Thermodynamic test bench with pressure large amplitude transient regulation

Abstract

The invention discloses a thermodynamic test bench with pressure large amplitude transient regulation, and belongs to the technical field of thermodynamic test equipment, the thermodynamic test bench comprises a thermal test bench, the front and rear sides of a thermal test sleeve are respectively communicated with a gas injection pipe and a material injection pipe, and the thermal test sleeve is provided with a gas injection regulation mechanism for regulating the gas injection pressure and temperature. An exhaust adjusting mechanism is arranged on the thermal test sleeve and used for adjusting exhaust pressure. Through cooperation of the exhaust partition plate and the electric push rod, when the electric push rod rapidly moves the exhaust partition plate, the volume of an exhaust cavity of a combustion chamber can be instantly changed, a sudden pressure drop or rise working condition is created, and pressure transient change in flight of an airspace engine is accurately simulated, and through cooperation of an air pressure monitoring plug and a compression spring, when the air inlet pressure is lower than a threshold value, the air pressure can be monitored. And the pre-tightening force of the compression spring is adjusted through the hydraulic push rod, so that the minimum air inlet pressure threshold value can be flexibly set, and different test scenes of the airspace engine can be adapted.

Description

Technical Field

[0001] The present invention relates to the technical field of thermodynamic testing, in particular to a thermodynamic testing platform with large pressure transient regulation. Background Art

[0002] The aviation thermal power test bench is mainly used for testing in the aircraft environmental control system laboratory, which includes comprehensive experiments on its air source system, air conditioning component performance tests, wing anti-icing system tests, low-pressure duct flow distribution tests, etc. The temperature and flow of the gas injected in the test can be achieved through fast response valves.

[0003] When an aerospace engine switches from high pressure and high temperature on the ground to low pressure and low temperature at high altitude, the amount of oxygen at the intake end suddenly decreases, resulting in incomplete combustion of fuel in the combustion chamber and fluctuations in the output thermal power. Traditional thermal power test benches cannot dynamically simulate the extreme working conditions of sudden changes in air pressure during flight, making it difficult to verify the stability of the engine's thermal power output under transient pressure. Summary of the Invention

[0004] The purpose of the present invention is to solve the problems existing in the prior art and to propose a thermal power test bench with large pressure transient regulation.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions: A thermal power test bench with large-amplitude transient pressure regulation includes a thermal test bench for combustion chamber thermal power testing, wherein the thermal test bench is fixedly mounted with a thermal test sleeve via a test stabilization frame, wherein the front and rear sides of the thermal test sleeve are respectively connected to an air injection pipe and a material injection pipe, wherein the thermal test sleeve is provided with an air injection regulating mechanism for regulating the air injection pressure and temperature, and the thermal test sleeve is provided with an exhaust regulating mechanism for regulating the exhaust pressure; The gas injection regulating mechanism includes a gas injection spacer provided at the front side of the combustion chamber, the gas injection spacer is installed with a hydraulic push rod through a support frame, the hydraulic push rod is connected to a compression spring through a hydraulic rod, and an air pressure monitoring plug is fixed on the compression spring; The exhaust adjustment mechanism includes an adjustment mounting seat sleeved on the outside of the injection tube, and a plurality of electric push rods are fixedly mounted on the adjustment mounting seat. The front side of the electric push rod is fixedly connected to an exhaust baffle arranged between the injection tube and the thermal test sleeve, and the exhaust baffle is provided with an exhaust port corresponding to the combustion position of the combustion chamber.

[0006] Preferably, an electric igniter is provided on one side of the combustion chamber close to the injection pipe, and a combustion groove located outside the electric igniter is opened on the combustion chamber.

[0007] Preferably, the gas injection spacer is provided with a plurality of gas injection holes distributed in a circular array and an air pressure monitoring slide groove located at the output end of the gas injection pipe, and the gas pressure monitoring plug is provided with a gas injection resistance groove.

[0008] Preferably, the cross section of the gas injection spacer is configured to be conical, and the front side of the air pressure monitoring plug is engaged with the air pressure monitoring slide groove.

[0009] Preferably, the inner wall of the gas injection partition is connected to a semi-enclosed auxiliary heating sleeve, and the auxiliary heating sleeve is connected to the injection pipe, and is used to transfer the heat of combustion in the combustion chamber to the gas injection partition to preheat the injected air. A drive bracket is installed at the pipe mouth end of the auxiliary heating sleeve, and a preheating simulation push rod is provided on the side of the drive bracket facing the gas injection partition.

[0010] Preferably, the inner walls of the gas injection pipe and the material injection pipe are provided with a fast response pressure regulating valve, the combustion chamber is sleeved and fixed on the outer surface of the material injection pipe, and an air supply sleeve located at the combustion groove is provided between the material injection pipe and the combustion chamber.

[0011] Preferably, a combustion monitoring mechanism is provided on the exhaust baffle for monitoring the fuel combustion state in the combustion chamber. The combustion monitoring mechanism includes monitors arranged in a ring shape on the exhaust baffle. Two of the monitors form a group, and the setting orientation of each group of monitors corresponds to the setting orientation of the electric igniter.

[0012] Preferably, the thermal test sleeve is provided with a simulation mechanism outside, which is used to simulate the gas composition during actual combustion in the combustion chamber. The simulation mechanism includes a simulation chamber arranged outside the thermal test sleeve, and the simulation chamber is provided with injection valves distributed in a ring array, and the injection valves are arranged on the gas injection side of the combustion chamber.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 1. The present invention uses an exhaust baffle in conjunction with an electric push rod. When the electric push rod quickly moves the exhaust baffle, it can instantly change the volume of the exhaust cavity of the combustion chamber, create a pressure drop or rise condition, and accurately simulate the pressure transients during the flight of the aerospace engine.

[0014] 2. The present invention uses an air pressure monitoring plug in conjunction with a compression spring to close the air injection channel when the intake pressure is lower than a threshold value, thereby preventing combustion failure when the combustion chamber is at low pressure. The preload force of the compression spring is adjusted by a hydraulic push rod, and the minimum intake pressure threshold can be flexibly set to adapt to different test scenarios of aerospace engines.

[0015] 3. This invention utilizes a movable auxiliary heating sleeve mechanism to accurately and flexibly simulate two key real-world operating conditions for aerospace engines: preheating low-temperature intake air at high altitude and near-Earth-level normal-temperature intake air. This significantly improves the accuracy and reliability of thermodynamic test data and provides a more realistic testing environment for engine performance verification. Furthermore, utilizing combustion chamber waste heat to preheat air eliminates the need for a complex heating system and improves the energy efficiency of fuel combustion. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The overall structure of a thermal power test bench with large pressure transient regulation proposed by the present invention is shown in FIG. Figure 1 ; Figure 2 The overall structure of a thermal power test bench with large pressure transient regulation proposed by the present invention is shown in FIG. Figure 2 ; Figure 3 This is an exploded view of the overall structure of a thermal power test bench with large pressure transient regulation proposed by the present invention; Figure 4 This is a schematic diagram of the structure of the exhaust baffle in a thermal power test bench with large pressure transient regulation proposed by the present invention; Figure 5 This is a schematic diagram of the internal structure of the cross section of the thermal test sleeve, gas injection cylinder and injection pipe in a thermal dynamic test bench with large-scale transient pressure regulation proposed by the present invention; Figure 6 For the present invention Figure 5 A magnified view of the structure at center A; Figure 7 This is a schematic cross-sectional diagram of the internal structure of the gas injection diaphragm in a thermal power test bench with large-scale transient pressure regulation proposed by the present invention.

[0017] Figure numerals: 1. Thermal test bench; 11. Test stabilizing frame; 2. Thermal test sleeve; 21. Combustion chamber; 22. Electric igniter; 3. Gas injection pipe; 31. Gas injection spacer; 311. Gas injection hole; 312. Support frame; 32. Hydraulic push rod; 321. Air pressure monitoring plug; 33. Auxiliary heating sleeve; 34. Preheating simulation push rod; 341. Drive bracket; 4. Injection pipe; 41. Electric push rod; 42. Exhaust baffle; 421. Monitor; 5. Simulation chamber; 51. Injection valve. DETAILED DESCRIPTION

[0018] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0019] In the description of the present invention, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0020] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "provided with," "mounted / connected," and "connected" should be understood in a broad sense. For example, "connected" can mean a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be internal communication between two components. Those skilled in the art will be able to understand the specific meanings of the above terms in the present invention in specific circumstances.

[0021] Example, see Figures 1 to 7 A thermal power test bench with large-amplitude transient pressure regulation includes a thermal test bench 1 for thermal power testing of a combustion chamber 21. The thermal test bench 1 is fixedly mounted with a thermal test sleeve 2 via a test stabilization frame 11. The front and rear sides of the thermal test sleeve 2 are respectively connected to an air injection pipe 3 and a material injection pipe 4. The thermal test sleeve 2 is provided with an air injection regulating mechanism for regulating the air injection pressure and temperature. The thermal test sleeve 2 is provided with an exhaust regulating mechanism for regulating the exhaust pressure. Furthermore, an electric igniter 22 is provided on the side of the combustion chamber 21 close to the injection pipe 4, and a combustion groove located outside the electric igniter 22 is opened on the combustion chamber 21, so that the high-pressure mixed gas injected from the gas injection pipe 3 and the injection pipe 4 can be ignited in the combustion chamber 21 and ignited by the electric igniter 22 to provide thrust for the aerospace engine.

[0022] It should be noted that: during the operation of the aerospace engine, due to the different altitudes of the external environment, the atmospheric pressure and temperature on the ground are higher than the atmospheric pressure and temperature in the air. Based on this, the aerospace engine in the air at high altitude still maintains the same intake pressure as that near the ground, which will cause the fuel in the combustion chamber 21 to reduce the amount of oxygen at the intake end, resulting in incomplete combustion, making the thermal power supply of the aerospace engine unstable. This is the intake environment of the existing aerospace engine combustion chamber 21 near the ground and at high altitude, and will not be repeated later.

[0023] like Figure 3 、 Figure 5 and Figure 6 As shown, the gas injection regulating mechanism includes a gas injection spacer 31 arranged at the front side of the combustion chamber 21. The gas injection spacer 31 is installed with a hydraulic push rod 32 through a support frame 312. The hydraulic push rod 32 is connected to a compression spring through a hydraulic rod. An air pressure monitoring plug 321 is fixed on the compression spring. When gas is injected into the gas injection pipe 3, the high gas pressure at the gas injection end causes the air pressure monitoring plug 321 to retreat, thereby opening the gas injection channel in the gas injection spacer 31. At the same time, the electrically controlled hydraulic push rod 32 can drive the compression distance between the compression spring and the air pressure monitoring plug 321 to adjust the air intake pressure of the air pressure monitoring plug 321, thereby achieving the purpose of monitoring the air intake pressure from the gas injection pipe 3. Furthermore, the gas injection spacer 31 is provided with a plurality of gas injection holes 311 distributed in a circular array and a gas pressure monitoring chute located at the output end of the gas injection pipe 3, and a gas injection resistance groove is provided on the gas pressure monitoring plug 321. The cross section of the gas injection spacer 31 is set to be conical, and the front side of the gas pressure monitoring plug 321 is engaged with the gas pressure monitoring chute. When the gas injection pipe 3 injects gas into the thermal test sleeve 2, the gas is blown toward the gas injection resistance groove through the outlet of the gas injection pipe 3, which can make the gas pressure monitoring plug 321 squeeze the compression spring backward, and when the inlet pressure at the outlet of the gas injection pipe 3 is less than the pressure of the compression spring, the gas pressure monitoring plug 321 touches the gas pressure monitoring chute and closes the gas injection channel in the gas injection spacer 31, wherein the gas injection channel is the flow path for the gas at the outlet of the gas injection pipe 3 to flow from the gas injection hole 311 to the combustion chamber 21 through the gas pressure monitoring chute; Furthermore, the inner wall of the gas injection partition 31 is connected to a semi-enclosed auxiliary heating sleeve 33, which is connected to the injection pipe 4 and is used to transfer the heat of combustion in the combustion chamber 21 to the gas injection partition 31 to preheat the injected air. A driving bracket 341 is installed at the mouth of the auxiliary heating sleeve 33, and a preheating simulation push rod 34 is provided on the side of the driving bracket 341 facing the gas injection partition 31. When it is necessary to simulate the preheating of the air intake end of the aerospace engine (when flying at high altitude, the air temperature outside the engine is low and preheating is required), the auxiliary heating sleeve 33 is extended into the space surrounded by the gas injection partition 31 through the preheating simulation push rod 34 to transfer the heat on the combustion side of the combustion chamber 21 to the gas injection partition 31. The amount of air is transported into the gas injection partition 31 through the gas injection partition 31 to preheat the air entering the thermal test sleeve 2, accelerating the combustion speed of the air and fuel injected therein by the electric igniter 22. When there is no need to simulate the preheating of the air intake end of the aerospace engine (in near-ground flight, the air temperature outside the engine is normal and preheating is not required), the auxiliary heating sleeve 33 is completely moved into the injection pipe 4 through the preheating simulation push rod 34, and the air passing through the gas injection channel is not preheated, thereby realizing the flexible switching of two completely different intake temperature conditions within the same test device, greatly improving the fidelity of the test environment simulation, and making the data obtained from the thermal dynamic test more accurate; It should be noted that the process of adjusting the gas injection into the combustion chamber 21 is divided into a gas injection pressure monitoring process to avoid the gas injection pressure being too low; and a gas injection preheating process, in which the air flowing through the gas injection channel in the gas injection partition 31 is preheated to shorten the ignition temperature difference of the air and fuel mixture gas.

[0024] like Figure 4 and Figure 7 As shown, the exhaust adjustment mechanism includes an adjustment mounting seat sleeved on the outside of the injection pipe 4, and a plurality of electric push rods 41 are fixedly mounted on the adjustment mounting seat. The front side of the electric push rods 41 is fixedly connected to an exhaust baffle 42 arranged between the injection pipe 4 and the thermal test sleeve 2. The exhaust baffle 42 is provided with an exhaust port corresponding to the combustion position of the combustion chamber 21, so that after combustion in the combustion chamber 21, the combustion exhaust gas can be directly discharged to the outside of the thermal test sleeve 2 through the exhaust port; Furthermore, a fast-response pressure-regulating valve is provided on the inner wall of the gas injection pipe 3 and the material injection pipe 4. The combustion chamber 21 is sleeved and fixed on the outer surface of the material injection pipe 4. An air supply sleeve located at the combustion groove is provided between the material injection pipe 4 and the combustion chamber 21, thereby ensuring that the fuel and air in the combustion chamber 21 are in a high-pressure state, promoting the mixing process of the two, and through the annular exhaust baffle 42 provided between the material injection pipe 4 and the thermal test sleeve 2 (the exhaust end of the combustion chamber 21), the gas discharge can be blocked and the gas discharge speed can be slowed down, thereby forming an exhaust high-pressure state, which also forms a high-pressure effect on the gas injection end, and the position of the exhaust baffle 42 is controlled by the electric push rod 41. After the exhaust baffle 42 is moved out of the exhaust end of the combustion chamber 21, the exhaust high-pressure state can be suddenly reduced, and a pressure-reducing effect can also be formed on the gas injection end, thereby realizing transient pressure regulation of the combustion chamber 21 during the thermal dynamic test. It should be noted that the electric push rod 41 controls the extension length, and can move the exhaust baffle 42 out from between the injection pipe 4 and the thermal test sleeve 2, thereby increasing the space of the exhaust cavity of the combustion chamber 21; like Figure 7 As shown, a combustion monitoring mechanism is provided on the exhaust baffle 42 for monitoring the fuel combustion state of the combustion chamber 21. The combustion monitoring mechanism includes a monitor 421 arranged in a ring shape on the exhaust baffle 42. Two monitors 421 form a group. The setting orientation of each group of monitors 421 corresponds to the setting orientation of the electric igniter 22.

[0025] It should be noted that the monitor 421 in the present invention can be configured as a temperature, pressure, flow, and emission sensor to monitor the combustion condition of the combustion chamber 21 and determine whether the fuel in the combustion chamber 21 is fully burned when the intake pressure and exhaust pressure in the combustion chamber 21 change. For example, when the fuel in the combustion chamber 21 is not fully burned, the calorific value provided by the fuel is less than the target calorific value. At this time, the monitored temperature is lower than the standard temperature. When the fuel in the combustion chamber 21 is not fully burned, the amount of combustion exhaust gas produced is reduced, resulting in deviations between the monitored gas flow and emission components and the flow and emission indicators of the standard combustion process. Therefore, based on the fuel combustion condition in the combustion chamber 21, it can be directly determined whether the thermal power mechanism of the aerospace engine can still provide stable thrust when the pressure changes greatly and instantaneously. Based on the above, in the process of the electric push rod 41 instantaneously moving the exhaust baffle 42, it can also simulate the transient change of pressure caused by the exhaust space, causing turbulence in the aerospace engine combustion chamber 21. At this time, the combustion monitoring mechanism can monitor the flow changes of the exhaust gas flow, and the thermal power supply of the combustion chamber 21 of the aerospace engine under turbulence can be known.

[0026] like Figure 5As shown, the thermal test sleeve 2 is provided with a simulation mechanism on the outside, which is used to simulate the gas composition during actual combustion in the combustion chamber 21. The simulation mechanism includes a simulation chamber 5 which is sleeved on the outside of the thermal test sleeve 2. The simulation chamber 5 is provided with injection valves 51 distributed in a ring array. The injection valves 51 are arranged on the gas injection side of the combustion chamber 21.

[0027] It should be noted that: when it is necessary to simulate the operating state of the aerospace engine, such as when it passes through clouds and rain curtains, mist droplets are injected into the thermal test sleeve 2 in the simulation chamber 5 through the injection valve 51, so as to simulate the high-humidity environment in the process of the aerospace engine passing through clouds and rain curtains; and when the aerospace engine is flying at high altitude, inert gas (nitrogen) is injected into the thermal test sleeve 2 through the injection valve 51, so as to simulate the low oxygen content in the high-altitude environment. Therefore, by simulating various extreme conditions of the combustion chamber 21 in the simulation chamber 5 when the aerospace engine is actually operating, the authenticity and accuracy of the monitoring data of the combustion monitoring mechanism are improved.

[0028] Working principle: The present invention is divided into a pressure regulation process and a combustion monitoring process for the combustion chamber 21 during the thermal dynamic test process of performing large-scale transient pressure regulation. The pressure regulation process is as follows: an annular exhaust baffle 42 is provided at the exhaust end of the combustion chamber 21 to block gas discharge and slow down the gas discharge speed, thereby forming an exhaust high-pressure state, which also has a high-pressure effect on the gas injection end. The position of the exhaust baffle 42 is controlled by the electric push rod 41. After the exhaust baffle 42 is moved out of the exhaust end of the combustion chamber 21, the exhaust high-pressure state is suddenly reduced, and a pressure reduction effect is also formed on the gas injection end, thereby realizing transient pressure regulation during the thermal dynamic test of the combustion chamber 21. Based on the above, an air injection regulating structure is also provided at the air inlet end to regulate and monitor the air injection pressure and temperature. The regulating and monitoring process is as follows: when the air injection pipe 3 injects air into the thermal test sleeve 2, the air is blown to the air injection resistance groove through the outlet of the air injection pipe 3, which can make the air pressure monitoring plug 321 squeeze the compression spring backward, and when the air inlet pressure at the outlet of the air injection pipe 3 is less than the pressure of the compression spring, the air pressure monitoring plug 321 touches the air pressure monitoring slide groove, and closes the air injection channel in the air injection partition 31, as well as the subsequent injection of the material injection pipe 4 to respond quickly to the pressure regulating valve, so as to prevent the combustion chamber 21 from burning in a low-pressure environment, and the heat on the combustion side of the combustion chamber 21 can be transported into the air injection partition 31 through the auxiliary heating sleeve 33, so as to preheat the air entering the thermal test sleeve 2, thereby accelerating the combustion speed of the air and fuel injected therein by the electric igniter 22; The combustion monitoring process of the combustion chamber 21 is as follows: the monitor 421 in the present invention can be set as temperature, pressure, flow and emission sensors to monitor the combustion status of the combustion chamber 21, and know whether the fuel in the combustion chamber 21 is fully burned when the intake pressure and exhaust pressure in the combustion chamber 21 change. For example, when the fuel in the combustion chamber 21 is not fully burned, the calorific value it provides is less than the target calorific value. At this time, the monitored temperature is lower than the standard temperature. When the fuel in the combustion chamber 21 is not fully burned, the amount of combustion exhaust gas produced is reduced, so that the monitored gas flow and emission components deviate from the flow and emission indicators of the standard combustion process. Therefore, according to the fuel combustion situation of the combustion chamber 21, it can be directly known whether the thermal power mechanism of the aerospace engine can still provide stable thrust when the pressure changes instantly with a large value.

[0029] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A thermal dynamic test bench with large pressure transient regulation, comprising a thermal test bench (1) for thermal dynamic testing of a combustion chamber (21), characterized in that: The thermal test bench (1) is fixedly mounted with a thermal test sleeve (2) via a test stabilizing frame (11); the front and rear sides of the thermal test sleeve (2) are respectively connected to an air injection pipe (3) and a material injection pipe (4); the thermal test sleeve (2) is provided with an air injection regulating mechanism for regulating the air injection pressure and temperature; the thermal test sleeve (2) is provided with an exhaust regulating mechanism for regulating the exhaust pressure; The gas injection regulating mechanism comprises a gas injection spacer (31) arranged at the front side of the combustion chamber (21), the gas injection spacer (31) being equipped with a hydraulic push rod (32) via a support frame (312), the hydraulic push rod (32) being connected to a compression spring via a hydraulic rod, and a gas pressure monitoring plug (321) being fixed to the compression spring; The exhaust adjustment mechanism includes an adjustment mounting seat sleeved on the outside of the injection pipe (4), a plurality of electric push rods (41) are fixedly mounted on the adjustment mounting seat, and the front side of the electric push rods (41) is fixedly connected to an exhaust baffle (42) arranged between the injection pipe (4) and the thermal test sleeve (2), and the exhaust baffle (42) is provided with an exhaust port corresponding to the combustion part of the combustion chamber (21).

2. A thermal power test bench with large pressure transient regulation according to claim 1, characterized in that: An electric igniter (22) is provided on one side of the combustion chamber (21) close to the injection pipe (4), and a combustion groove located outside the electric igniter (22) is provided on the combustion chamber (21).

3. The thermal power test bench with large pressure transient regulation according to claim 1, characterized in that: The gas injection spacer (31) is provided with a plurality of gas injection holes (311) distributed in a ring array and a gas pressure monitoring slide groove located at the output end of the gas injection pipe (3), and the gas pressure monitoring plug (321) is provided with a gas injection resistance groove.

4. The thermal power test bench with large pressure transient regulation according to claim 3, characterized in that: The cross section of the gas injection spacer (31) is configured to be conical, and the front side of the air pressure monitoring plug (321) is engaged with the air pressure monitoring chute.

5. The thermal power test bench with large pressure transient regulation according to claim 3, characterized in that: The inner wall of the gas injection partition (31) is connected to a semi-enclosed auxiliary heating sleeve (33), and the auxiliary heating sleeve (33) is connected to the injection pipe (4) and is used to transfer the heat of combustion in the combustion chamber (21) to the gas injection partition (31) to preheat the injected air. A driving bracket (341) is installed at the pipe mouth end of the auxiliary heating sleeve (33), and a preheating simulation push rod (34) is provided on the side of the driving bracket (341) facing the gas injection partition (31).

6. The thermal power test bench with large pressure transient regulation according to claim 2, characterized in that: The inner walls of the gas injection pipe (3) and the material injection pipe (4) are provided with a fast response pressure regulating valve, the combustion chamber (21) is sleeved and fixed on the outer surface of the material injection pipe (4), and an air supply sleeve located at the combustion groove is provided between the material injection pipe (4) and the combustion chamber (21).

7. The thermal power test bench with large pressure transient regulation according to claim 1, characterized in that: A combustion monitoring mechanism is provided on the exhaust baffle (42) for monitoring the fuel combustion state of the combustion chamber (21). The combustion monitoring mechanism includes a monitor (421) arranged in an annular shape on the exhaust baffle (42). Two monitors (421) form a group. The arrangement orientation of each group of monitors (421) corresponds to the arrangement orientation of the electric igniter (22).

8. The thermal power test bench with large pressure transient regulation according to claim 1, characterized in that: The thermal test sleeve (2) is provided with a simulation mechanism on its outer shell for simulating the gas composition during actual combustion in the combustion chamber (21). The simulation mechanism includes a simulation chamber (5) sleeved on the outside of the thermal test sleeve (2). The simulation chamber (5) is provided with injection valves (51) distributed in a ring array. The injection valves (51) are arranged on the gas injection side of the combustion chamber (21).

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