Air engine core test air intake pipe network and its control method

Abstract

The application belongs to the technical field of aero-engine core engine test inlet design, and particularly relates to an aero-engine core engine test inlet pipe network and a control method thereof. The design comprises two branches, i.e., a normal state inlet branch and a transition state inlet branch, which supply air to the core engine in normal state test and transition state test, respectively. The temperature, pressure and flow required by the transition state test can be pre-adjusted, and the switching is performed at a certain rate through a valve, which is convenient to operate and can accurately simulate the rapid change of the transition state core engine inlet air inlet condition. Therefore, the transition state performance of the core engine can be reliably verified, the switching process can be smoothly transitioned, and the adjustment overage can be avoided, so that the aerodynamic stability of the core engine can be ensured. In addition, the design can ensure the rapid and high-precision adjustment of the temperature, pressure and flow through the electric regulating valve and the hydraulic regulating valve.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of air engine core test inlet design, and particularly relates to an air engine core test inlet pipe network and a control method thereof. BACKGROUND

[0002] The core engine is a core component of an air engine, and the design stage of the air engine involves testing of the core engine. On the basis of performance verification of the core engine, rapid design of the air engine is completed.

[0003] When the core engine is tested, the core engine is supplied with air by using the inlet pipe network. The inlet pipe network has temperature, pressure, flow and its flow regulation and pressure stabilization capabilities to simulate the inlet conditions of the core engine under different high speeds and Mach numbers. The current inlet pipe network can be well applied to the core engine test under normal conditions, but its cavity is large, and the temperature, pressure and flow are adjusted by relying on electric valves and heat exchangers. Limited by the action time of the electric valve and the performance of the heat exchanger, the temperature adjustment rate can only reach 3-5K / s, which is far lower than the change rate 20-30K / s of the transition state core engine inlet temperature. The pressure adjustment rate can only reach 2-3kPa / s, which is far lower than the change rate 30-50kPa / s of the transition state core engine inlet pressure. The flow change also cannot reach the change rate 80kg / s of the transition state core engine inlet flow. The inlet pipe network does not have the rapid temperature, pressure and flow adjustment capabilities, and it is difficult to simulate the rapid change of the inlet conditions of the transition state core engine and verify the performance of the transition state core engine. In addition, the adjustment precision of the temperature, pressure and flow is low, and the temperature and pressure are prone to over-adjustment when adjusted, which will affect the aerodynamic stability of the core engine and even cause danger.

[0004] The present application is proposed in view of the above technical defects.

[0005] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide an air engine core test inlet pipe network and a control method thereof to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] In one aspect, an air engine core test inlet pipe network is provided, comprising:

[0009] The inlet end of the air inlet pipeline is connected with the compressor, and a water-cooled heat exchanger, an air inlet pipeline temperature electric regulating valve are sequentially arranged on the air inlet pipeline.

[0010] The inlet end of the normal state air inlet branch is connected with the outlet end of the air inlet pipeline, and the outlet end is connected with the pressure stabilizing tank.

[0011] The inlet end of the normal state pressure regulating bypass is connected on the normal state air inlet branch, and the connection node is located between the normal state branch mixing device and the normal state branch pressure hydraulic regulating valve.

[0012] The inlet end of the transition state air inlet branch is connected with the outlet end of the air inlet pipeline, and the outlet end is connected with the pressure stabilizing tank.

[0013] The inlet end of the transition state pressure regulating bypass is connected on the transition state air inlet branch, and the connection node is located between the transition state branch mixing device and the transition state branch pressure hydraulic regulating valve.

[0014] The inlet end of the state switching control bypass is connected on the transition state air inlet branch, and the connection node is located between the transition state branch pressure hydraulic regulating valve and the branch state switching hydraulic control valve.

[0015] According to at least one embodiment of the present application, the above-mentioned air inlet pipeline network for testing the core engine of the aero-engine further comprises:

[0016] The outlet end of the air inlet bypass is connected on the normal state air inlet branch, and the connection node is located between the normal state branch pressure hydraulic regulating valve and the pressure stabilizing tank.

[0017] According to at least one embodiment of the present application, the above-mentioned air inlet pipeline network for testing the core engine of the aero-engine further comprises:

[0018] The transition state pressure regulating bypass outlet end is connected with a transition state bypass exhaust muffler.

[0019] The state switching control bypass outlet end is connected with a state switching bypass exhaust muffler.

[0020] According to at least one embodiment of the present application, the above-mentioned air engine core test air inlet pipe network is connected with a compressor, a water-cooled heat exchanger, an air inlet pipe temperature electric regulating valve, an air inlet bypass temperature electric regulating valve, a normal state branch flow electric regulating valve, a normal state branch temperature heater, a normal state branch mixer, a normal state branch pressure hydraulic regulating valve, a normal state branch pressure electric regulating valve, a normal state bypass pressure hydraulic regulating valve, a normal state bypass pressure electric regulating valve, a transition state branch flow electric regulating valve, a transition state branch temperature heater, a transition state branch mixer, a transition state branch pressure hydraulic regulating valve, a branch state switching hydraulic control valve, a transition state branch pressure electric regulating valve, a transition state bypass pressure hydraulic regulating valve, a transition state bypass pressure electric regulating valve, a bypass state switching hydraulic control valve, and an air bypass flow hydraulic regulating valve, and is connected with a controller for control.

[0021] In another aspect, a method for operating an air engine core test air inlet pipe network is provided, comprising:

[0022] With continuous air supply of the air inlet pipe, the pressure is controlled by the compressor, and the temperature is controlled by the water-cooled heat exchanger and the air inlet pipe temperature electric regulating valve.

[0023] During normal test, the branch state switching hydraulic control valve is closed, the normal state air inlet branch is used for air supply, the normal test required flow is adjusted by the normal state branch flow electric regulating valve, the normal test required temperature is heated by the normal state branch temperature heater, the temperature is made uniform by the normal state branch mixer, the normal test required temperature is adjusted by the normal state branch pressure hydraulic regulating valve, the normal state branch pressure electric regulating valve, the normal state bypass pressure hydraulic regulating valve, and the normal state bypass pressure electric regulating valve, the rectification and pressure stabilization are performed by the pressure stabilizing tank, the core engine is supplied with air through the air supply pipe, and the normal test is performed.

[0024] During normal test, the branch state switching hydraulic control valve is closed, the normal state air inlet branch is used for air supply, the normal test required flow is adjusted by the normal state branch flow electric regulating valve, the normal test required temperature is heated by the normal state branch temperature heater, the temperature is made uniform by the normal state branch mixer, the normal test required temperature is adjusted by the normal state branch pressure hydraulic regulating valve, the normal state branch pressure electric regulating valve, the normal state bypass pressure hydraulic regulating valve, and the normal state bypass pressure electric regulating valve, the rectification and pressure stabilization are performed by the pressure stabilizing tank, the core engine is supplied with air through the air supply pipe, and the normal test is performed.

[0025] During the transition state test, the normal branch pressure hydraulic regulating valve, the normal branch pressure electric regulating valve, the bypass state switching hydraulic control valve are gradually closed, and the branch state switching hydraulic control valve is gradually opened at the same time, so that the air is supplied to the transition state inlet branch, the steady box is used for rectification and pressure stabilization, the core engine is supplied through the air supply pipeline, and the transition state test is performed. BRIEF DESCRIPTION OF DRAWINGS

[0026] Figure 1 is a schematic diagram of an aero-engine core engine test air inlet pipe network provided by the embodiment of the present application;

[0027] Among them:

[0028] A-air inlet pipeline; 2-compressor; 3-water-cooled heat exchanger; 4-inlet pipeline temperature electric regulating valve; 5-inlet bypass temperature electric regulating valve; B-normal inlet branch; 7-steady box; 8-normal branch flow electric regulating valve; 9-normal branch temperature heater; 10-normal branch mixer; 11-normal branch pressure hydraulic regulating valve; 12-normal branch pressure electric regulating valve; 13-core engine; C-normal pressure regulating bypass; 15-normal bypass pressure hydraulic regulating valve; 16-normal bypass pressure electric regulating valve; D-transition state inlet branch; 18-transition state branch flow electric regulating valve; 19-transition state branch temperature heater; 20-transition state branch mixer; 21-transition state branch pressure hydraulic regulating valve; 22-branch state switching hydraulic control valve; 23-transition state branch pressure electric regulating valve; E-transition state pressure regulating bypass; 25-transition state bypass pressure hydraulic regulating valve; 26-transition state bypass pressure electric regulating valve; F-state switching control bypass; 28-bypass state switching hydraulic control valve; G-air inlet bypass; 30-normal bypass exhaust silencer; 31-transition state bypass exhaust silencer; 32-state switching bypass exhaust silencer; 33-air bypass flow hydraulic regulating valve.

[0029] In order to better illustrate the embodiment, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the patent. DETAILED DESCRIPTION

[0030] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further described in detail below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0031] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like, which indicate orientation in the description of the present application, are used only to indicate relative directional or positional relationships, and are not intended to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship thereof can also be changed accordingly when the absolute position of the described object is changed, and therefore cannot be understood as a limitation on the present application. The "first", "second", "third" and the like used in the description of the present application are only for the purpose of description, to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the quantity, but should be understood as the presence of at least one. The "including" or "containing" and the like used in the description of the present application means that the elements or objects appearing before the word are encompassed by the elements or objects listed after the word and their equivalents, and other elements or objects are not excluded.

[0032] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0033] The following will be described in detail with reference to the accompanying drawings Figure 1 The present application will be further described in detail.

[0034] In one aspect, an air engine core test air inlet pipe network is provided, comprising:

[0035] The inlet end of the air inlet pipeline A is connected with the compressor 2, and the water-cooled heat exchanger 3 and the air inlet pipeline temperature electric regulating valve 4 are arranged in sequence thereon. The water-cooled heat exchanger 3 and the air inlet pipeline temperature electric regulating valve 4 are connected in parallel with the air inlet bypass temperature electric regulating valve 5.

[0036] Normal state air intake branch B, its inlet end is connected to the outlet end of the air intake pipeline A, and the outlet end is connected to the pressure stabilizing box 7, and the pressure stabilizing box 7 is sequentially connected with a normal state branch flow electric regulating valve 8, a normal state branch temperature heater 9, a normal state branch mixer 10 and a normal state branch pressure hydraulic regulating valve 11; the normal state branch pressure hydraulic regulating valve 11 is connected in parallel with a normal state branch pressure electric regulating valve 12; the pressure stabilizing box 7 is connected with the core engine 13 through a gas supply pipeline;

[0037] Normal state pressure regulating bypass C, its inlet end is connected to the normal state air intake branch B, and the connection node is located between the normal state branch mixer 10 and the normal state branch pressure hydraulic regulating valve 11, and the normal state pressure regulating bypass C is provided with a normal state bypass pressure hydraulic regulating valve 15; the normal state bypass pressure hydraulic regulating valve 15 is connected in parallel with a normal state bypass pressure electric regulating valve 16;

[0038] Transition state air intake branch D, its inlet end is connected to the outlet end of the air intake pipeline A, and the outlet end is connected to the pressure stabilizing box 7, and the pressure stabilizing box 7 is sequentially connected with a transition state branch flow electric regulating valve 18, a transition state branch temperature heater 19, a transition state branch mixer 20, a transition state branch pressure hydraulic regulating valve 21 and a branch state switching hydraulic control valve 22; the transition state branch pressure hydraulic regulating valve 21 is connected in parallel with a transition state branch pressure electric regulating valve 23;

[0039] Transition state pressure regulating bypass E, its inlet end is connected to the transition state air intake branch D, and the connection node is located between the transition state branch mixer 20 and the transition state branch pressure hydraulic regulating valve 21, and the transition state pressure regulating bypass E is provided with a transition state bypass pressure hydraulic regulating valve 25; the transition state bypass pressure hydraulic regulating valve 25 is connected in parallel with a transition state bypass pressure electric regulating valve 26;

[0040] State switching control bypass F, its inlet end is connected to the transition state air intake branch D, and the connection node is located between the transition state branch pressure hydraulic regulating valve 21 and the branch state switching hydraulic control valve 22, and the state switching control bypass F is provided with a bypass state switching hydraulic control valve 28.

[0041] Optionally, in the above-mentioned air intake pipeline network for testing the core engine of an aero-engine, the air intake pipeline network further comprises:

[0042] Air intake bypass G, its outlet end is connected to the normal state air intake branch B, and the connection node is located between the normal state branch pressure hydraulic regulating valve 11 and the pressure stabilizing box 7, and the air intake bypass G is provided with an air bypass flow hydraulic regulating valve 33.

[0043] Optionally, in the above-mentioned air intake pipeline network for testing the core engine of an aero-engine, the outlet end of the normal state pressure regulating bypass C is connected with a normal state bypass exhaust silencer 30;

[0044] The outlet end of the transition state pressure regulating bypass E is connected with a transition state bypass exhaust silencer 31;

[0045] The state switching control bypass F outlet end is connected to a state switching bypass exhaust muffler 32.

[0046] Optionally, in the above-mentioned aero-engine core engine test air inlet pipe network, the compressor 2, the water-cooled heat exchanger 3, the air inlet pipe temperature electric regulating valve 4, the air inlet bypass temperature electric regulating valve 5, the normal state branch flow electric regulating valve 8, the normal state branch temperature heater 9, the normal state branch mixer 10, the normal state branch pressure hydraulic regulating valve 11, the normal state branch pressure electric regulating valve 12, the normal state bypass pressure hydraulic regulating valve 15, the normal state bypass pressure electric regulating valve 16, the transition state branch flow electric regulating valve 18, the transition state branch temperature heater 19, the transition state branch mixer 20, the transition state branch pressure hydraulic regulating valve 21, the branch state switching hydraulic control valve 22, the transition state branch pressure electric regulating valve 23, the transition state bypass pressure hydraulic regulating valve 25, the transition state bypass pressure electric regulating valve 26, the bypass state switching hydraulic control valve 28, and the air bypass flow hydraulic regulating valve 33 are connected to a controller for control.

[0047] The above-mentioned embodiment discloses an aero-engine core engine test air inlet pipe network control method, which refers to the following:

[0048] The air inlet pipe A continuously supplies air, the compressor 2 controls the pressure, the water-cooled heat exchanger 3 and the air inlet pipe temperature electric regulating valve 4 control the temperature, the temperature can be adjusted to 30-150℃, and the continuous supply of air with a certain temperature and pressure is carried out according to the test requirements.

[0049] During normal state testing, the branch state switching hydraulic control valve 22 is closed, the normal state air inlet branch B is used for air supply, the normal state branch flow electric regulating valve 8 is used for adjusting the flow to the normal state test requirement, the normal state branch temperature heater 9 is used for heating to the normal state test requirement, the normal state branch mixer 10 is used for mixing to make the temperature uniform, the normal state pressure regulating bypass C is used for venting, the normal state branch pressure hydraulic regulating valve 11, the normal state branch pressure electric regulating valve 12, the normal state bypass pressure hydraulic regulating valve 15, and the normal state bypass pressure electric regulating valve 15 are used for adjusting the temperature to the normal state test requirement, the pressure stabilizing tank 7 is used for rectification and pressure stabilization, the air supply pipe is used for supplying the core engine 13, and the normal state test is carried out.

[0050] The bypass state switching hydraulic control valve 28 is opened to adjust the transition state intake branch D, the transition state branch flow electric regulating valve 18 is adjusted to the required flow rate of the transition state test, the transition state branch temperature heater 19 is heated to the required temperature of the normal state test, the transition state branch mixer 20 is used for mixing to make the temperature uniform, the transition state pressure regulating bypass E is vented, and the transition state branch pressure hydraulic regulating valve 21, the transition state branch pressure electric regulating valve 23, the transition state bypass pressure hydraulic regulating valve 25 and the transition state bypass pressure electric regulating valve are adjusted to the required temperature of the normal state test, that is, the temperature, pressure and flow rate required by the core engine 13 for the transition state test are adjusted in advance in the transition state intake branch D.

[0051] During the transition state test, the normal state branch pressure hydraulic regulating valve 11, the normal state branch pressure electric regulating valve 12 and the bypass state switching hydraulic control valve 28 are gradually closed, and the branch state switching hydraulic control valve 22 is gradually opened at the same time to supply air through the transition state intake branch D, the pressure stabilizing tank 7 is used for rectification and pressure stabilization, and the core engine 13 is supplied through the air supply pipeline to perform the transition state test. The opening and closing rates of the normal state branch pressure hydraulic regulating valve 11, the normal state branch pressure electric regulating valve 12, the bypass state switching hydraulic control valve 28 and the bypass state switching hydraulic control valve 28 are converted by the change rate of the temperature, flow rate and pressure of the transition state inlet air of the core engine 13 to achieve rapid switching of the inlet air conditions of the core engine 13 during the transition state test, simulate the rapid change of the transition state core engine 13 inlet air conditions, and reliably verify the transition state performance of the core engine 13.

[0052] The above-mentioned embodiment discloses an air engine core engine test intake pipe network and a control method thereof. The design includes a normal state intake branch B and a transition state intake branch D to supply air to the core engine 13 during normal state tests and transition state tests. The required temperature, pressure and flow rate of the transition state test can be pre-adjusted, the valves are switched at a certain rate, the operation is convenient, the rapid change of the transition state core engine 13 inlet air conditions can be accurately simulated, the transition state performance of the core engine 13 can be reliably verified, the switching process can be smoothly transitioned, and the adjustment overage can be avoided to ensure the aerodynamic stability of the core engine. In addition, the electric regulating valve and the hydraulic regulating valve are designed to jointly adjust the temperature, pressure and flow rate to ensure rapid and high-precision adjustment.

[0053] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts of each embodiment can be referred to each other.

[0054] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and it should be understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An inlet duct network for aeroengine core engine testing, characterized in that, It includes: The inlet end of the air intake pipeline (A) is connected with the compressor (2), and the water-cooled heat exchanger (3) and the air intake pipeline temperature electric regulating valve (4) are sequentially arranged thereon, and the water-cooled heat exchanger (3) and the air intake pipeline temperature electric regulating valve (4) are connected with the air intake bypass temperature electric regulating valve (5) in parallel; The normal air intake branch (B) is connected with the outlet end of the air intake pipeline (A) at the inlet end, and is connected with the pressure stabilizing tank (7) at the outlet end, and the normal branch flow electric regulating valve (8), the normal branch temperature heater (9), the normal branch mixer (10) and the normal branch pressure hydraulic regulating valve (11) are sequentially connected on the normal air intake branch (B); the normal branch pressure hydraulic regulating valve (11) is connected with the normal branch pressure electric regulating valve (12) in parallel; the pressure stabilizing tank (7) is connected with the core engine (13) through the gas supply pipeline; The normal pressure regulating bypass (C) is connected on the normal air intake branch (B) at the inlet end, and the connection node is located between the normal branch mixer (10) and the normal branch pressure hydraulic regulating valve (11), and the normal bypass pressure hydraulic regulating valve (15) is arranged thereon; the normal bypass pressure hydraulic regulating valve (15) is connected with the normal bypass pressure electric regulating valve (16) in parallel; The transition state air intake branch (D) is connected with the outlet end of the air intake pipeline (A) at the inlet end, and is connected with the pressure stabilizing tank (7) at the outlet end, and the transition state branch flow electric regulating valve (18), the transition state branch temperature heater (19), the transition state branch mixer (20), the transition state branch pressure hydraulic regulating valve (21) and the branch state switching hydraulic control valve (22) are sequentially connected on the transition state air intake branch (D); the transition state branch pressure hydraulic regulating valve (21) is connected with the transition state branch pressure electric regulating valve (23) in parallel; The transition state pressure regulating bypass (E) is connected on the transition state air intake branch (D) at the inlet end, and the connection node is located between the transition state branch mixer (20) and the transition state branch pressure hydraulic regulating valve (21), and the transition state bypass pressure hydraulic regulating valve (25) is arranged thereon; the transition state bypass pressure hydraulic regulating valve (25) is connected with the transition state bypass pressure electric regulating valve (26) in parallel; The state switching control bypass (F) is connected on the transition state air intake branch (D) at the inlet end, and the connection node is located between the transition state branch pressure hydraulic regulating valve (21) and the branch state switching hydraulic control valve (22), and the bypass state switching hydraulic control valve (28) is arranged thereon.

2. The air intake pipeline network for the core engine test of the aircraft engine according to claim 1, further comprising: The air intake bypass (G) is connected on the normal air intake branch (B) at the outlet end, and the connection node is located between the normal branch pressure hydraulic regulating valve (11) and the pressure stabilizing tank (7), and the air bypass flow hydraulic regulating valve (33) is arranged thereon.

3. The air intake pipeline network for the core engine test of the aircraft engine according to claim 2, wherein: The outlet end of the normal pressure regulating bypass (C) is connected with the normal bypass exhaust silencer (30); The outlet end of the transition state pressure regulating bypass (E) is connected with the transition state bypass exhaust silencer (31); The outlet end of the state switching control bypass (F) is connected with the state switching bypass exhaust silencer (32). ​ 4. The air engine core engine test air inlet pipe network according to claim 3, characterized in that, The compressor (2), the water-cooled heat exchanger (3), the air inlet pipe temperature electric regulating valve (4), the air inlet bypass temperature electric regulating valve (5), the normal state branch flow electric regulating valve (8), the normal state branch temperature heater (9), the normal state branch mixer (10), the normal state branch pressure hydraulic regulating valve (11), the normal state branch pressure electric regulating valve (12), the normal state bypass pressure hydraulic regulating valve (15), the normal state bypass pressure electric regulating valve (16), the transition state branch flow electric regulating valve (18), the transition state branch temperature heater (19), the transition state branch mixer (20), the transition state branch pressure hydraulic regulating valve (21), the branch state switching hydraulic control valve (22), the transition state branch pressure electric regulating valve (23), the transition state bypass pressure hydraulic regulating valve (25), the transition state bypass pressure electric regulating valve (26), the bypass state switching hydraulic control valve (28), the air bypass flow hydraulic regulating valve (33) are connected to the controller for control.

5. An air intake duct network handling method for aeroengine core engine testing, characterized in that, It comprises: The air inlet pipe (A) continuously supplies air, the compressor (2) controls the pressure, the water-cooled heat exchanger (3), the air inlet pipe temperature electric regulating valve (4), and the water-cooled heat exchanger (3) controls the temperature; During the normal state test, the branch state switching hydraulic control valve (22) is closed, the normal state air inlet branch (B) supplies air, the normal state branch flow electric regulating valve (8) is adjusted to the required flow of the normal state test, the normal state branch temperature heater (9) is heated to the required temperature of the normal state test, the normal state branch mixer (10) is used for mixing to make the temperature uniform, the normal state branch pressure hydraulic regulating valve (11), the normal state branch pressure electric regulating valve (12), the normal state bypass pressure hydraulic regulating valve (15), and the normal state bypass pressure hydraulic regulating valve (15) are adjusted to the required temperature of the normal state test, the steady pressure tank (7) is used for rectification and pressure stabilization, and the core engine (13) is supplied with air through the air supply pipe to perform the normal state test; The bypass state switching hydraulic control valve (28) is opened, the transition state air inlet branch (D) is adjusted, the transition state branch flow electric regulating valve (18) is adjusted to the required flow of the transition state test, the transition state branch temperature heater (19) is heated to the required temperature of the normal state test, the transition state branch mixer (20) is used for mixing to make the temperature uniform, the transition state branch pressure hydraulic regulating valve (21), the transition state branch pressure electric regulating valve (23), the transition state bypass pressure hydraulic regulating valve (25), and the transition state bypass pressure electric regulating valve are adjusted to the required temperature of the normal state test; During the transition state test, the normal state branch pressure hydraulic regulating valve (11), the normal state branch pressure electric regulating valve (12), the bypass state switching hydraulic control valve (28), and the branch state switching hydraulic control valve (22) are gradually closed, the transition state air inlet branch (D) supplies air, the steady pressure tank (7) is used for rectification and pressure stabilization, and the core engine (13) is supplied with air through the air supply pipe to perform the transition state test.

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