the lower wall of the binary convergent section 2-2, so that the air flow entering the binary straight section 2-1 flows through the rectangular strong pre-cooler 2-3 and then enters the pre-cooling passage 2-2-1 formed by the binary adjusting plate 2-4 and the upper wall of the binary convergent section 2-2; while in the low Mach number non-pre-cooling state, the binary adjusting plate 2-4 is rotated counterclockwise, the rear end of the binary adjusting plate 2-4 is adjusted to be in contact with the upper wall of the binary convergent section 2-2, so that the air flow entering the binary straight section 2-1 directly enters the non-pre-cooling passage 2-2-2 formed by the binary adjusting plate 2-4 and the lower wall of the binary convergent section 2-2.

[0025] Further, the rectangular strong pre-cooler 2-3 is provided with an air inlet, an air outlet, a cooling medium inlet, and a cooling medium outlet. The air inlet is arranged on the side of the rectangular strong pre-cooler 2-3 close to the lower wall of the binary straight section 2-1, and the air outlet is arranged on the side of the rectangular strong pre-cooler 2-3 close to the upper wall of the binary straight section 2-1.

[0026] Further, the heat exchange core inside the rectangular strong pre-cooler 2-3 is not limited to various forms such as circular tubes and plate fins.

[0027] The power device 4 is a conventional turbine engine, comprising a turbine core engine 4-1, a booster combustion chamber 4-2, and an axisymmetric converging-diverging nozzle 4-3.

[0028] The strong pre-cooling section 2 with the flow channel switching function is connected with the two-dimensional inlet channel 1 through the rear end of the inlet channel fairing section 1-4 and the front end of the two-dimensional straight section 2-1, and is connected with the inlet-to-ram transition section 3 through the rear end of the two-dimensional converging section 2-2 and the front end of the inlet-to-ram transition section 3; the inlet-to-ram transition section 3 is connected with the power device 4 through the rear end of the inlet-to-ram transition section 3 and the front end of the turbine core engine 4-1, and the connection needs to use a sleeving connection or other connection mode that can compensate for the structural thermal expansion.

[0029] The inlet-to-ram transition section 3 is used to transition the square section of the strong pre-cooling section 2 with the flow channel switching function to the cylindrical section of the power device 4.

[0030] Compared with the conventional turbine engine, the turbine engine based on the strong pre-cooled inlet air designed according to the application can widen the upper limit of engine operation and delay the thrust decay at high Mach numbers.

[0031] The strong pre-cooling inlet air system with the flow channel switching function designed according to the application can avoid the total pressure loss caused by the airflow flowing through the pre-cooler in the non-pre-cooling state of the conventional strong pre-cooling turbine engine, because the airflow does not need to flow through the strong pre-cooler at low Mach numbers.

[0032] The strong pre-cooling inlet air system with the flow channel switching function and the power device provided by the application have the advantages that: the pre-cooling channel is closed at low Mach numbers to make the airflow bypass the strong pre-cooler and directly enter the turbine engine, so as to reduce the total pressure loss of the inlet air; the pre-cooling channel is opened at high Mach numbers to make the airflow flow through the strong pre-cooler to pre-cool the airflow, so as to prolong the service life of the engine components and improve the engine performance, thereby taking into account the low Mach number and high Mach number performance of the strong pre-cooling turbine engine.

Claims

1. A dual strong pre-cooling intake system and power device with flow channel switching function, characterized in that: It includes a binary air inlet (1), a strong pre-cooling section with a flow channel switching function (2), an inlet transition section (3), and a power unit (4), specifically: The dual air inlet (1) includes an air inlet compression section (1-1), an air inlet expansion section (1-3), and an air inlet straightening section (1-4). To improve the starting performance of the air inlet under low Mach number flight conditions, multiple air inlet bleed grooves (1-2) are arranged on the multi-stage compression surface of the air inlet compression section (1-1); the air inlet bleed grooves (1-2) are communicated with the air inlet compression section (1-1); The strong precooling section (2) with flow channel switching function includes a binary straight section (2-1), a binary convergent section (2-2), a rectangular strong precooler (2-3), and a binary adjustment plate (2-4), wherein the rectangular strong precooler (2-3) is obliquely placed in the binary straight section (2-1) and fixed on the two side walls of the binary straight section (2-1) through the side ends; the front section of the binary adjustment plate (2-4) is hinged to the rear end of the rectangular strong precooler (2-3), and can be rotated and adjusted in the binary convergent section (2-2), and dynamically sealed with the side walls of the binary convergent section (2-2) to reduce airflow leakage; in the high Mach number precooling state, the binary adjustment plate (2-4) is rotated clockwise to adjust The rear end of the binary adjusting plate (2-4) contacts the lower wall of the binary convergent section (2-2), so that the airflow entering the binary straight section (2-1) flows through the rectangular strong precooler (2-3) and then enters the precooling channel (2-2-1) formed by the binary adjusting plate (2-4) and the upper wall of the binary convergent section (2-2); while in the low Mach number non-precooling state, the binary adjusting plate (2-4) is rotated counterclockwise to adjust the rear end of the binary adjusting plate (2-4) to contact the upper wall of the binary convergent section (2-2), so that the airflow entering the binary straight section (2-1) directly enters the non-precooling channel (2-2-2) formed by the binary adjusting plate (2-4) and the lower wall of the binary convergent section (2-2); The power unit (4) is a turbine engine; The strong pre-cooling section (2) with the flow channel switching function is fixedly connected to the binary air inlet (1) through the rear end of the air inlet duct straightening section (1-4) and the front end of the binary straight section (2-1); the strong pre-cooling section (2) with the flow channel switching function is fixedly connected to the forward transition section (3) through the rear end of the binary convergent section (2-2) and the front end of the forward transition section (3); and the forward transition section (3) is connected to the front end of the power unit (4).

2. A dual strong pre-cooling intake system and power device with flow channel switching function according to claim 1, characterized in that: An air inlet, an air outlet, a cooling medium inlet, and a cooling medium outlet are provided on the rectangular strong precooler (2-3). The air inlet is provided on the side of the rectangular strong precooler (2-3) close to the lower wall surface of the binary equal straight section (2-1), and the air outlet is provided on the side of the rectangular strong precooler (2-3) close to the upper wall surface of the binary equal straight section (2-1).

3. A dual strong pre-cooling intake system and power device with flow channel switching function according to claim 2, characterized in that: The internal heat exchange core of the rectangular strong precooler (2-3) is a circular tube or plate fin.

4. The dual strong pre-cooling intake system and power device with flow channel switching function according to claim 1, characterized in that: The power unit (4) includes a turbine core (4-1), an afterburner (4-2) and an axisymmetric convergent-divergent nozzle (4-3).

5. The dual strong pre-cooling intake system and power device with flow channel switching function according to claim 1, characterized in that: The forward transition section (3) is used to transition the square section of the strong pre-cooling section (2) with a flow channel switching function to the cylindrical section of the power device (4).

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