Compressor test piece structure and compressor test piece testing system.

Abstract

This invention discloses a compressor test piece structure and a compressor test piece system having the same, comprising: a test piece body, an inlet auxiliary support device and a fixed exhaust device connected to the inlet and rear inlet ends of the test piece body. The inlet end of the inlet auxiliary support device is axially movable and circumferentially sealed to the inlet volute of the test bench equipment to form a "front simply supported structure," thereby radially limiting the inlet end of the test piece body and simultaneously compensating for axial thermal deformation of the test piece casing. The exhaust end of the fixed exhaust device is fixedly connected to the exhaust volute to form a "rear fixed support structure." In this invention, the inlet auxiliary support device provides a certain radial constraint capability to the inlet end of the test piece body, reducing the stiffness attenuation of the test piece casing at the inlet end, alleviating the long cantilever vibration problem caused by an excessively long test piece body, and also compensating for axial thermal deformation of the test piece casing.

Description

Technical Field

[0001] This invention relates to the field of compressor test piece structure design technology, and in particular, to a compressor test piece structure. Furthermore, this invention also relates to a compressor test piece testing system including the above-described compressor test piece structure. Background Technology

[0002] In aero engines, the compressor, driven by a rear turbine, performs work and pressurizes the gas. The compressor's performance significantly impacts the overall engine performance. A comprehensive evaluation of compressor performance requires various tests at multiple points, including the inlet, outlet, interstages, and blade surfaces, to measure airflow pressure, temperature, and direction. Performing these tests directly within the engine is risky and costly; therefore, engineering often involves designing a separate compressor test specimen and testing its performance on a test bench. A compressor test specimen typically includes the compressor body (i.e., the engine compressor components) and a transition section (i.e., components that provide intake, exhaust, power input, and test bench support for the compressor body; these are not engine compressor components).

[0003] Existing aero-engine compressor test pieces often use bolts to secure the exhaust casing and volute (part of the test bench equipment) at the rear end of the test piece body. This creates a rigid connection between the rear end of the test piece and the test bench, leaving the front end in a cantilever state, as exemplified by the compressor test piece structure in patent CN111312058B. This connection structure allows power input only through the rear end of the test piece. When structural limitations prevent power input from the rear, this support structure is unsuitable. Furthermore, when the test piece body is long, resulting in a long cantilever at the front end, excessive cantilever length can lead to significant vibration problems, making it impossible to conduct the test normally.

[0004] Another type of dual-rotor combined compressor test piece divides the dual-rotor engine compressor into a high-pressure section and a low-pressure section. The front end of the low-pressure section is fastened to the intake volute (belonging to the test vehicle equipment) by bolts, and the rear end of the high-pressure section is fastened to the exhaust volute (belonging to the test vehicle equipment) by bolts. The front and rear of the test piece are rigidly connected to the test bench, which is a support structure with complete front and rear fixed support, such as the existing patent CN115184026A dual-rotor combined compressor test piece and compressor performance testing method. This type of test specimen support structure allows power input to both the front and rear ends of the test specimen, meeting the power requirements of a dual-rotor compressor test. However, during the test, the flow channel components of the compressor test specimen perform work on the airflow, causing the test specimen temperature to rise and inevitably leading to thermal deformation. The fully fixed support structure at the front and rear of the test specimen cannot compensate for this deformation. Therefore, an additional transition section (not an engine compressor part) containing flexible connecting components is added between the high-pressure compressor body and the low-pressure compressor body. The deformation of the flexible components compensates for the thermal deformation of the test specimen. The main purpose of the compressor test specimen is to accurately measure the performance of the compressor when operating in an aero-engine. Therefore, the closer the compressor test specimen structure is to the engine, the more accurate the test results will be. In this structure, the transition section containing flexible connecting components is a compromise design to compensate for the inability of the fully fixed support structure at the front and rear of the test specimen to compensate for deformation. It is not a component of the aero-engine compressor body and is an artificially introduced interference factor, which will inevitably have a certain impact on the accuracy of the test results and reduce the precision of the test results. Summary of the Invention

[0005] This invention provides a compressor test specimen structure and a compressor test specimen testing system thereof, to solve the following technical problems with existing compressor test specimens: when the structure is limited and power input cannot be achieved through the rear end, this support structure is not applicable; when the test specimen body is long, forming a long cantilever at the front end, the excessively long cantilever can easily cause large vibration problems, making it impossible to carry out the test normally; and due to the introduction of interference factors, the accuracy of the test results is affected, reducing the precision of the test results.

[0006] The technical solution adopted in this invention is as follows:

[0007] A compressor test piece structure includes: a test piece body, an inlet auxiliary support device connected to the inlet air end of the test piece body, and a fixed exhaust device connected to the rear exhaust end of the test piece body; the inlet air end of the inlet auxiliary support device is used to be axially movable and circumferentially sealed to the inlet volute of the test vehicle equipment to form a "front simply supported structure", thereby limiting the inlet air end of the test piece body radially and compensating for thermal deformation of the test piece casing of the test piece body axially; the exhaust end of the fixed exhaust device is used to be fixedly connected to the exhaust volute of the test vehicle equipment to form a "rear fixed support structure".

[0008] Furthermore, the imported auxiliary support device includes an intake casing, the exhaust end of which is fixedly connected to the inlet end of the test piece body; the inlet end of the intake casing is used to connect with the intake volute, and an axial movable connection structure and a circumferential sealing structure are formed at the connection between the two. The axial movable connection structure is used to connect the intake casing and the intake volute to radially limit the inlet end of the test piece body, and also to compensate for the thermal deformation of the test piece casing along the axial direction; the circumferential sealing structure is used to seal the gap at the connection between the intake casing and the intake volute.

[0009] Furthermore, the axial movable connection structure includes multiple cantilever brackets connected to the outer annular wall of the intake end of the intake casing, spherical bearings disposed in each cantilever bracket, and pins passing through each spherical bearing along the axial direction. The multiple cantilever brackets are arranged sequentially at intervals along the circumference of the outer annular wall on one side of the intake casing. The axial movable connection structure also includes multiple connecting forks disposed corresponding to each cantilever bracket and fixed to the exhaust end of the intake volute. Each connecting fork has a concave fork opening, the outer end of the cantilever bracket extends into the corresponding fork opening, and the two ends of the pin pass through the two opposite side walls of the fork opening.

[0010] Furthermore, the axial movable connection structure includes multiple overhanging plates connected to the outer annular wall of the intake end of the intake casing. Each overhanging plate protrudes radially toward the intake volute to form a connecting protrusion. The outer end of the connecting protrusion is machined to form an axially curved arc sliding contact surface, which is used to abut against the annular surface of the exhaust end of the intake volute.

[0011] Furthermore, the circumferential sealing structure includes two annular mounting grooves formed by the concave extension of two outer annular surfaces on both sides of the intake end of the intake casing, and an inflation ring arranged in each annular mounting groove; the two inflation rings are used to abut against two inner annular surfaces on both sides of the exhaust end of the intake volute after inflation, thereby forming two circumferential seals.

[0012] Furthermore, the circumferential sealing structure includes four annular mounting grooves formed by the concave extension of two outer annular surfaces on both sides of the intake end of the intake casing; each of the two annular mounting grooves on each side of the intake casing is equipped with a first energy storage ring and a sealing ring, which are used to abut against the two inner annular surfaces on both sides of the exhaust end of the intake volute to form multiple circumferential seals.

[0013] Furthermore, the compressor test piece structure also includes a front power input adapter shaft and a rear power input adapter shaft spaced back and forth along the axial direction, and a displacement compensation shaft assembly arranged between the two along the axial direction. The front power input adapter shaft and the displacement compensation shaft assembly are sequentially installed in the inlet auxiliary support device, and the displacement compensation shaft assembly is located between the front power input adapter shaft and the rotor of the test piece body. The front power input adapter shaft and the rotor extend into the displacement compensation shaft assembly from both ends of the displacement compensation shaft assembly and are splinedly connected to the displacement compensation shaft assembly to compensate for the interference of thermal deformation of the test piece casing and rotor on the rotor. The rear power input adapter shaft is installed in the fixed exhaust device and is fixedly connected to the rotor along the axial direction.

[0014] Furthermore, the displacement compensation shaft assembly includes a hollow displacement compensation shaft with both ends connected, and multiple retaining rings that are spaced apart and fixedly installed in the displacement compensation shaft along the axial direction; the front power input adapter shaft extends into the displacement compensation shaft along the axial direction and is splinedly connected to the displacement compensation shaft through a first spline structure, with the first spline structure located between two adjacent retaining rings; the rotor extends into the displacement compensation shaft along the axial direction and is splinedly connected to the displacement compensation shaft through a second spline structure, with the second spline structure located between two adjacent retaining rings.

[0015] Furthermore, the compressor test piece structure also includes at least two sets of rotor-stator connection structures, wherein at least one set of rotor-stator connection structures is disposed between the front power input adapter shaft and the inlet auxiliary support device, and the remaining at least one set of rotor-stator connection structures is disposed between the rear power input adapter shaft and the fixed support exhaust device; the rotor-stator connection structures are used to rotatably connect the front power input adapter shaft and the rear power input adapter shaft to the corresponding inlet auxiliary support device and the fixed support exhaust device, respectively, and at the same time to reduce the interference of vibration on the rotor.

[0016] According to another aspect of the present invention, a compressor test piece testing system is also provided, having a compressor test piece structure as described in any of the above.

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

[0018] This invention proposes a compressor test piece structure. The inlet auxiliary support device is located at the air inlet end of the test piece body, providing auxiliary support for the test piece body. It is combined with the fixed exhaust device located at the exhaust end of the test piece body to form a "simple support in front and fixed support in the back" support layout. Compared with the conventional compressor test piece structure, the inlet auxiliary support device has radial constraint capability on the test piece body, while allowing the compressor test piece structure to have displacement freedom in the axial direction, thus forming a simple support with incomplete constraint. Because the imported auxiliary support device has a certain radial constraint capability on the inlet end of the test piece body, it can provide auxiliary support for the test piece body to reduce the stiffness attenuation of the test piece casing at the inlet end of the test piece body, and at the same time alleviate the long cantilever vibration problem caused by the excessive length of the test piece body; on the other hand, during the operation, when the test piece body expands due to heat generation, the deformation displacement of the test piece body accumulates towards the inlet end due to the fixed constraint of the exhaust device and the exhaust volute on its exhaust end. At this time, the imported auxiliary support device can slide forward to compensate for thermal deformation. After the test, the test piece body cools and shrinks, and the imported auxiliary support device slides backward to compensate for cooling deformation; in addition, the imported auxiliary support device is also circumferentially sealed to the exhaust end of the intake volute to prevent the airflow passage from communicating with the external atmospheric environment.

[0019] Specifically, in the dual-rotor compressor test piece using the imported auxiliary support of this invention, the low-pressure compressor, transition section, and high-pressure compressor of the test piece body can all maintain a rigid connection consistent with the engine body. The exhaust end of the high-pressure compressor is fixedly supported on the exhaust volute, and the intake end of the low-pressure compressor is supported on the intake volute through the imported auxiliary support device. The airflow enters the imported auxiliary support device through the intake volute, and then passes through the low-pressure compressor, transition section, and high-pressure compressor before being discharged from the exhaust volute. No compromise design for deformation compensation is introduced into the test piece body, so it will not affect the accuracy of the test results, and the test results are highly accurate. At the same time, since the low-pressure compressor, transition section, and high-pressure compressor are rigidly connected and the exhaust end is fixed, the thermal deformation of the test piece body accumulates at the intake end. The axial thermal deformation of the inlet section is relatively large. The imported auxiliary support device of this invention can provide a large axial displacement compensation capability, while providing auxiliary support for the inlet end, reducing the stiffness loss of the casing and playing a certain role in vibration reduction.

[0020] 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

[0021] 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:

[0022] Figure 1 This is a front view schematic diagram of the compressor test piece structure according to a preferred embodiment of the present invention;

[0023] Figure 2 yes Figure 1 Schematic diagram of force transmission and deformation compensation in the structure of the medium-compression air turbine test piece;

[0024] Figure 3 Figure 1 A schematic diagram showing the connection between the mid-displacement compensation shaft assembly and the front power input adapter shaft and rotor.

[0025] Figure 4 yes Figure 1 A schematic diagram of the main structure of the intermediate stator connection structure;

[0026] Figure 5 This is a schematic diagram of an embodiment of the axial movable connection structure and the circumferential sealing structure;

[0027] Figure 6 This is a schematic diagram of Embodiment 2 of the axial movable connection structure and circumferential sealing structure;

[0028] Figure 7 This is a schematic diagram of Embodiment 2 of the circumferential sealing structure.

[0029] Legend:

[0030] 11. Intake volute; 12. Exhaust volute;

[0031] 2. Test specimen body; 21. Test specimen casing; 22. Rotor;

[0032] 3. Intake casing;

[0033] 4. Axial movable connection structure; 41. Cantilever bracket; 42. Spherical bearing; 43. Pin; 44. Connecting fork; 45. Cantilever plate; 46. Connecting protrusion; 460. Arc-shaped sliding contact surface;

[0034] 5. Circumferential sealing structure; 51. Inflatable expansion ring; 52. First energy storage ring; 53. Sealing ring;

[0035] 6. Front-mounted power input adapter shaft; 7. Rear-mounted power input adapter shaft;

[0036] 8. Displacement compensation shaft assembly; 81. Displacement compensation shaft; 82. Snap ring; 83. First spline structure; 84. Second spline structure;

[0037] 9. Rotor-stator connection structure; 91. Connecting bearing; 92. Vibration isolation ring; 93. Second energy storage ring. Detailed Implementation

[0038] 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.

[0039] Reference Figure 1-2 A preferred embodiment of the present invention provides a compressor test piece structure, comprising: a test piece body 2, an inlet auxiliary support device connected to the inlet air end of the test piece body 2, and a fixed exhaust device connected to the rear exhaust end of the test piece body 2. The inlet air end of the inlet auxiliary support device is axially movable and circumferentially sealed to the inlet volute 11 of the test bench equipment to form a "front simply supported structure," thereby radially limiting the inlet air end of the test piece body 2 and simultaneously compensating for thermal deformation of the test piece casing 21 of the test piece body 2 axially. The exhaust end of the fixed exhaust device is fixedly connected to the exhaust volute 12 of the test bench equipment to form a "rear fixed support structure."

[0040] This invention proposes a compressor test piece structure. The inlet auxiliary support device is located at the air inlet end of the test piece body 2, providing auxiliary support for the test piece body 2. It is combined with the fixed exhaust device located at the exhaust end of the test piece body 2 to form a "front simply supported and rear fixed supported" support layout. Compared with the conventional compressor test piece structure, the inlet auxiliary support device has radial constraint capability on the test piece body 2, while allowing the compressor test piece structure to have displacement freedom in the axial direction, thus forming a simply supported structure with incomplete constraint. Since the imported auxiliary support device has a certain radial constraint capability on the inlet end of the test piece body 2, it can provide auxiliary support for the test piece body 2 to reduce the stiffness attenuation of the test piece casing 21 at the inlet end of the test piece body 2, and at the same time alleviate the long cantilever vibration problem caused by the excessive length of the test piece body 2; on the other hand, during the operation, when the test piece body 2 expands due to heat generation, the deformation displacement of the test piece body 2 accumulates towards the inlet end based on the fixed constraint of the exhaust device and the exhaust volute 12 on its exhaust end. At this time, the imported auxiliary support device can slide forward to compensate for thermal deformation. After the test, the test piece body 2 cools and shrinks, and the imported auxiliary support device slides backward to compensate for cooling deformation; in addition, the imported auxiliary support device is also circumferentially sealed to the exhaust end of the intake volute 11 to prevent the airflow passage from communicating with the external atmospheric environment.

[0041] Specifically, in the dual-rotor compressor test piece using the imported auxiliary support of the present invention, the low-pressure compressor, transition section, and high-pressure compressor of the test piece body can all maintain a rigid connection consistent with the engine body. The exhaust end of the high-pressure compressor is fixedly supported on the exhaust volute 12, and the intake end of the low-pressure compressor is supported on the intake volute 11 through the imported auxiliary support device. The airflow enters the imported auxiliary support device through the intake volute 11, and then passes through the low-pressure compressor, transition section, and high-pressure compressor before being discharged from the exhaust volute 12. No compromise design for deformation compensation is introduced into the test piece body, so it will not affect the accuracy of the test results, and the test results are highly accurate. At the same time, since the low-pressure compressor, transition section, and high-pressure compressor are rigidly connected and the exhaust end is fixed, the thermal deformation of the test piece body accumulates at the intake end, and the axial thermal deformation of the inlet section is relatively large. The imported auxiliary support device of the present invention can provide a large axial displacement compensation capability, while providing auxiliary support for the inlet end, reducing the stiffness loss of the casing and playing a certain role in vibration reduction.

[0042] Optionally, such as Figure 1 As shown, the imported auxiliary support device includes an intake casing 3, the exhaust end of which is fixedly connected to the inlet end of the test piece body 2. The inlet end of the intake casing 3 is used to connect with the intake volute 11, and an axial movable connection structure 4 and a circumferential sealing structure 5 are formed at the connection between the two. The axial movable connection structure 4 is used to connect the intake casing 3 and the intake volute 11 to radially limit the inlet end of the test piece body 2, and also to compensate for thermal deformation of the test piece casing 21 along the axial direction. The circumferential sealing structure 5 is used to seal the gap at the connection between the intake casing 3 and the intake volute 11.

[0043] In this optional solution, the first embodiment of the axial movable connection structure 4 is as follows: Figure 5 As shown, the axial movable connection structure 4 includes multiple cantilever brackets 41 connected to the outer annular wall of the intake end of the intake casing 3, spherical bearings 42 disposed within each cantilever bracket 41, and pins 43 axially passing through each spherical bearing 42. The multiple cantilever brackets 41 are arranged sequentially at intervals along the circumference of the outer annular wall on one side of the intake casing 3. The axial movable connection structure 4 also includes multiple connecting forks 44 corresponding to each cantilever bracket 41 and fixed to the exhaust end of the intake volute 11. Each connecting fork 44 has a concave fork opening, the outer end of the cantilever bracket 41 extends into the corresponding fork opening, and the two ends of the pin 43 respectively pass through the two opposite side walls of the fork opening. During the design, the pin 43 is fixed to the connecting fork 44, and the spherical bearing 42 slides through the pin 43. During axial thermal compensation, the test piece casing 21 drives the intake casing 3 to expand and move towards the intake end. At this time, the cantilever bracket 41 drives the spherical bearing 42 to slide along the pin 43, thereby compensating for the thermal expansion of the test piece body 2. At the same time, through the connection between the pin 43 and the connecting fork 44, the inlet end of the test piece body 2 is also radially limited.

[0044] In this optional solution, the second embodiment of the axial movable connection structure 4, as follows: Figure 6 As shown, the axial movable connection structure 4 includes multiple overhanging plates 45 connected to the outer annular wall of the intake end of the intake casing 3. Each overhanging plate 45 protrudes radially toward the intake volute 11 to form a connecting protrusion 46. The outer end of the connecting protrusion 46 is machined to form an axially curved arc-shaped sliding contact surface 460, which is used to abut against the annular surface of the exhaust end of the intake volute 11. During operation, the test specimen casing 21 drives the intake casing 3 to expand and move toward the intake end. At this time, the overhanging plates 45 drive the connecting protrusion 46 to slide axially relative to the annular surface of the exhaust end of the intake volute 11 through the arc-shaped sliding contact surface 460, thereby compensating for the thermal expansion of the test specimen body 2. At the same time, the contact between the arc-shaped sliding contact surface 460 on the connecting protrusion 46 and the annular surface of the exhaust end of the intake volute 11 limits the intake end of the test specimen body 2 radially. In addition, the design of the arc-shaped sliding contact surface 460 of the connecting protrusion 46 is also important.

[0045] In this optional solution, the first embodiment of the circumferential sealing structure 5 is as follows: Figure 5 and Figure 6 As shown, the circumferential sealing structure 5 includes two annular mounting grooves formed by the concave extension of two outer annular surfaces on both sides of the intake end of the intake casing 3, and inflatable expansion rings 51 arranged in each annular mounting groove. The two inflatable expansion rings 51 are used to abut against two inner annular surfaces on both sides of the exhaust end of the intake volute 11 after inflation, thereby forming two circumferential seals. During operation, the inlet auxiliary support device has axial displacement freedom, resulting in a gap between the inlet auxiliary support device and the intake volute 11, causing the airflow passage between the two to be connected to the external atmospheric environment. In this optional scheme, an inflatable expansion ring 51 is designed between the inlet auxiliary support device and the intake volute 11. By inflating the inflatable expansion ring 51, the inflatable expansion ring 51 protrudes and seals the gap between the two, forming a sealing effect. At the same time, the gas pressure inside the inflatable expansion ring 51 can also form a damping effect to reduce device vibration.

[0046] In this optional solution, the first embodiment of the circumferential sealing structure 5 is as follows: Figure 7 As shown, the circumferential sealing structure 5 includes four annular mounting grooves formed by the concave extension of two outer annular surfaces on both sides of the intake end of the intake casing 3. Each of the two annular mounting grooves on each side of the intake casing 3 is equipped with a first energy storage ring 52 and a sealing ring 53, which respectively abut against the two inner annular surfaces on both sides of the exhaust end of the intake volute 11 to form multiple circumferential seals. In this optional embodiment, the first energy storage ring 52 is a structure in which a metal spring is wrapped in a rubber-plastic material, which can play a damping and vibration reduction role; the sealing ring 53 is an O-ring, which plays a sealing role, thereby achieving both vibration reduction and sealing effects.

[0047] Optionally, such as Figure 2 and Figure 3As shown, the compressor test piece structure also includes a front power input adapter shaft 6 and a rear power input adapter shaft 7 spaced axially, and a displacement compensation shaft assembly 8 arranged axially between them. The front power input adapter shaft 6 and the displacement compensation shaft assembly 8 are sequentially installed in the inlet auxiliary support device, and the displacement compensation shaft assembly 8 is located between the front power input adapter shaft 6 and the rotor 22 of the test piece body 2. The front power input adapter shaft 6 and the rotor 22 extend into the displacement compensation shaft assembly 8 from both ends and are splined to the displacement compensation shaft assembly 8 to compensate for the interference of thermal deformation of the test piece casing 21 and the rotor 22 on the rotor 22. The rear power input adapter shaft 7 is installed in the fixed exhaust device and is fixedly connected to the rotor 22 axially. During operation, the rotor 22 needs to be supported on the imported auxiliary support device by bearings. In addition to the thermal deformation of the rotor 22 itself, the thermal deformation of the test specimen casing 21 is also transmitted to the rotor 22 through the ball bearings, resulting in a large axial displacement of the rotor 22 and affecting the stability of rotor operation. In order to solve this technical problem, a displacement compensation shaft assembly 8 is designed between the front power input adapter shaft 6 and the rotor 22 of the test specimen body 2. The two axial ends of the displacement compensation shaft assembly 8 are splinedly connected to the front power input adapter shaft 6 and the rotor 22, respectively, thereby compensating for the interference of the thermal deformation of the test specimen casing 21 and the rotor 22 on the rotor 22 by sliding compensation of axial displacement.

[0048] In this optional solution, such as Figure 3 As shown, the displacement compensation shaft assembly 8 includes a hollow displacement compensation shaft 81 with both ends connected, and multiple retaining rings 82 that are spaced apart axially and fixedly installed within the displacement compensation shaft 81. A front-mounted power input adapter shaft 6 extends axially into the displacement compensation shaft 81 and is splinedly connected to the displacement compensation shaft 81 via a first spline structure 83, with the first spline structure located between two adjacent retaining rings 82. A rotor 22 extends axially into the displacement compensation shaft 81 and is splinedly connected to the displacement compensation shaft 81 via a second spline structure 84, with the second spline structure located between two adjacent retaining rings 82. In this optional embodiment, the retaining rings 82 are used to limit the axial sliding of the front-mounted power input adapter shaft 6 and the rotor 22.

[0049] Optionally, such as Figure 1 and Figure 4As shown, the compressor test specimen structure also includes at least two sets of rotor-stator connection structures 9. At least one set of rotor-stator connection structures 9 is located between the front power input adapter shaft 6 and the inlet auxiliary support device, while the remaining at least one set of rotor-stator connection structures 9 is located between the rear power input adapter shaft 7 and the fixed exhaust device. The rotor-stator connection structures 9 are used to rotatably connect the front power input adapter shaft 6 and the rear power input adapter shaft 7 to their respective inlet auxiliary support devices and fixed exhaust devices, and also to reduce vibration interference on the rotor 22. During operation, to reduce the impact of vibration of the test specimen casing 21 on the operation of the rotor 22, at least one set of rotor-stator connection structures 9 is provided between the front power input adapter shaft 6 and the inlet auxiliary support device, and between the rear power input adapter shaft 7 and the fixed exhaust device, respectively, to reduce vibration interference on the rotor 22.

[0050] In this optional solution, such as Figure 4 As shown, the rotor-stator connection structure 9 includes a connecting bearing 91 mounted on the outer circle of the front power input adapter shaft 6 or the rear power input adapter shaft 7, a vibration isolation ring 92 fitted on the outer circle of the connecting bearing 91, and two second energy storage rings 93 mounted on the outer circles of the two ends of the vibration isolation ring 92 along the axial direction. The two second energy storage rings 93 are clamped in the shaft holes of the inlet auxiliary support device or the fixed support exhaust device. During operation, the two second energy storage rings 93 at both ends of the vibration isolation ring 92 form an annular cavity with the shaft holes of the inlet auxiliary support device or the fixed support exhaust device. By introducing high-pressure oil, a vibration isolation oil cavity is formed. The second energy storage rings 93 and the high-pressure oil together provide support. The support stiffness can be adjusted by adjusting the oil pressure. The second energy storage rings 93 and the high-pressure oil also have a damping function, which can absorb the vibration energy of the test piece casing 21 and reduce the impact on the rotor 22.

[0051] A preferred embodiment of the present invention also provides a compressor test piece testing system, characterized in that it has a compressor test piece structure as described above. Thus, the compressor test piece testing system of the present invention, due to the radial constraint capability of the inlet auxiliary support device on the inlet end of the test piece body 2, can provide auxiliary support for the test piece body 2, thereby reducing the stiffness attenuation of the test piece casing 21 at the inlet end of the test piece body 2, and simultaneously alleviating the long cantilever vibration problem caused by the excessive length of the test piece body 2. On the other hand, during operation, when the test piece body 2 expands due to heat generation, based on the fixed constraint of the exhaust device and the exhaust volute 12 on its exhaust end, the deformation displacement of the test piece body 2 accumulates towards the intake end. At this time, the inlet auxiliary support device can slide forward to compensate for thermal deformation. After the test, the test piece body 2 cools and contracts, and the inlet auxiliary support device slides backward to compensate for cooling deformation. In addition, the inlet auxiliary support device is also circumferentially sealed to the exhaust end of the intake volute 11 to prevent the airflow passage from communicating with the external atmospheric environment. In particular, when using this invention to test a dual-rotor compressor test piece, no compromise design for deformation compensation is introduced within the test piece itself, so it will not affect the accuracy of the test results, and the test results are highly accurate.

[0052] The above description is merely a preferred embodiment of the present invention and is not intended to limit the 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 compressor test piece structure, characterized in that, include: Test specimen body (2), inlet auxiliary support device connected to the front air end of test specimen body (2), and fixed exhaust device connected to the rear exhaust end of test specimen body (2); The air inlet of the imported auxiliary support device is used to axially move and circumferentially seal the air inlet volute (11) of the test vehicle platform to form a "front simple support structure", thereby limiting the front air inlet of the test piece body (2) radially, and simultaneously compensating for thermal deformation of the test piece casing (21) of the test piece body (2) axially. The exhaust end of the fixed support exhaust device is used to be fixedly connected to the exhaust volute (12) of the test vehicle platform equipment to form a "rear fixed support structure"; The imported auxiliary support device includes an intake casing (3), the exhaust end of which is fixedly connected to the inlet end of the test piece body (2); the inlet end of the intake casing (3) is used to connect with the intake volute (11), and an axial movable connection structure (4) and a circumferential sealing structure (5) are formed at the connection between the two. The axial movable connection structure (4) is used to connect the intake casing (3) with the intake volute (11) to radially limit the inlet end of the test piece body (2), and is also used to compensate for the thermal deformation of the test piece casing (21) along the axial direction; the circumferential sealing structure (5) is used to seal the gap at the connection between the intake casing (3) and the intake volute (11). The axial movable connection structure (4) includes multiple cantilever brackets (41) connected to the outer ring wall of the intake end of the intake casing (3), spherical bearings (42) disposed in each cantilever bracket (41), and pins (43) disposed axially through each spherical bearing (42). The multiple cantilever brackets (41) are arranged sequentially at intervals along the circumference of the outer ring wall on one side of the intake casing (3). The axial movable connection structure (4) also includes multiple connecting forks (44) disposed corresponding to each cantilever bracket (41) and fixed to the exhaust end of the intake volute (11). Each connecting fork (44) has a concave fork opening. The outer end of the cantilever bracket (41) extends into the corresponding fork opening, and the two ends of the pin (43) are respectively disposed in the two side walls opposite to the fork opening. Alternatively, the axial movable connection structure (4) includes multiple overhang plates (45) connected to the outer annular wall of the intake end of the intake casing (3), each overhang plate (45) protruding radially toward the intake volute (11) to form a connecting protrusion (46); the outer end of the connecting protrusion (46) is machined to form an axially curved arc sliding contact surface (460), the arc sliding contact surface (460) is used to abut against the annular surface of the exhaust end of the intake volute (11); The circumferential sealing structure (5) includes two annular mounting grooves formed by the concave extension of two outer annular surfaces on both sides of the intake end of the intake casing (3), and an inflation ring (51) arranged in each annular mounting groove; the two inflation rings (51) are used to abut against the two inner annular surfaces on both sides of the exhaust end of the intake volute (11) after inflation, thereby forming two circumferential seals. Alternatively, the circumferential sealing structure (5) includes four annular mounting grooves formed by the concave extension of two outer annular surfaces on both sides of the intake end of the intake casing (3); each of the two annular mounting grooves on each side of the intake casing (3) is equipped with a first energy storage ring (52) and a sealing ring (53) to abut against the two inner annular surfaces on both sides of the exhaust end of the intake volute (11) to form multiple circumferential seals.

2. The compressor test specimen structure according to claim 1, characterized in that, The compressor test piece structure also includes a front power input adapter shaft (6) and a rear power input adapter shaft (7) arranged axially at intervals, and a displacement compensation shaft group (8) arranged axially between the two. The front power input adapter shaft (6) and the displacement compensation shaft assembly (8) are sequentially installed in the inlet auxiliary support device. The displacement compensation shaft assembly (8) is located between the front power input adapter shaft (6) and the rotor (22) of the test piece body (2). The front power input adapter shaft (6) and the rotor (22) extend into the displacement compensation shaft assembly (8) from both ends of the displacement compensation shaft assembly (8) and are splined to the displacement compensation shaft assembly (8) to compensate for the interference of the thermal deformation of the test piece casing (21) and the rotor (22) on the rotor (22). The rear power input adapter shaft (7) is installed in the fixed exhaust device and is fixedly connected to the rotor (22) along the axial direction.

3. The compressor test specimen structure according to claim 2, characterized in that, The displacement compensation shaft assembly (8) includes a hollow displacement compensation shaft (81) with both ends connected, and multiple retaining rings (82) that are spaced apart along the axial direction and fixedly installed inside the displacement compensation shaft (81). The front power input adapter shaft (6) extends axially into the displacement compensation shaft (81) and is splinedly connected to the displacement compensation shaft (81) through the first spline structure, and the first spline structure is located between two adjacent retaining rings (82); The rotor (22) extends axially into the displacement compensation shaft (81) and is splined to the displacement compensation shaft (81) through a second spline structure, with the second spline structure located between two adjacent retaining rings (82).

4. The compressor test specimen structure according to claim 2, characterized in that, The compressor test piece structure also includes at least two sets of rotor-stator connection structures (9), wherein at least one set of rotor-stator connection structures (9) is located between the front power input adapter shaft (6) and the inlet auxiliary support device, and the remaining at least one set of rotor-stator connection structures (9) is located between the rear power input adapter shaft (7) and the fixed exhaust device. The rotor-stator connection structure (9) is used to rotatably connect the front power input adapter shaft (6) and the rear power input adapter shaft (7) to the corresponding inlet auxiliary support device and fixed support exhaust device, respectively, and at the same time to reduce the vibration interference to the rotor (22).

5. A compressor test piece testing system, characterized in that, It has the structure of a compressor test piece as described in any one of claims 1-4.

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