An experimental piece and a regulation method for regulating radial distribution of turbine gas inlet temperature

Abstract

The present application belongs to the technical field of turbine heat transfer test device of aero-engine, and discloses a kind of experimental pieces for adjusting turbine gas inlet temperature radial distribution and regulation and control method, wherein, test piece includes the gas inlet section, test section and exhaust section connected in sequence;The end of the gas inlet section close to the test section is relatively provided with upper and lower orifice plates, and a plurality of gas inlet holes are arranged on the upper and lower orifice plates;The test piece further includes first and second gas collecting covers, the first gas collecting cover is covered outside the upper orifice plate, and the first gas collecting cover forms an upper gas collecting cavity with the upper orifice plate, and the second gas collecting cover is covered outside the lower orifice plate, and the second gas collecting cover forms a lower gas collecting cavity with the lower orifice plate.The present application increases the upper gas collecting cavity, the lower gas collecting cavity, the upper orifice plate and the lower orifice plate structure on the test piece for temperature adjustment, which can realize the adjustment of gas inlet temperature radial distribution, achieve the purpose of simulating the real engine turbine inlet temperature, further reduce the test error, and improve the test precision.

Description

Technical Field

[0001] This invention belongs to the technical field of turbine heat transfer test equipment for aero-engines, and specifically relates to an experimental piece and control method for adjusting the radial distribution of turbine gas inlet temperature. Background Technology

[0002] As aero-engines develop, turbine inlet temperatures continue to rise, and the non-uniformity of the turbine inlet gas becomes increasingly prominent. Hot spots and high-temperature distribution areas have a worse impact on turbine blades, resulting in large temperature gradients on the blade surface. This can easily lead to dangers such as localized overheating and blade erosion. In experimental verification, using only the mainstream average temperature for simulation tests cannot truly reflect cooling performance. This may lead to design deviations due to experimental errors, posing a danger to the safe and reliable operation of the engine. It can be seen that the radial distribution characteristics of the mainstream temperature in heat transfer tests have become an influencing factor that cannot be ignored.

[0003] Currently, with the continuous improvement of turbine heat transfer test bench capabilities, the temperature of the test combustion gas has been significantly increased, enabling the simulation of some real engine operating conditions. However, the means of radial distribution adjustment are relatively scarce. When using electric heaters to heat the airflow, the airflow passes through multiple heating wires during its flow, resulting in a basically uniform temperature distribution in the airflow before the turbine during the test, making it impossible to achieve radial distribution adjustment of the test combustion gas temperature. Using a combustion chamber to heat the airflow can achieve radial distribution characteristics in the test combustion gas temperature, but this requires a custom-designed combustion chamber with matching features. Once the combustion chamber is determined, the radial temperature distribution characteristics are basically not adjustable, making it impossible to adapt to the different temperature distribution requirements of turbine heat transfer tests for different engines. Frequent replacement of combustion chambers is also unacceptable.

[0004] For example, current mainstream turbine heat transfer tests primarily achieve flow and temperature control through electric heaters or combustion chambers, such as... Figure 1 As shown, the existing test specimen for adjusting the inlet temperature of the turbine heat transfer test gas consists of an inlet section 1, a test section 2, and an exhaust section 3. High-temperature gas flows through the inlet section and enters the test section with a uniform inlet temperature distribution. The existing test specimen can only control the gas temperature to meet the test requirements, such as... Figure 2 As shown, the existing intake section has a straight flow channel at the end near the test section, as... Figure 3 As shown, existing intake sections can only achieve temperature regulation of around 1430K at different radial heights, which greatly limits the means of adjusting the radial distribution of inlet temperature. This makes it largely unable to meet and adapt to the different inlet temperature distribution characteristics of various engines, and the main technical problems are as follows: 1. When an electric heater heats the airflow, the airflow passes through a multi-channel electric heating wire during its flow, resulting in a basically uniform temperature distribution of the airflow before the turbine during the test. This makes it impossible to achieve a radial distribution of the test gas temperature, and it is even more unadjustable.

[0005] 2. Heating the airflow through the combustion chamber can achieve radial distribution characteristics of the test gas temperature, but this requires a custom-designed combustion chamber with matching features. Once the combustion chamber is determined, the radial temperature distribution characteristics are basically not adjustable, which cannot meet the different temperature distribution requirements of different engine turbine heat transfer tests. Frequent replacement of the combustion chamber is also unacceptable due to the high cost and time required.

[0006] In summary, the existing test specimen structure for adjusting the radial distribution of gas inlet temperature cannot simulate the actual radial distribution of gas inlet temperature before the turbine of an engine, resulting in deviations between the test results and the actual engine flow conditions. Summary of the Invention

[0007] To address the above problems, the present invention provides an experimental component for adjusting the radial distribution of turbine gas inlet temperature, comprising an intake section, a test section, and an exhaust section connected in sequence, wherein the intake section, the test section, and the exhaust section are provided with interconnected gas passages along the axial direction. The test section includes an upper orifice plate and a lower orifice plate positioned opposite each other at one end near the test section. Both the upper and lower orifice plates have multiple air inlets. The test piece also includes a first gas collecting hood and a second gas collecting hood. The first gas collecting hood covers the outside of the upper orifice plate, forming an upper gas collecting chamber with the upper orifice plate. The second gas collecting hood covers the outside of the lower orifice plate, forming a lower gas collecting chamber with the lower orifice plate. The multiple air inlets on the upper orifice plate connect the gas passage and the upper gas collecting chamber, and the multiple air inlets on the lower orifice plate connect the gas passage and the lower gas collecting chamber.

[0008] Furthermore, the first gas collecting hood is provided with a first cooling gas inlet, and the second gas collecting hood is provided with a second cooling gas inlet.

[0009] Furthermore, the distance between the centerline of the first cooling gas inlet and the end face of the first gas collecting hood furthest from the test section is... L 1 satisfies: ,in, L 01 It is the length of the upper gas collecting chamber in the direction of gas flow within the gas passage.

[0010] Furthermore, the distance between the centerline of the second cooling gas inlet and the end face of the second gas collecting hood furthest from the test section... L 2. Satisfies: The length of the lower gas collecting chamber in the gas flow direction within the gas passage is... L 02 .

[0011] Furthermore, the distance between the first row of air inlets on the upper orifice plate and the end face of the upper orifice plate furthest from the test section... X 1 satisfies: .

[0012] Furthermore, the distance between the first row of air inlets on the lower orifice plate and the end face of the lower orifice plate furthest from the test section is... X 2. Satisfies: .

[0013] Furthermore, the angle between the centerline of the air inlet on the upper perforated plate and the airflow direction of the gas passage is... α 1, among which, .

[0014] Furthermore, the angle between the centerline of the air inlet on the lower perforated plate and the airflow direction of the gas passage is... α 2, of which, .

[0015] Furthermore, the flow area of ​​the first cooling gas inlet is not less than the total flow area of ​​all air inlets on the upper orifice plate, and the flow area of ​​the second cooling gas inlet is not less than the total flow area of ​​all air inlets on the lower orifice plate.

[0016] This invention also provides a method for controlling the radial distribution of turbine gas inlet temperature, based on the above-mentioned experimental specimen for adjusting the radial distribution of gas inlet temperature, comprising the following steps: S1. Determine the mainstream gas parameters of the engine and the geometric parameters of the test piece; S2. Based on the mainstream gas parameters and the geometric parameters of the test piece, obtain the mainstream gas temperature distribution after mixing in the gas passage, and the radial distribution curve of the average circumferential temperature after mixing in the gas passage. S3. Calculate the radial temperature distribution coefficient of the mainstream gas based on the radial distribution curve of the mainstream gas temperature distribution and the radial temperature distribution curve of the circumferential average temperature. Calculate the deviation between the radial temperature distribution coefficient of the mainstream gas and the radial temperature distribution coefficient of the engine design. If the deviation is greater than the threshold, adjust the outflow area of ​​the air inlet on the upper and lower orifice plates and return to step S2. If the deviation is less than the threshold, proceed to step S5. S4. Estimate the amount of cold air required for the upper and lower air collection chambers; S5. Deliver the estimated amount of cold air to the upper and lower gas collecting chambers, measure the mainstream gas data of the gas passage, and obtain the temperature and pressure data of the mainstream gas at different radial heights in the intake section. S6. Calculate the radial temperature distribution coefficient of the mainstream gas based on the temperature and pressure data of the mainstream gas at different radial heights in the intake section; calculate the deviation between the radial temperature distribution coefficient of the mainstream gas and the radial temperature distribution coefficient designed for the engine. If the deviation is greater than the threshold, return to step S4 to adjust the required amount of cold air in the upper and lower air chambers and then proceed to step S5. If the deviation is less than the threshold, proceed to step S7. S7. Solve the cold air volume matrix of the upper and lower gas collecting chambers, as well as the radial temperature distribution coefficient matrix of the test, based on the geometric parameters of the test piece. S8. Based on the cold air volume matrix of the upper and lower gas collecting chambers and the experimental radial temperature distribution coefficient matrix, determine the relationship between the cold air volume input to the upper and lower gas collecting chambers and the experimental radial temperature distribution coefficient.

[0017] The beneficial effects of this invention are: Based on the conventional simple test piece design, this invention adds an upper gas collecting chamber, a lower gas collecting chamber, an upper orifice plate, and a lower orifice plate structure for temperature regulation. This allows for adjustment of the radial distribution of the gas inlet temperature, achieving the goal of simulating the inlet temperature of a real engine turbine, further reducing test errors and improving test accuracy.

[0018] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A schematic diagram of the test specimen structure and mainstream gas flow according to the prior art is shown; Figure 2 A schematic diagram of the structure of the air intake section near the test section according to the prior art is shown; Figure 3 A schematic diagram illustrating the effect of radial temperature distribution adjustment in the intake section according to the prior art is shown. Figure 4 A schematic diagram of an experimental component for adjusting the radial distribution of turbine gas inlet temperature according to an embodiment of the present invention is shown. Figure 5A schematic diagram of the internal structure of an experimental piece for adjusting the radial distribution of turbine gas inlet temperature according to an embodiment of the present invention is shown. Figure 6 A schematic diagram of the installation of a first gas collecting hood and an upper perforated plate, and a second gas collecting hood and a lower perforated plate, according to an embodiment of the present invention, is shown. Figure 7 A schematic diagram of the structure of a first gas collection hood according to an embodiment of the present invention is shown; Figure 8 It shows Figure 7 Sectional view of section AA; Figure 9 A schematic diagram of the structure of a second gas collection hood according to an embodiment of the present invention is shown; Figure 10 It shows Figure 9 Sectional view of section BB; Figure 11 A schematic diagram of the structure of the upper perforated plate according to an embodiment of the present invention is shown; Figure 12 It shows Figure 11 A sectional view of section C-C; Figure 13 A schematic diagram of the structure of the lower perforated plate according to an embodiment of the present invention is shown; Figure 14 It shows Figure 13 Sectional view of section DD; Figure 15 The included angle of the air inlet on the upper perforated plate according to an embodiment of the present invention is shown. α 1, and the included angle of the air inlet on the lower perforated plate. α Both are structural diagrams with a 90° angle; Figure 16 The included angle of the air inlet according to an embodiment of the present invention is shown. α 1 and α Schematic diagram of the radial temperature distribution adjustment effect of the intake section when both are 90°; Figure 17 The included angle of the air inlet on the upper perforated plate according to an embodiment of the present invention is shown. α 1, and the included angle of the air inlet on the lower perforated plate. α Both are structural diagrams with a 90° angle; Figure 18 The included angle of the air inlet according to an embodiment of the present invention is shown. α 1 and α Schematic diagram of the radial temperature distribution adjustment effect of the intake section when both are 90°; Figure 19 A schematic flowchart of a method for controlling the radial distribution of turbine gas inlet temperature according to an embodiment of the present invention is shown.

[0021] In the diagram: 1. Inlet section; 2. Test section; 3. Exhaust section; 4. Gas passage; 5. Upper orifice plate; 6. Lower orifice plate; 7. Inlet port; 8. First gas collection hood; 9. Second gas collection hood; 10. First cooling gas inlet; 11. Second cooling gas inlet. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] It should be noted that the terms "first," "second," etc., used in this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein. In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," "longitudinal," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings.

[0024] This invention provides a test specimen and control method for adjusting the radial distribution of turbine gas inlet temperature, which is designed for aero-engine turbine heat transfer test. The specimen is placed in front of the turbine inlet and changes the incident angle and velocity of the cold air through the temperature adjustment hole to realistically simulate different temperature distributions at the turbine inlet, thereby reducing test errors and improving test accuracy.

[0025] like Figure 4 and Figure 5 As shown, a test piece for adjusting the radial distribution of turbine gas inlet temperature includes an intake section 1, a test section 2, and an exhaust section 3 connected in sequence. The intake section 1, the test section 2, and the exhaust section 3 are provided with interconnected gas passages 4 along the axial direction inside them.

[0026] Among them, the upper orifice plate 5 and the lower orifice plate 6 are respectively arranged at the end of the air intake section 1 near the test section 2, and multiple air intake holes 7 are provided on both the upper orifice plate 5 and the lower orifice plate 6.

[0027] like Figure 6As shown, the test piece also includes a first gas collecting hood 8 and a second gas collecting hood 9. The first gas collecting hood 8 is installed on the outside of the upper perforated plate 5. The upper perforated plate 5 is arc-shaped and convex upward. The first gas collecting hood 8 and the upper perforated plate 5 form an upper gas collecting cavity. The second gas collecting hood 9 is installed on the outside of the lower perforated plate 6. The second gas collecting hood 9 and the lower perforated plate 6 form a lower gas collecting cavity. The lower perforated plate 6 is arc-shaped and concave.

[0028] The first gas collecting hood 8 is provided with a first cooling gas inlet 10, and the second gas collecting hood 9 is provided with a second cooling gas inlet 11. Multiple air inlets 7 on the upper perforated plate 5 are connected to the gas passage 4 and the upper gas collecting chamber, and multiple air inlets 7 on the lower perforated plate 6 are connected to the gas passage 4 and the lower gas collecting chamber.

[0029] The first cooling gas inlet 10 and the second cooling gas inlet 11 are connected to the air intake duct for connection to the external air supply device. The external cooling gas enters the upper and lower gas collecting chambers through the first cooling gas inlet 10 and the second cooling gas inlet 11, respectively. The high-temperature gas flow passes through the gas passage 4 of the intake section 1. The cooling gas flow of the upper gas collecting chamber enters the gas passage 4 of the intake section 1 through multiple air intake holes 7 on the upper perforated plate 5. The cooling gas flow of the lower gas collecting chamber enters the gas passage 4 of the intake section 1 through multiple air intake holes 7 on the lower perforated plate 6. The high-temperature gas flow in the gas passage 4 of the intake section 1 is mixed with the cooling gas on both sides. Under the regulation of the cooling gas on both sides, the temperature distribution around the wall is changed, causing the high-temperature gas to enter the test section 2 with a radial distribution characteristic.

[0030] like Figure 7 and Figure 9 As shown, the length of the upper gas collecting chamber in the gas flow direction within the gas passage 4 is... L 01 The length of the lower gas collecting chamber in the gas flow direction within the gas passage 4 is... L 02 ,like Figure 8 and Figure 10 As shown, the spatial height of the upper gas collecting chamber is y 1. The spatial height of the lower gas collecting chamber is y 2.

[0031] like Figure 7 As shown, the distance between the centerline of the first cooling gas inlet 10 and the end face of the first gas collecting shroud 8 away from the test section 2 is... L 1, among which, ;like Figure 9 As shown, the distance between the centerline of the second cooling gas inlet 11 and the end face of the second gas collecting shroud 9 furthest from the test section 2 is... L 2, of which, ;like Figure 8 and Figure 10 As shown, the diameter of the first cooling gas inlet 10 is d 1. The diameter of the second cooling gas inlet 11 isd 2.

[0032] like Figure 11 and Figure 12 As shown, the distance between the first row of air inlets 7 on the upper perforated plate 5 and the end face of the upper perforated plate 5 furthest from the test section 2 is... X 1, among which, .

[0033] like Figure 13 and Figure 14 As shown, the distance between the first row of air inlets 7 on the lower orifice plate 6 and the end face of the lower orifice plate 6 furthest from the test section 2 is... X 2, of which, The angle between the centerline of the air inlet 7 on the upper perforated plate 5 and the airflow direction of the gas passage 4 is... α 1, among which, The diameter of the air inlet 7 on the upper perforated plate 5 is d 3. The number of air inlets 7 on the upper perforated plate 5 is: n1 The angle between the centerline of the air inlet 7 on the lower perforated plate 6 and the airflow direction of the gas passage 4 is . α 2, of which, The diameter of the air inlet 7 on the lower perforated plate 6 is d 4. The number of air inlets 7 on the upper perforated plate 5 is: n2 .

[0034] like Figure 15 and Figure 16 As shown, the included angle of the air inlet 7 on the upper perforated plate 5 α 1, and the included angle of the air inlet 7 on the lower perforated plate 6. α The radial temperature distribution adjustment effect of intake section 1 when both are 90° shows that the test piece of this embodiment can achieve temperature distribution adjustment in the range of 1360~1430K at different radial heights.

[0035] like Figure 17 and Figure 18 As shown, the included angle of the air inlet 7 on the upper perforated plate 5 α 1, and the included angle of the air inlet 7 on the lower perforated plate 6. α The radial temperature distribution adjustment effect of intake section 1 is shown when both are 50°. The test piece of this embodiment can achieve temperature distribution adjustment of 1245~1430 at different radial heights.

[0036] The flow area of ​​the first cooling gas inlet 10 is not less than the total flow area of ​​all the air inlets 7 on the upper orifice plate 5, and the flow area of ​​the second cooling gas inlet 11 is not less than the total flow area of ​​all the air inlets 7 on the lower orifice plate 6.

[0037] In this embodiment of the invention, by adjusting the structure of the upper orifice plate 5 and the lower orifice plate 6, the flow rate, velocity and outflow angle of the cooling gas are adjusted, thereby achieving radial temperature distribution control of the inlet gas.

[0038] like Figure 19 As shown, this embodiment of the invention also provides a method for controlling the radial distribution of turbine gas inlet temperature, which is implemented based on the above-mentioned experimental specimen for adjusting the radial distribution of gas inlet temperature, and includes the following steps: S1. Determine the mainstream gas parameters of the engine and the geometric parameters of the test piece. The mainstream gas parameters include the average temperature of the mainstream gas, the inlet flow rate of the mainstream gas, the average pressure of the mainstream gas, and the radial temperature distribution coefficient of the engine design. The geometric parameters of the test piece include the structural parameters of the intake section 1, the flow channel area of ​​the test section 2, and the area of ​​the intake holes 7 of the upper orifice plate 5 and the lower orifice plate 6.

[0039] S2. Based on the mainstream gas parameters and the geometric parameters of the test piece, the temperature distribution of the mainstream gas after mixing in the gas passage 4 is obtained through numerical simulation, which is as close as possible to the engine design temperature distribution. The required airflow parameters for the test are determined, and the radial distribution curve of the average circumferential temperature after mixing in the gas passage 4 is obtained through the test.

[0040] S3. Based on the mainstream gas temperature distribution and the radial distribution curve of the circumferential temperature average, calculate the radial temperature distribution coefficient of the mainstream gas through numerical simulation. Calculate the deviation between the mainstream gas radial temperature distribution coefficient and the engine design radial temperature distribution coefficient. If the deviation is greater than a threshold value... δ Then adjust the outflow area of ​​the air inlet 7 on the upper orifice plate 5 and the lower orifice plate 6, return to step S2 to iteratively solve the mainstream gas temperature distribution and the radial distribution curve of the circumferential temperature average, and obtain a new mainstream gas radial temperature distribution coefficient; if the deviation value is less than the threshold δ (Pick δ If the value is ≤0.01, then proceed to step S5.

[0041] The calculation of the radial temperature distribution coefficient of the mainstream gas is as follows:

[0042] In the formula, RTDF The radial temperature distribution coefficient of the mainstream gas. Tin,tmax To obtain the highest value on the radial distribution curve of the average circumferential temperature of the mainstream gas measured in the experiment; Tin,tav The average temperature of the mainstream gas was obtained by measuring the mainstream gas temperature distribution. TC,t This is a reference temperature, and this state typically corresponds to the combustion chamber intake temperature.

[0043] The outflow area of ​​the air inlet 7 on the upper orifice plate 5 and the lower orifice plate 6 is calculated as follows:

[0044] In the formula, A The outlet area of ​​the air inlet 7 on the upper orifice plate 5 and the lower orifice plate 6. n The number of air inlets 7 on the upper perforated plate 5 and the lower perforated plate 6; d The diameter of the air inlet 7 on the upper orifice plate 5 and the lower orifice plate 6; α The angle between the air inlet 7 on the upper orifice plate 5 and the airflow direction of the gas passage 4.

[0045] S4. Estimate the required cooling air volume for the upper and lower air collecting chambers. 。

[0046] S5. The estimated required amount of cold air is delivered to the upward air collecting chamber through the first cooling air inlet 10. ， The estimated amount of cold air is delivered to the lower gas collecting chamber through the second cooling gas inlet 11. The mainstream gas data of the gas passage 4 is measured to obtain the temperature and pressure data of the mainstream gas at different radial heights in the intake section 1. Specifically, this includes: obtaining the temperature data of the mainstream gas at different radial heights in the intake section 1 through the total temperature probe of the inlet section, and obtaining the pressure data of the mainstream gas at different radial heights in the intake section 1 through the total pressure probe of the inlet section.

[0047] S6. Based on the temperature and pressure data of the mainstream gas at different radial heights in intake section 1, calculate the radial temperature distribution coefficient of the mainstream gas; calculate the deviation between the radial temperature distribution coefficient of the mainstream gas and the engine design radial temperature distribution coefficient. If the deviation is greater than a threshold value... δ Then return to step S4 to adjust the required amount of cold air for the upper and lower air collecting chambers, and then proceed to step S5. If the deviation value is less than the threshold... δ (Pick δ If the value is ≤0.1), then proceed to step S7.

[0048] S7. Solve for the cold air volume matrix of the upper and lower gas collecting chambers, as well as the radial temperature distribution coefficient matrix of the test, based on the geometric parameters of the test piece.

[0049] S8. Based on the cold air volume matrix of the upper and lower gas collecting chambers and the experimental radial temperature distribution coefficient matrix, determine the relationship between the cold air volume input to the upper and lower gas collecting chambers and the experimental radial temperature distribution coefficient, and output it outward.

[0050] Through simulation and analysis, the test specimen of the present invention demonstrates that the test specimen structure and method of the present invention have good feasibility. The control method of the present invention can realize and flexibly adjust the radial distribution of the inlet airflow temperature in the turbine heat transfer test, satisfying and adapting to the inlet temperature distribution characteristics of different engines.

[0051] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An experimental specimen for adjusting the radial distribution of turbine gas inlet temperature, characterized in that, It includes an intake section (1), a test section (2) and an exhaust section (3) connected in sequence. The intake section (1), the test section (2) and the exhaust section (3) are provided with interconnected gas passages (4) along the axial direction inside. The air intake section (1) is provided with an upper perforated plate (5) and a lower perforated plate (6) at one end near the test section (2). Both the upper perforated plate (5) and the lower perforated plate (6) are provided with multiple air intake holes (7). The test piece also includes a first gas collecting hood (8) and a second gas collecting hood (9). The first gas collecting hood (8) covers the outside of the upper perforated plate (5) and forms an upper gas collecting chamber with the upper perforated plate (5). The second gas collecting hood (9) covers the outside of the lower perforated plate (6) and forms a lower gas collecting chamber with the lower perforated plate (6). The multiple air intake holes (7) on the upper perforated plate (5) connect the gas passage (4) and the upper gas collecting chamber. The multiple air intake holes (7) on the lower perforated plate (6) connect the gas passage (4) and the lower gas collecting chamber.

2. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to claim 1, characterized in that, The first gas collecting hood (8) is provided with a first cooling gas inlet (10), and the second gas collecting hood (9) is provided with a second cooling gas inlet (11).

3. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to claim 2, characterized in that, The distance between the centerline of the first cooling gas inlet (10) and the end face of the first gas collecting shroud (8) away from the test section (2) L 1 satisfies: ,in, L 01 The length of the upper gas collecting chamber in the direction of gas flow within the gas passage.

4. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to claim 2, characterized in that, The distance between the centerline of the second cooling gas inlet (11) and the end face of the second gas collecting shroud (9) away from the test section (2) L 2. Satisfies: The length of the lower gas collecting chamber in the gas flow direction within the gas passage (4) is... L 02 .

5. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to claim 3, characterized in that, The distance between the first row of air inlets on the upper perforated plate and the end face of the upper perforated plate away from the test section (2) X 1 satisfies: .

6. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to claim 4, characterized in that, The distance between the first row of air inlets (7) on the lower orifice plate (6) and the end face of the lower orifice plate (6) away from the test section (2) is... X 2. Satisfies: .

7. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to any one of claims 1-6, characterized in that, The centerline of the air inlet (7) on the upper perforated plate (5) forms an angle with the airflow direction of the gas passage. α 1, among which, .

8. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to any one of claims 1-6, characterized in that, The centerline of the air inlet (7) on the lower perforated plate (6) forms an angle with the airflow direction of the gas passage (4). α 2, of which, .

9. The experimental specimen for adjusting the radial distribution of turbine gas inlet temperature according to any one of claims 2-6, characterized in that, The flow area of ​​the first cooling gas inlet (10) is not less than the total flow area of ​​all the air inlets (7) on the upper perforated plate (5), and the flow area of ​​the second cooling gas inlet (11) is not less than the total flow area of ​​all the air inlets (7) on the lower perforated plate (6).

10. A method for controlling the radial distribution of turbine gas inlet temperature, characterized in that, Based on the experimental piece for adjusting the radial distribution of gas inlet temperature according to any one of claims 1-9, the process includes the following steps: S1. Determine the mainstream gas parameters of the engine and the geometric parameters of the test piece; S2. Based on the mainstream gas parameters and the geometric parameters of the test piece, the temperature distribution of the mainstream gas after mixing in the gas channel (4) and the radial distribution curve of the average circumferential temperature after mixing in the gas channel (4) are obtained. S3. Calculate the radial temperature distribution coefficient of the mainstream gas based on the radial distribution curve of the mainstream gas temperature distribution and the radial temperature distribution curve of the circumferential average temperature; calculate the deviation between the radial temperature distribution coefficient of the mainstream gas and the radial temperature distribution coefficient of the engine design; if the deviation is greater than the threshold, adjust the outflow area of ​​the air inlet (7) on the upper orifice plate (5) and the lower orifice plate (6) and return to step S2; if the deviation is less than the threshold, execute step S5. S4. Estimate the amount of cold air required for the upper and lower air collection chambers; S5. Deliver the estimated amount of cold air to the upper and lower gas collecting chambers, measure the mainstream gas data of the gas passage (4), and obtain the temperature and pressure data of the mainstream gas at different radial heights in the intake section (1). S6. Based on the temperature and pressure data of the mainstream gas at different radial heights in the intake section (1), calculate the radial temperature distribution coefficient of the mainstream gas; calculate the deviation between the radial temperature distribution coefficient of the mainstream gas and the radial temperature distribution coefficient designed for the engine. If the deviation is greater than the threshold, return to step S4 to adjust the required amount of cold air in the upper and lower gas chambers and then execute step S5. If the deviation is less than the threshold, execute step S7. S7. Solve the cold air volume matrix of the upper and lower gas collecting chambers, as well as the radial temperature distribution coefficient matrix of the test, based on the geometric parameters of the test piece. S8. Based on the cold air volume matrix of the upper and lower gas collecting chambers and the experimental radial temperature distribution coefficient matrix, determine the relationship between the cold air volume input to the upper and lower gas collecting chambers and the experimental radial temperature distribution coefficient.

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