An air turbine engine test platform

Abstract

The application discloses an air turbine engine experiment platform, and relates to the field of aerospace, and aims to solve the problem that an air turbine engine is inconvenient to test performance. The air turbine engine experiment platform comprises a gas generator, an electric duct is arranged at one end of the gas generator, a spark plug is arranged on the outer wall and is in communication, a first nozzle is arranged between the spark plug and the electric duct in the gas generator; a turbine is in communication with the gas generator at one end; a main combustion chamber is in communication with the other end of the turbine, and the main combustion chamber is provided with a first through hole close to the one end of the turbine; and a compressor is coaxially connected with the turbine and is in communication with the first through hole. The electric duct is started to introduce air into the gas generator, the spark plug ignites the fuel injected by the first nozzle, high-temperature gas is generated to drive the turbine to rotate, the compressor is driven to move, air is introduced into the main combustion chamber, and the high-temperature gas and the air are discharged after being combusted in the main combustion chamber. The application uses air as an oxidizing agent to realize the function of an air turbine rocket engine, and is convenient to operate and test the performance of the air turbine engine.

Description

Technical Field

[0001] This invention relates to the aerospace field, and more specifically to an air turbine engine experimental platform. Background Technology

[0002] Currently, the gas generator of existing air turbine rocket engines needs to be replaced by a special liquid rocket. Liquid rockets have a complex structure and large volume, and require a special oxidizer supply to operate the gas generator. Therefore, it is inconvenient to carry out research work when using existing air turbine rocket engines for performance testing. Summary of the Invention

[0003] The purpose of this invention is to provide an air turbine engine experimental platform for convenient operation and testing of air turbine engine performance.

[0004] To achieve the above objectives, the present invention provides the following technical solution: The present invention provides an air turbine engine experimental platform, comprising:

[0005] A gas generator has an electric duct at one end for supplying air into the gas generator and regulating the air speed. A spark plug is connected to the outer wall of the gas generator near the electric duct. A first nozzle is installed inside the gas generator and is located between the spark plug and the electric duct. The first nozzle is used to inject fuel into the gas generator.

[0006] The turbine has its inlet and outlet facing different directions. The turbine's inlet is connected to the end of the gas generator away from the electric duct. The turbine's shaft is equipped with a connecting shaft.

[0007] The main combustion chamber has one end connected to the air outlet, and a first through hole is provided at the end of the main combustion chamber near the air outlet.

[0008] The compressor is coaxially connected to the turbine via a connecting shaft, and the compressor is located on the side of the turbine away from the outlet. The compressor is connected to the first through hole and is used to introduce air into the main combustion chamber.

[0009] Optionally, the above-mentioned air turbine engine test platform also includes a tail nozzle, which is located at the end of the main combustion chamber away from the turbine and is used to eject gas.

[0010] Optionally, in the above-mentioned air turbine engine experimental platform, the gas generator housing is a cylindrical housing, one end of which is provided with an electric duct, and the other end of which is connected to the turbine's air inlet.

[0011] Optionally, in the aforementioned air turbine engine test platform, the main combustion chamber is also equipped with:

[0012] The combustion-supporting component is located at the end furthest from the first through hole;

[0013] The second nozzle is connected to the main combustion chamber and is located between the first through hole and the combustion-supporting component. The second nozzle is used to inject fuel into the main combustion chamber.

[0014] Optionally, in the aforementioned air turbine engine experimental platform, the combustion-supporting components include:

[0015] The first connecting ring is arranged coaxially with the main combustion chamber and is located close to the second nozzle. The first connecting ring is provided with multiple second through holes.

[0016] The second connecting ring is arranged coaxially and spaced apart from the first connecting ring. The second connecting ring is located away from the second nozzle and has multiple third through holes.

[0017] The connecting pipe has two ends connected to the first connecting ring and the second connecting ring respectively. The center of the first connecting ring and the center of the second connecting ring are both on the axial extension line of the connecting pipe. The outer wall of the connecting pipe is provided with multiple fourth through holes.

[0018] Optionally, in the above-mentioned air turbine engine test platform, the diameter of the fourth through hole distributed along the axial direction of the connecting pipe gradually increases, that is, the diameter of the fourth through hole near the first connecting ring is smaller than the diameter of the fourth through hole near the second connecting ring.

[0019] Optionally, in the above-mentioned air turbine engine test platform, the second through holes are arranged at intervals along the circumferential direction of the first connecting ring.

[0020] Optionally, in the above-mentioned air turbine engine test platform, the third through holes are arranged at intervals along the circumferential direction of the second connecting ring.

[0021] Optionally, in the above-mentioned air turbine engine experimental platform, the diameter of the second through hole is larger than the diameter of the third through hole.

[0022] Optionally, in the above-mentioned air turbine engine test platform, the axial direction of the second through hole is parallel to and not collinear with the axial direction of the third through hole.

[0023] Compared with existing technologies, when adopting the above technical solution, the electric duct at one end of the gas generator starts working, continuously supplying speed-regulated air into the gas generator. Then, fuel is injected into the gas generator through the first nozzle, using the continuously supplied air as the oxidant. At this time, the spark plug generates an electric spark to ignite the fuel inside the gas generator, producing high-temperature gas. The generated high-temperature gas enters the turbine, driving it to rotate. The turbine is coaxially connected to the compressor, driving the compressor to rotate as well. After the compressor operates, it passes air through the first through-hole into the main combustion chamber. The high-temperature gas, after its flow direction is changed by the turbine's rotation, enters the main combustion chamber along with the air from the compressor, where it is burned and then discharged. This invention replaces the traditional air-turbine rocket engine's gas generator, which uses liquid rocket as the gas generator. It uses a smaller gas generator that uses air as the oxidant, resulting in a simpler and more compact structure, facilitating operation and testing of the air-turbine engine's performance, and simplifying research. Attached Figure Description

[0024] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0025] Figure 1 This is a schematic diagram of the structure of a gas generator for a space turbine engine experimental platform according to an embodiment of the present invention;

[0026] Figure 2 This is a schematic diagram of the overall structure of a space turbine engine experimental platform according to an embodiment of the present invention;

[0027] Figure 3 This is a schematic diagram of the main combustion chamber of a space turbine engine experimental platform according to an embodiment of the present invention;

[0028] Figure 4 This is a schematic diagram of the combustion-supporting component of a space turbine engine experimental platform according to an embodiment of the present invention;

[0029] Figure 5 This is a temperature change diagram at the inlet and outlet of the gas generator of the space turbine engine experimental platform in an embodiment of the present invention, under the condition that the fuel is ethanol.

[0030] Figure label:

[0031] 1-Gas generator; 101-Electric duct; 102-Spark plug; 103-First nozzle; 2-Turbine; 3-Main

[0032] Combustion chamber; 301-First through hole; 302-Second nozzle; 4-Compressor; 5-Tail nozzle; 6-Combustion-supporting components;

[0033] 601-First connecting ring; 602-Second connecting ring; 603-Connecting pipe; 604-Second through hole; 605-Third connecting ring

[0034] Through hole; 606 - Fourth through hole. Detailed Implementation

[0035] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0036] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0037] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0038] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0039] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0040] like Figures 1-5As shown, an engine test platform provided in this embodiment of the invention includes a gas generator 1, a turbine 2, a main combustion chamber 3, and a compressor 4.

[0041] The gas generator 1 has an electric duct 101 at one end, which is used to supply air into the gas generator 1 and regulate the air speed. A spark plug 102 is connected to the outer wall of the gas generator 1 near the electric duct 101. A first nozzle 103 is installed inside the gas generator 1, between the spark plug 102 and the electric duct 101, and is used to inject fuel into the gas generator 1. The turbine 2 has an air inlet and an air outlet. The turbine 2 is connected to the end of the gas generator 1 away from the electric duct 101, and the turbine 2 is connected to the main combustion chamber 3. One end of the main combustion chamber 3 is connected to the exhaust port, and the end of the main combustion chamber 3 near the exhaust port is provided with a first through hole 301. The compressor 4 is coaxially connected to the turbine 2 through the connecting shaft, and the compressor 4 is located on the side of the turbine 2 away from the exhaust port. The compressor 4 is connected to the first through hole 301 and is used to introduce air into the main combustion chamber 3.

[0042] In specific implementation, such as Figure 1As shown, when the engine test platform starts working, both the inlet of the electric bypass duct 101 and the inlet of the compressor 4 are open. After the electric bypass duct 101 is started, the electric bypass duct 101 at one end of the gas generator 1 begins to work, directly obtaining air from the inlet of the electric bypass duct 101. After stepless speed regulation of the obtained air, a high-speed airflow is formed, and this high-speed airflow is continuously and stably introduced into the gas generator 1. Then, fuel is injected into the gas generator 1 through the first nozzle 103, using the continuously introduced air as an oxidant. At this time, the spark plug 102 generates an electric spark to ignite the fuel inside the gas generator 1, producing high-temperature gas. The high-speed airflow acts as an oxidant, promoting combustion. The combustion process improves combustion efficiency. After the high-speed airflow mixes with the high-temperature gas produced by combustion, it enters the turbine 2 through the air inlet, driving the turbine 2 to rotate. The turbine 2 is coaxially connected to the compressor 4, and drives the compressor 4 to rotate together through the connecting shaft. After the compressor 4 is activated, it passes the air through the first through hole 301 into the main combustion chamber 3. The high-temperature gas changes its flow direction after the turbine 2 rotates and flows out through the air outlet, and enters the main combustion chamber 3 together with the air from the compressor 4. In the high-temperature environment, the compressor 4 continues to continuously supply air into the main combustion chamber 3, ensuring the combustion efficiency and movement speed of the high-temperature gas in the main combustion chamber 3. After being fully combusted in the main combustion chamber 3, the gas is discharged, generating thrust. Compared with traditional air turbine rocket engines, the air turbine engine in this invention decouples the structure of the air turbine rocket engine in principle, dividing it into four working areas: gas generator 1, turbine 2, compressor 4, and main combustion chamber 3. This replaces the traditional air turbine rocket engine where the gas generator 1 is a liquid rocket. Instead, a smaller gas generator 1 is used, which uses air as the oxidant. The structure is simpler and more compact, making it easier to operate and test the performance of the air turbine engine, and facilitating research.

[0043] Furthermore, in this embodiment, the fuel injected into the gas generator 1 by the first nozzle 103 is a fuel that can achieve stable combustion, such as ethanol, aviation kerosene, ethylene, or methanol. There is no specific limitation on the fuel. After the first nozzle 103 injects ethanol into the gas generator 1, air is used as the oxidant, and the spark plug 102 ignites the ethanol fuel. Continuous and stable combustion can be achieved in the gas generator 1, and the temperature generated inside the gas generator 1 meets the requirements of the experimental work, reducing the cost of fuel and oxidant.

[0044] It should be noted that this invention reduces the required size of the engine test platform, allowing for scientific research simulating the operating conditions of an air turbine rocket engine, such as the analysis of gas composition at high temperatures and the efficiency analysis of turbine 2 and the combustion chamber. When using ethanol as fuel, the constructed engine test platform can generate temperatures of approximately 1500K. The gas generator 1 in the air turbine rocket engine developed by the Muroran Institute of Technology can generate combustion temperatures of 900K~1400K, such as... Figure 5 As shown, the combustion temperature generated by the engine experimental platform of this invention is 1000K~1500K. This combustion temperature is slightly higher than that of the gas generator 1 in the air turbine rocket engine developed by the Muroran Institute of Technology, thus meeting the experimental requirements. Furthermore, this invention simplifies the components required for an air turbine rocket, achieves the functionality of an air turbine rocket, and features a relatively simple structure and small size for convenient small-scale research in a laboratory environment.

[0045] Furthermore, the engine test platform in this invention can simulate ignition tests in high-altitude environments by simulating different airflow conditions, providing experimental support for the development of combined propulsion and hypersonic aircraft.

[0046] Specifically, in this embodiment, the speed at which high-temperature gas is generated can be adjusted by regulating the rotational speed of the electric duct 101. The higher the rotational speed of the electric duct 101, the greater the airflow velocity that can be provided within the gas generator 1, thereby increasing the speed of the high-temperature gas generated in the gas generator 1 and improving the power provided by the engine test platform.

[0047] As another possible approach, the composition and temperature of the high-temperature combustion gas can be adjusted by regulating the fuel flow rate of the first nozzle 103. Different fuels produce high-temperature combustion gases with different compositions when burned with air as the oxidant, and the temperatures produced after combustion of different fuels with air also vary. By adjusting the fuel injection flow rate and composition of the first nozzle 103, fuel combustion efficiency and resource utilization can be improved.

[0048] In some embodiments, a bracket is further provided between the first nozzle 103 and the gas generator 1, the bracket being used to fix the first nozzle 103. Exemplarily, the first nozzle 103 and the gas generator 1 can also be connected by welding, threaded connection, or other connection methods that can fix the position of the first nozzle 103; no specific limitation is made here regarding the connection method between the first nozzle 103 and the gas generator 1. The bracket further facilitates the adjustment, disassembly, and installation of the first nozzle 103, improving the flexibility of the first nozzle 103's placement and simplifying operation. The first nozzle 103 and the gas generator 1 are welded together as a single structure, reducing installation steps and improving the structural stability between them.

[0049] like Figure 1 and Figure 3 As shown, specifically in this embodiment, a tailpipe 5 is also included. The tailpipe 5 is located at the end of the main combustion chamber 3 away from the turbine 2, and is used to eject combustion gases. The structure of the tailpipe 5 can protect the structure in the combustion ejection area of ​​the main combustion chamber 3 from burn-out, and extend the service life of the air turbine engine test platform. Specifically, the tailpipe 5 is conical, meaning the diameter of the end connecting the tailpipe 5 to the main combustion chamber 3 is larger than the diameter of the ejection end of the tailpipe 5. This increases the velocity of the high-temperature combustion gases as they flow from the main combustion chamber 3 to the ejection end of the tailpipe 5, thereby increasing the thrust that the air turbine engine can generate.

[0050] like Figure 1 and Figure 2 As shown, specifically in this embodiment, the housing of the gas generator 1 is a cylindrical housing, with an electric duct 101 provided at one end and the other end connected to the air inlet of the turbine 2. The cylindrical housing of the gas generator 1 increases the contact area between the gas generator 1 and the air inlet of the turbine 2, ensuring a tight fit and guaranteeing airtightness and stability of the connection structure throughout the entire operation.

[0051] Specifically, in this embodiment, the main combustion chamber 3 is further provided with a combustion-supporting component 6 and a second nozzle 302. The combustion-supporting component 6 is located at one end near the first through hole 301; the second nozzle 302 communicates with the main combustion chamber 3 and is located between the first through hole 301 and the tail nozzle 5. The second nozzle 302 is used to inject fuel into the main combustion chamber 3. Since there is high-temperature gas in the main combustion chamber 3, the high temperature can meet the requirements for fuel combustion, and there is no need to set up an additional ignition device. Fuel is directly injected into the main combustion chamber 3 through the second nozzle 302. In the high-temperature environment of the main combustion chamber 3, the fuel is burned by using the air injected through the first through hole 301 as an oxidant. Then, the high-temperature gas and air inside the main combustion chamber 3 are fully mixed and burned by the combustion-supporting component 6, and then sprayed out through the tail nozzle 5. The second nozzle 302 and the air injected by the compressor 4 in the main combustion chamber 3 produce high-temperature gas with a higher temperature. This gas mixes with the high-temperature gas output by the gas generator 1, increasing the flow rate of the high-temperature gas and improving the combustion efficiency, thus enabling the air turbine engine to obtain greater thrust.

[0052] It should be noted that one or more first nozzles 103 are provided in the gas generator 1, and one or more second nozzles 302 are provided in the main combustion chamber 3. The first nozzle 103 and the second nozzle 302 are respectively controlled by their respective fuel valves to spray fuel, and they do not interfere with each other. For example, there may be 1, 2, 6, 8, etc., of the first nozzle 103. The number of first nozzles 103 is not specifically limited here. The more first nozzles 103 there are, the better the uniformity of fuel injection and the greater the fuel injection flow rate, thus improving combustion efficiency. Similarly, there may be 1, 2, 4, 9, etc., of the second nozzles 302. The number of second nozzles 302 there are not specifically limited here. The more second nozzles 302 there are, the better the fuel impact atomization effect and the better the uniformity of fuel injection, thus improving combustion efficiency. In some embodiments, the fuel burned in the gas generator 1 and the main combustion chamber 3 is the same, and the size and model of the first nozzle 103 and the second nozzle 302 are the same. In other embodiments, the fuel burned in the gas generator 1 is different from that in the main combustion chamber 3, and the size and model of the first nozzle 103 and the second nozzle 302 are different. This improves the design flexibility of the first nozzle 103 and the second nozzle 302, allowing them to adapt to various working conditions during experiments.

[0053] Specifically, in this embodiment, the combustion-supporting component 6 includes: a first connecting ring 601, a second connecting ring 602, and a connecting pipe 603. The first connecting ring 601 is coaxially arranged with the main combustion chamber 3 and is located near the second nozzle 302. The first connecting ring 601 is provided with a plurality of second through holes 604. The second connecting ring 602 is coaxially spaced from the first connecting ring 601 and is located near the tail nozzle 5. The second connecting ring 602 is provided with a plurality of third through holes 605. The two ends of the connecting pipe 603 are respectively connected to the first connecting ring 601 and the second connecting ring 602. The center of the first connecting ring 601 and the center of the second connecting ring 602 are both on the axial extension line of the connecting pipe 603. The outer wall of the connecting pipe 603 is provided with a plurality of fourth through holes 606. When the high-temperature combustion gas and the air injected through the first through-hole 301 reach the combustion-supporting component 6 together, to prevent the high-temperature combustion gas and air from being discharged from the tail nozzle 5 too quickly, the combustion-supporting component 6 blocks the high-temperature combustion gas and air, reducing their speed and increasing the residence time of the fuel in the combustion-supporting component 6, so that the fuel can achieve complete combustion within the combustion-supporting component 6. Among them, the high-temperature combustion gas is located in the central region of the axis of the main combustion chamber 3, and the air surrounds the high-temperature combustion gas in a circumferential direction. At this time, the outer air flows through multiple second through-holes 604 on the first connecting ring 601 to the outer wall of the connecting pipe 603. The unburned part of the high-temperature combustion gas in the middle region continues to mix and burn with the air surrounding the combustion-supporting component 6 through the fourth through-hole 606. The burned high-temperature combustion gas is discharged to the tail nozzle 5 through the third through-hole 605. The fully burned gas in the high-temperature combustion gas in the middle region does not participate in the combustion process with air and is discharged to the tail nozzle 5 through the other end of the connecting pipe 603. The combustion-supporting component 6 improves the combustion efficiency and increases the gas temperature of the high-temperature combustion gas ejected from the tail nozzle 5, thereby increasing the power of the air turbine engine.

[0054] Specifically, in this embodiment, the diameter of the fourth through holes 606 distributed along the axial direction of the connecting pipe 603 gradually increases, that is, the diameter of the fourth through hole 606 near the first connecting ring 601 is smaller than the diameter of the fourth through hole 606 near the second connecting ring 602. The increasing diameter of the fourth through holes 606 distributed along the axial direction of the connecting pipe 603 facilitates the mixing of the high-temperature combustion gas inside the connecting pipe 603 with the air on the outer wall of the connecting pipe 603, ensuring complete combustion and improving combustion efficiency.

[0055] Specifically, in this embodiment, the second through holes 604 are arranged at intervals along the circumference of the first connecting ring 601. The air surrounding the high-temperature gas flows through the second through holes 604 on the first connecting ring 601 to the outer wall of the connecting pipe 603. The first connecting ring 601 reduces the air velocity and prolongs the residence time of the air in the combustion-supporting component 6, allowing the unburned portion of the fuel in the high-temperature gas to come into contact with the air at the connecting pipe 603 and burn completely, thereby improving the utilization rate of fuel combustion.

[0056] Specifically, in this embodiment, the third through holes 605 are arranged at intervals along the circumference of the second connecting ring 602. The unburned portion of fuel in the high-temperature combustion gas comes into contact with air at the connecting pipe 603 and is fully combusted, then discharged through the third through holes 605 at the second connecting ring 602. The fully combusted and expanded high-temperature combustion gas generates a large flow rate, which is discharged from the tailpipe 5, increasing the thrust of the air turbine engine.

[0057] Specifically, in this embodiment, the diameter of the second through hole 604 is larger than the diameter of the third through hole 605. After air flows into the outer wall of the connecting pipe 603 through the second through hole 604, it flows out through the third through hole 605. The larger diameter of the second through hole 604 makes the air flow more smoothly, while the air encounters resistance when flowing out, thus prolonging the time the air stays in the combustion-supporting component 6, ensuring complete combustion of the fuel, and improving combustion efficiency.

[0058] Specifically, in this embodiment, the axial direction of the second through hole 604 is parallel to and not collinear with the axial direction of the third through hole 605. The second through hole 604 and the third through hole 605 are arranged alternately, so that air cannot move in a straight line along the axial direction of the connecting pipe 603 when it flows in and out, thus avoiding rapid air outflow, prolonging the residence time of air in the combustion-supporting component 6, increasing combustion efficiency, and improving engine power.

[0059] In the description of the above embodiments, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0060] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. An air turbine engine experimental platform, comprising: A gas generator, wherein one end of the gas generator is provided with an electric duct, the electric duct is used to introduce air into the gas generator and regulate the speed of the air, a spark plug is provided in connection with the outer wall of the gas generator near the electric duct, and a first nozzle is provided inside the gas generator and is located between the spark plug and the electric duct, the first nozzle is used to inject fuel into the gas generator. The turbine has an air inlet and an air outlet facing different directions. The air inlet of the turbine is connected to the end of the gas generator away from the electric duct. The turbine has a connecting shaft at its shaft center. The main combustion chamber has one end connected to the air outlet, and a first through hole is provided at the end of the main combustion chamber near the air outlet. A compressor is coaxially connected to the turbine via the connecting shaft, and the compressor is located on the side of the turbine away from the air outlet. The compressor communicates with the first through hole, and the compressor is used to introduce air into the main combustion chamber. The main combustion chamber is also equipped with: The combustion-supporting component is located at the end furthest from the first through hole; The second nozzle is connected to the main combustion chamber and is disposed between the first through hole and the combustion-supporting component. The second nozzle is used to inject fuel into the main combustion chamber. The combustion-supporting component includes: A first connecting ring is arranged coaxially with the main combustion chamber. The first connecting ring is located close to the second nozzle and has multiple second through holes. The second connecting ring is arranged coaxially and spaced apart from the first connecting ring. The second connecting ring is located away from the second nozzle and has multiple third through holes. A connecting pipe, the two ends of which are respectively connected to the first connecting ring and the second connecting ring, the center of the first connecting ring and the center of the second connecting ring are both on the axial extension line of the connecting pipe, and the outer wall of the connecting pipe is provided with a plurality of fourth through holes.

2. The air turbine engine experimental platform according to claim 1, characterized in that, It also includes a tailpipe, which is located at the end of the main combustion chamber away from the turbine, and is used to inject combustion gas.

3. The air turbine engine experimental platform according to claim 1, characterized in that, The housing of the gas generator is a cylindrical housing, one end of which is provided with the electric duct, and the other end of which is connected to the air inlet of the turbine.

4. The air turbine engine experimental platform according to claim 1, characterized in that, The diameter of the fourth through hole distributed along the axial direction of the connecting pipe gradually increases, that is, the diameter of the fourth through hole near the first connecting ring is smaller than the diameter of the fourth through hole near the second connecting ring.

5. The air turbine engine experimental platform according to claim 1, characterized in that, The second through holes are arranged at intervals along the circumferential direction of the first connecting ring.

6. The air turbine engine experimental platform according to claim 1, characterized in that, The third through holes are arranged at intervals along the circumferential direction of the second connecting ring.

7. The air turbine engine experimental platform according to claim 1, characterized in that, The diameter of the second through hole is larger than the diameter of the third through hole.

8. The air turbine engine experimental platform according to claim 1, characterized in that, The axial direction of the second through hole is parallel to and not collinear with the axial direction of the third through hole.

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