A high-temperature rotating table for engine rotor blade test

Abstract

The application discloses a high-temperature rotating table for engine rotor blade test, and belongs to the technical field of aero-engine rotor test. According to the scheme, a plurality of heating elements are arranged at intervals along a rotating path of a test piece in an air inlet section, and cooling air is delivered into the air inlet section by a cooling air source. The heating elements are used for heating the test piece, and the cooling air passes through the gaps between the heating elements to cool the test piece. The rotating path of the test piece is divided into staggered heating and cooling areas by the interval arrangement of the heating elements. In the rotating process of the test piece, the test piece is alternately heated and cooled. When the test piece rotates to the cooling area, the surface of the test piece is rapidly cooled. This process generates a transient and huge temperature gradient in the thickness direction of the test piece at the same position. This gradient is a typical state of a high-pressure compressor blade in a real engine. Therefore, the application can better simulate the actual working condition of the blade of the rotor upstream of the combustion chamber, and effectively improve the accuracy and authenticity of the test results.

Description

Technical Field

[0001] This invention relates to the field of aero-engine rotor testing technology, specifically a high-temperature rotary table for testing engine rotor blades. Background Technology

[0002] Aero-engine rotor blades undergo creep behavior under continuous high temperature and high speed, leading to blade creep failure. Their lifespan directly affects the reliability and safety of the engine. Due to the high cost of whole-engine testing, it is difficult to carry out large-scale testing. Standard and simulated component tests cannot reflect the stress state of real components and cannot characterize the real creep failure behavior of blades. Therefore, it is of great significance to propose a real blade creep test method using a high-temperature rotary table.

[0003] In existing test benches, when simulating the blade environment, the test site is usually placed directly in a stable high-temperature environment to bring the specimen to the set temperature. However, in a real engine, the rotor blade is not in a uniform and stable high-temperature field. It periodically passes through regions with different temperatures during high-speed rotation, and alternating thermal stress is generated inside. Traditional test benches keep the specimen in a stable high-temperature field during the test, which cannot simulate the alternating thermal stress generated inside a real blade.

[0004] Meanwhile, the rotor blades upstream of the combustion chamber are subjected not only to high-temperature thermal radiation from the combustion chamber during operation, but also to the impact of the cooling airflow from the previous stage. This causes a huge temperature gradient to form in the thickness direction of the blades. The existing test benches cannot reproduce this state, resulting in a large discrepancy between the creep test results of the rotor blades and the actual situation.

[0005] Based on this, the present invention designs a high-temperature rotary table for testing engine rotor blades to solve the above problems. Summary of the Invention

[0006] This invention provides a high-temperature rotary table for testing engine rotor blades, which solves the technical problem in the prior art that the test site is usually placed directly in a stable high-temperature environment when simulating the blade environment.

[0007] According to one aspect of the present invention, a high-temperature rotary table for testing engine rotor blades is provided, comprising a mounting platform for mounting a test specimen and driving the test specimen to rotate, the test specimen being used to mount a test specimen, and further comprising an air intake section, a cooling air source, and heating elements; the inner cavity of the air intake section is used to accommodate the test specimen, and multiple heating elements are provided, which are positioned upstream of the test specimen and are spaced apart along the rotation path of the test specimen to heat the test specimen at different positions on the rotation path; the cooling air source is used to deliver cooling airflow into the air intake section, and a space for cooling airflow is formed between adjacent heating elements, the cooling airflow passing between adjacent heating elements to cool the test specimen.

[0008] As a further embodiment of the present invention, the air intake section includes an air intake section inner shell and an air intake section outer shell, which are coaxially arranged to form an annular air intake channel for cooling airflow between the air intake section inner shell and the air intake section outer shell. The air intake section inner shell is provided with a clearance opening for the test piece to enter the annular air intake channel, or the test piece is located at the outlet end of the annular air intake channel.

[0009] As a further embodiment of the present invention, the diameter of the inner shell of the air intake section is smaller than the inner diameter of the rotation path of the specimen, and the heating element is located inside the annular air intake channel.

[0010] As a further embodiment of the present invention, the air outlet end of the air inlet section is provided with a baffle, and an air duct is provided on the baffle. The air duct is used to introduce the cooling airflow output by the cooling air source to cool the test specimen.

[0011] As a further aspect of the present invention, the heating element includes a flame gun, and the nozzle of the flame gun is directed toward the test specimen.

[0012] As a further embodiment of the present invention, the heating element includes a heating channel, which is disposed in the air inlet section facing upstream of the test piece. The heating channel has an air inlet and an air outlet. The air inlet is used to introduce cooling airflow into the heating channel, and the air outlet is used to discharge the airflow in the heating channel into the rotation path of the test piece. A heating component is provided in the heating channel, which is used to heat the airflow flowing through the heating channel.

[0013] As a further embodiment of the present invention, a plurality of the heating elements are arranged at equal intervals along the rotation path of the specimen.

[0014] As a further aspect of the present invention, the height of the heating element in the radial direction of the air inlet section is not less than the height of the test piece.

[0015] As a further aspect of the present invention, a cooling channel for the flow of cooling medium is provided inside the air intake section housing, and the cooling channel is located downstream of the heating element on the air intake section housing.

[0016] As a further aspect of the present invention, an exhaust section is connected downstream of the intake section. The exhaust section includes an exhaust section inner shell and an exhaust volute. The exhaust volute is used to introduce the cooling airflow discharged from the intake section and discharge it upward.

[0017] The present invention has the following beneficial effects:

[0018] This design involves placing multiple heating elements at intervals along the specimen's rotation path within the intake section, and supplying cooling airflow into the intake section via a cooling air source. The heating elements heat the specimen, while the cooling airflow passes through the gaps between them to cool it. The spacing of the heating elements divides the specimen's rotation path into alternating heating and cooling zones. During the specimen's rotation, heating and cooling alternate, simulating the transient thermodynamic environment of a real engine under dynamic thermal cycle temperature control. Furthermore, by controlling the heating power of the heating elements, the temperature of the specimen can be adjusted at different rotational positions. Heating the specimen to different temperatures allows for a more accurate reproduction of the periodic temperature changes of the rotor blades. Furthermore, when the specimen is instantaneously heated in the heating zone, its surface temperature rises rapidly, while the internal material of the specimen experiences a slower temperature increase due to thermal inertia. When the specimen rotates to the cooling zone, its surface is rapidly cooled. This process generates a sudden and significant temperature gradient along the thickness of the specimen at the same location. This gradient is typical of high-pressure compressor blades in a real engine. In summary, this application can better simulate actual operating conditions for the blades of the upstream rotor in the combustion chamber, effectively improving the accuracy and realism of the test results.

[0019] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0021] Figure 1 A schematic diagram of the structure of the high-temperature rotary table for testing engine rotor blades provided by the present invention;

[0022] Figure 2 for Figure 1 The diagram shows an enlarged view of part A of the high-temperature rotary table used for testing engine rotor blades.

[0023] Figure 3for Figure 1 The diagram shows an enlarged view of part B of the high-temperature rotary table used for testing engine rotor blades.

[0024] Figure 4 This is a side view of the intake section of a high-temperature rotating test bench for engine rotor blade testing provided by the present invention.

[0025] Legend:

[0026] 1. Mounting platform; 21. Test specimen; 22. Test specimen; 3. Intake section; 31. Intake section inner shell; 32. Intake section outer shell; 321. Cooling channel; 33. Annular intake air passage; 34. Baffle; 35. Air vent; 4. Cooling air source; 5. Heating element; 6. Exhaust section; 61. Exhaust section inner shell; 62. Exhaust volute. Detailed Implementation

[0027] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0028] Please see Figure 1-4 The present invention provides a technical solution: a high-temperature rotary table for testing engine rotor blades, including a mounting platform 1, which is used to mount a test specimen 21 and drive the test specimen 21 to rotate. The test specimen 21 is used to mount a test specimen 22. The high-temperature rotary table for testing engine rotor blades also includes an air intake section 3, a cooling air source 4, and heating elements 5. The inner cavity of the air intake section 3 is used to accommodate the test specimen 22. Multiple heating elements 5 are provided. The heating elements 5 are used to be arranged upstream of the test specimen 22 in the air intake section 3, and the multiple heating elements 5 are used to be arranged at intervals along the rotation path of the test specimen 22, so as to heat the test specimen 22 at different positions on the rotation path of the test specimen 22. The cooling air source 4 is used to deliver cooling airflow into the air intake section 3. A space for cooling airflow is formed between adjacent heating elements 5. The cooling airflow is used to pass through the space between adjacent heating elements 5 to cool the test specimen 22.

[0029] The upstream and downstream directions within intake section 3 refer to the flow direction of the cooling airflow within intake section 3.

[0030] In this application, specimen 22 represents a rotor blade, while the auxiliary specimen 21 represents the part of the rotor used to mount specimen 22 (such as a wheel). The mounting conditions of the rotor blade are simulated by mounting specimen 22 on auxiliary specimen 21. Auxiliary specimen 21 is mounted on mounting platform 1, and the mounting platform 1 drives auxiliary specimen 21 and specimen 22 to rotate, thereby restoring the rotation state of specimen 22.

[0031] In use, the specimen 22 is mounted on the mounting platform 1 via the accompanying specimen 21. The mounting platform 1, specimen 22, air intake section 3, and cooling air source 4 are arranged sequentially. After the specimen 22 is installed, the mounting platform 1 is started, driving the accompanying specimen 21 to rotate. The accompanying specimen 21 drives the test to rotate along a set path. The heating elements 5 in the air intake section 3 are arranged at intervals along the rotation path of the specimen 22. After the heating elements 5 are started, when the specimen 22 rotates to the downstream of the heating elements 5, the heating elements 5 can heat the specimen 22. The portion of the rotation path of the specimen 22 located downstream of the heating elements 5 is defined as... In the heating zone, since the heating elements 5 are arranged at intervals, there will be gaps between the heating elements 5. The cooling airflow output by the cooling air source 4 will pass through the gaps between the heating elements 5. When the specimen 22 rotates to the downstream of the gap between the heating elements 5, the cooling airflow comes into contact with the specimen 22 and takes away the heat of the specimen 22, thus cooling the specimen 22. The part of the specimen 22 located downstream of the gap between the heating elements 5 in the rotation path is defined as the cooling zone. The cooling zone and the heating zone are arranged alternately on the rotation path of the specimen 22. The specimen 22 will alternately undergo heating and cooling during the rotation process.

[0032] The heating power of each heating element 5 can be controlled independently. When the specimen 22 is rotated to different positions, it can be heated to different temperatures to simulate different temperature ranges when the blade is working.

[0033] This application uses multiple heating elements 5 spaced apart along the rotation path of the test specimen 22 within the intake section 3, and a cooling airflow is supplied to the intake section 3 via a cooling air source 4. The heating elements 5 heat the test specimen 22, and the cooling airflow passes through the gaps between the heating elements 5 to cool the test specimen 22. The spaced arrangement of the heating elements 5 divides the rotation path of the test specimen 22 into staggered heating and cooling zones. During the rotation of the test specimen 22, heating and cooling alternate, simulating the transient thermodynamic environment of a real engine during dynamic thermal cycle temperature control. Furthermore, by controlling the heating power of the heating elements 5, the rotation path of the test specimen 22 can be controlled. When the specimen is rotated to different positions and heated to different temperatures, the periodic temperature changes of the rotor blades can be more accurately reproduced. At the same time, when the specimen 22 is heated instantaneously in the heating zone, the surface temperature rises rapidly, while the internal material of the specimen 22 heats up more slowly due to thermal inertia. When the specimen 22 rotates to the cooling zone, the surface is rapidly cooled. This process will generate an instantaneous and huge temperature gradient in the thickness direction at the same position of the specimen 22. This gradient is typical of the high-pressure compressor blades in a real engine. In summary, this application can better simulate the actual working conditions of the blades of the upstream rotor of the combustion chamber, and can effectively improve the accuracy and authenticity of the test results.

[0034] Specifically, the installation platform 1 is a conventional technical means in this field, and this application will not elaborate on it.

[0035] Furthermore, the intake section 3 includes an intake section inner shell 31 and an intake section outer shell 32. The intake section inner shell 31 and the intake section outer shell 32 are coaxially arranged to form an annular intake air passage 33 for cooling airflow between the intake section inner shell 31 and the intake section outer shell 32. The intake section inner shell 31 is provided with a clearance opening for the test piece 22 to enter the annular intake air passage 33, or the test piece 22 is located at the outlet end of the annular intake air passage 33.

[0036] like Figure 1 As shown, the intake section 3 includes an inner intake section shell 31 and an outer intake section shell 32. The inner intake section shell 31 and the outer intake section shell 32 are coaxially arranged, and the diameter of the inner intake section shell 31 is smaller than the diameter of the outer intake section shell 32. Due to the diameter difference between the outer intake section shell 32 and the inner intake section shell 31, an annular airflow channel 33 is formed between the outer surface of the inner intake section shell 31 and the inner surface of the outer intake section shell 32. When the cooling air source delivers cooling airflow to the intake section 3, the cooling airflow enters the intake flow. At the same time, the inner intake section shell 31 is provided with a clearance port. This allows the specimen 22 to enter the annular inlet airflow channel 33. Once the specimen 22 enters the annular inlet airflow channel 33, the cooling airflow flowing in the annular inlet airflow channel 33 will pass through the specimen 22, or the specimen 22 may be located directly at the outlet end of the annular inlet airflow channel 33. The cooling airflow discharged from the annular inlet airflow channel 33 will also pass through the specimen 22. By restricting the cooling airflow through the airflow, the uniformity of the cooling airflow in different cooling areas is ensured, so as to control the cooling effect of the cooling area on the specimen 22, thereby ensuring the authenticity of the final test results.

[0037] When placing the test specimen 22 at the outlet end of the airflow channel, the distance between the test specimen 22 and the outlet end of the airflow channel should not be too far to avoid airflow escaping and causing differences in the cooling effect of each cooling zone.

[0038] In other examples, such as Figure 1 As shown, the outlet end of the air intake section shell 32 is closer to the mounting platform 1 than the outlet end of the air intake section inner shell 31, so that the air intake section shell 32 can enclose the test piece 22 and the auxiliary test piece 21. The air intake section shell 32 can further restrict the cooling airflow discharged from the outlet end of the annular air intake channel 33. Even after the cooling airflow is discharged from the annular air intake channel 33, the cooling airflow can still be restricted, further improving the uniformity of the cooling airflow after leaving the annular air intake channel 33. When the test piece 22 is placed at the outlet end of the annular air intake channel 33, the consistency of the cooling effect in different cooling areas can be better guaranteed.

[0039] Furthermore, the diameter of the inner shell 31 of the air intake section is smaller than the inner diameter of the rotation path of the specimen 22, and the heating element 5 is located in the annular air intake channel 33.

[0040] like Figure 1As shown, the diameter of the inner shell 31 of the air intake section is smaller than the inner diameter of the rotation path of the specimen 22. That is to say, the radial height of the annular air intake channel 33 is greater than the height of the specimen 22. The cooling airflow flowing in the annular air intake channel 33 can completely cover the specimen 22 in the height direction. When the specimen passes through the cooling area for cooling, the cooling airflow can cool the specimen comprehensively, avoiding local cooling. Similarly, when the radial height of the annular air intake channel 33 is greater than the height of the specimen 22, the heating element 5 can be directly installed in the annular air intake channel 33. At this time, the heating element 5 and the accompanying specimen 21 will be separated by the inner shell 31 of the air intake section. When the heating element 5 heats the specimen 22, it can effectively isolate the heat conduction between the heating element 5 and the accompanying specimen 21, reduce the temperature of the accompanying specimen 21 during the test, avoid the temperature of the accompanying specimen 21 from being too high during the test, and ensure test safety.

[0041] In order to ensure the heat insulation effect of the inner shell 31 of the air intake section on the heating element 5, the diameter of the inner shell 31 of the air intake section is as close as possible to the inner diameter of the rotation path of the test piece 22, so as to minimize the part of the test piece 21 entering the annular air intake channel 33 and improve the heat insulation effect of the inner shell 31 of the air intake section on the heating element 5.

[0042] Furthermore, the air outlet end of the air intake section inner shell 31 is provided with a baffle 34, and an air duct 35 is provided on the baffle 34. The air duct 35 is used to introduce the cooling airflow output by the cooling air source 4 to the downstream of the air intake section inner shell 31 to cool the test piece 21.

[0043] like Figure 1 As shown, in order to control the path of the cooling airflow and prevent the cooling airflow from entering the test specimen 21 and the test specimen 22 in a disorderly manner, a baffle 34 is provided at the air outlet end of the air inlet shell. At the same time, an air duct 35 is provided on the baffle 34. The cooling airflow upstream of the air inlet shell 31 can be introduced into the test specimen 21 through the air duct 35 to cool the test specimen 21. The cooling airflow used to cool the test specimen 22 and the test specimen 21 is controlled so that the cooling airflow can only cool the test specimen 22 and the test specimen 21 along the set path, which effectively improves the stability of the test environment.

[0044] Figure 1 A first example of a heating element 5 is disclosed, in which the heating element 5 includes a flame gun and the nozzle of the flame gun is directed toward the specimen 22;

[0045] In this example, the heating element 5 includes a flame gun, which is positioned upstream of the specimen 22. The flame jet end of the flame gun faces the specimen, so that the flame gun itself can shield the cooling airflow and protect the stability of the flame jet end. The flame gun can heat its outlet air to an extremely high temperature in a very short time, and the use of the flame gun equipment is relatively inexpensive.

[0046] Figure 4 A second example of the heating element 5 is disclosed. In this example, the heating element 5 includes a heating channel with an air inlet and an air outlet. The air inlet is used to introduce cooling airflow into the heating channel, and the air outlet is used to discharge the airflow in the heating channel into the rotation path of the specimen 22. A heating component is provided in the heating channel to heat the airflow flowing through the heating channel.

[0047] In this example, the heating element 5 includes a heating channel. Since there is cooling airflow in the annular inlet channel 33 during the test, the heating channel can be used to heat the cooling airflow in the annular inlet channel 33. The high-temperature airflow discharged through the heating channel heats the specimen 22. During use, the heating channel is located in the annular inlet channel 33. The cooling airflow in the annular inlet channel 33 enters the heating channel through the air inlet of the heating channel. The airflow is heated by the heating element in the heating channel. After the airflow in the heating channel is heated into heated airflow, it is discharged from the exhaust port of the heating channel and enters the rotation path of the specimen 22. When the specimen 22 rotates through the heated airflow, the specimen 22 will be heated, thereby achieving the heating of the specimen 22. By using the heating channel to heat the cooling airflow flowing through it, a stable and uniform heated airflow can be obtained. When heating the specimen 22 through the heated airflow, the specimen 22 can be heated to the set temperature more accurately, and the heating of the specimen 22 is more uniform, making the final test results more realistic.

[0048] Furthermore, such as Figure 4 As shown, multiple heating elements 5 are arranged at equal intervals along the rotation path of the specimen 22. When multiple heating elements 5 are arranged at equal intervals along the rotation path of the specimen 22, the gap between the heating elements 5 is also the same. Thus, when forming the heating area and the cooling area, the gap between the heating areas is the same, and the size and interval of the cooling areas are the same, so as to control the temperature of the specimen 22 during the rotation process.

[0049] Furthermore, such as Figure 4 As shown, the height of the heating element 5 in the radial direction of the air inlet section 3 is not less than the height of the test piece 22. When the test piece 22 is heated by the heating element 5, it can ensure that the heating effect of the heating element 5 in the height direction of the test piece 22 is uniform, avoid the temperature gradient in the height direction during the heating process of the test piece 22, and ensure that the test piece 22 is heated uniformly.

[0050] Furthermore, a cooling channel 321 for the flow of cooling medium is provided inside the intake section housing 32, and the cooling channel 321 is located downstream of the heating element 5 on the intake section housing 32.

[0051] like Figure 3As shown, during the test, the heating element 5 heats the downstream specimen 22. During the heating process, the part of the inner shell 31 of the intake section adjacent to it will also be heated. In order to prevent the outer shell 32 of the intake section from overheating, a cooling channel 321 is opened on the outer shell 32 of the intake section. Cooling medium can flow in the cooling channel 321 to remove the heat from the outer shell 32 of the intake section and prevent the outer shell 32 of the intake section from overheating. Since the location where the outer shell 32 of the intake section may overheat is the location closest to the downstream of the heating element 5, setting the cooling channel 321 at this location can effectively prevent the outer shell 32 of the intake section from overheating and make full use of the cooling medium.

[0052] This application does not impose any restrictions on the selection of cooling medium, as long as it can flow in the cooling channel 321 and carry the heat of the intake section shell 32.

[0053] Furthermore, an exhaust section 6 is connected downstream of the intake section 3. The exhaust section 6 includes an exhaust section inner shell 61 and an exhaust volute 62. The exhaust volute 62 is used to introduce the cooling airflow discharged from the intake section 3 and discharge it upward.

[0054] like Figure 1 As shown, an exhaust end is connected downstream of the intake section 3. The exhaust section 6 includes an exhaust section inner shell 61 and an exhaust volute 62. The diameter of the exhaust section inner shell 61 is smaller than that of the exhaust volute 62. By coaxially arranging the exhaust section inner shell 61 and the exhaust volute 62, an exhaust flow channel can be formed between the exhaust section inner shell 61 and the exhaust volute 62. The size of the exhaust flow channel matches that of the annular intake flow channel 33. When the cooling airflow in the annular intake flow channel 33 is discharged, the exhaust flow channel can receive the cooling airflow and discharge it after changing direction through the exhaust volute 62. This avoids the high-temperature cooling airflow from contacting the mounting platform 1, prevents the temperature of the mounting platform 1 from rising, ensures that the mounting platform 1 is at a suitable working temperature, and ensures the safety of the overall test.

[0055] Specifically, since the cooling airflow from the previous stage is not natural wind when the rotor blades are working, the cooling airflow output by the cooling air source 4 needs to be heated to the set temperature according to the requirements during the test. The ambient temperature can be heated to the required temperature by the overall heating scheme in the prior art, and then the airflow is generated by the cooling air source 4. Alternatively, a heating device can be directly installed in the cooling air source 4 to heat the cooling airflow output by the cooling air source 4 so that the cooling airflow output by the cooling air source 4 can reach the set temperature. These are all conventional technical means in this field, and will not be described in detail in this application.

[0056] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A high-temperature rotating table for engine rotor blade testing, comprising a mounting table (1) for mounting and driving in rotation a test partner (21) for mounting a test piece (22), characterized in that: The high-temperature rotary table for testing engine rotor blades also includes an intake section (3), a cooling air source (4), and a heating element (5); The inner cavity of the air intake section (3) is used to accommodate the test piece (22). Multiple heating elements (5) are provided. The heating elements (5) are arranged upstream of the test piece (22) in the air intake section. The multiple heating elements (5) are arranged at intervals along the rotation path of the test piece (22) to heat the test piece (22) at different positions on the rotation path of the test piece (22). The cooling air source (4) is used to deliver cooling airflow into the air intake section (3). A space for cooling airflow is formed between adjacent heating elements (5). The cooling airflow is used to pass through between adjacent heating elements (5) to cool the test piece (22). The intake section (3) includes an intake section inner shell (31) and an intake section outer shell (32). The intake section inner shell (31) and the intake section outer shell (32) are coaxially arranged to form an annular intake channel (33) for cooling airflow between the intake section inner shell (31) and the intake section outer shell (32). The intake section inner shell (31) is provided with a clearance port for the test piece (22) to enter the annular intake channel (33), or the test piece (22) is located at the outlet end of the annular intake channel (33). The diameter of the inner shell (31) of the air intake section is smaller than the inner diameter of the rotation path of the test piece (22), and the heating element (5) is located inside the annular air intake channel (33); The air outlet end of the air inlet section inner shell (31) is provided with a baffle (34), and an air duct (35) is provided on the baffle (34). The air duct (35) is used to introduce the cooling airflow output by the cooling air source (4) to cool the test piece (21). The height of the heating element (5) in the radial direction of the air intake section (3) is not less than the height of the test piece (22).

2. A high temperature spin stand for testing an engine rotor blade according to claim 1, characterized in that: The heating element (5) includes a flame gun, and the nozzle of the flame gun is directed toward the specimen (22).

3. A high temperature spin stand for testing an engine rotor blade as recited in claim 1, characterized by: The heating element (5) includes a heating channel, which is located in the air inlet section (3) and is positioned upstream of the test piece (22). The heating channel has an air inlet and an air outlet. The air inlet is used to introduce cooling airflow into the heating channel, and the air outlet is used to discharge the airflow in the heating channel into the rotation path of the test piece (22). The heating channel is provided with a heating component, which is used to heat the airflow flowing through the heating channel.

4. A high temperature spin stand for testing an engine rotor blade as recited in claim 1, characterized by: Multiple heating elements (5) are arranged at equal intervals along the rotation path of the specimen (22).

5. A high temperature spin stand for testing an engine rotor blade as recited in claim 1, characterized by: The intake section housing (32) has a cooling channel (321) for the flow of cooling medium, and the cooling channel (321) is located downstream of the heating element (5) on the intake section housing (32).

6. A high temperature spin stand for testing an engine rotor blade as recited in claim 1, characterized by: The intake section (3) is connected downstream to the exhaust section (6), which includes an exhaust section inner shell (61) and an exhaust volute (62). The exhaust volute (62) is used to introduce the cooling airflow discharged from the intake section (3) and discharge it upward.

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