Compressor test stand, test method, compressor and gas turbine engine

Abstract

The application provides a compressor test bench, a test method, a compressor and a gas turbine engine. The compressor test bench comprises a first fluid pipeline, a second fluid pipeline and a fluid transmission control system. The first fluid pipeline and the second fluid pipeline are connected with a compressor to be tested. The first fluid pipeline and the second fluid pipeline are used for conveying fluid to an internal space defined by a drum, so that the fluid exchanges heat with a wheel disc of the compressor. The fluid transmission control system is used for controlling the fluid input into the first fluid pipeline and the second fluid pipeline. The test bench has a first state and a second state. The structure for conveying fluid into the drum through the first fluid pipeline and the second fluid pipeline can actively control the wheel disc heat exchange of the input fluid and the tip clearance of the compressor rotor, and the structure is simple, easy to build and debug.

Description

Technical Field

[0001] This invention relates to the field of compressor testing technology, and in particular to a compressor test bench, test method, compressor, and gas turbine engine. Background Technology

[0002] The blade tip clearance of the compressor rotor blades in an aero-engine is crucial to the compressor's performance and safe operation. If the blade tip clearance is too large, the compressor's aerodynamic performance will be significantly reduced, while if the blade tip clearance is too small, there will be significant safety hazards in the compressor's operation, as it is easy to cause collisions and friction with the casing, leading to safety accidents. Whether in the testing and verification stage or in the actual engine operation stage, it is desirable to keep the compressor rotor blade tip clearance within a certain range. However, in the actual operation of the compressor, it is difficult to actively control the compressor rotor blade tip clearance.

[0003] Changes in blade tip clearance are often a result of the coupling of factors such as the centrifugal force of the blades, the thermal expansion of the blades, the thermal expansion of the rotor disk, and the thermal expansion of the casing. These numerous influencing factors make accurate simulation and calculation difficult, frequently leading to excessively small blade tip clearances in actual test specimens. Especially during the experimental verification phase, when experience is insufficient, for safety reasons, it is necessary to disassemble the rotor, scrape the blade tips, and then reassemble it for testing. This entire disassembly and reassembly process is extremely costly in terms of manpower, resources, and time. Conversely, if the blade tip clearance is too large, it may result in poor performance of the test specimen, deviating significantly from the design goals, leading to inaccurate and unusable test results, or even the scrapping of the test specimen. Therefore, if an active clearance control method can be adopted during testing, allowing for more flexible clearance control, it can greatly facilitate the smooth conduct of tests and make clearance studies more convenient, reducing the need for repeated disassembly and reassembly processes and minimizing the waste of manpower, resources, and time. In actual engine operation, active blade tip clearance control technology can maximize compressor performance and reduce engine fuel consumption while ensuring safe compressor operation.

[0004] In existing technologies, most solutions adjust the thermal expansion of the compressor casing to affect the rotor tip clearance. For example, Chinese invention patent CN 112595520 A, entitled "Compressor Test Bench and Test Method," relates to a compressor test bench including a housing and a fluid transfer control system. The inner wall of the housing and the outer wall of the compressor casing form a heat transfer fluid channel with a gap between them. The heat transfer fluid channel has an inlet for receiving fluid and an outlet for discharging fluid. The fluid transfer control system controls the fluid entering the heat transfer fluid channel through the inlet. In the test state of the compressor test bench, the fluid transfer control system activates fluid transfer to the inlet and outlet of the heat transfer fluid channel, allowing the fluid to flow in the channel and transfer heat with the outer wall of the compressor casing, thereby adjusting the thermal expansion of the compressor casing in the test state and thus adjusting the compressor rotor tip clearance in the test state. Existing technical solutions are complex in structure, have large overall equipment size, and are difficult to set up and debug, which brings many inconveniences to the testing and actual operation phases. Summary of the Invention

[0005] The purpose of this invention is to provide a compressor test bench.

[0006] Another object of the present invention is to provide a compressor testing method.

[0007] Another object of the present invention is to provide an air compressor.

[0008] Another object of the present invention is to provide a gas turbine engine.

[0009] According to one aspect of the present invention, a compressor test bench includes: a first fluid line and a second fluid line connected to a compressor to be tested; the first fluid line and the second fluid line are fixedly connected to the drum of the compressor for conveying fluid to the internal space defined by the drum, so that the fluid exchanges heat with the compressor disc; the axial position of the first fluid line is located before the first stage of the compressor, and the axial position of the second fluid line is located after the last stage of the compressor; a fluid transfer control system is used to control the fluid input to the first fluid line and the second fluid line; the test bench has a first state and a second state. In the first state, the fluid transmission control system controls fluid at a first temperature to enter the internal space defined by the drum from one of the first fluid line and the second fluid line, and to exit the internal space from the other of the first fluid line and the second fluid line, in order to cool the wheel; in the second state, the fluid transmission control system controls fluid at a second temperature to enter the internal space defined by the drum from one of the first fluid line and the second fluid line, and to exit the internal space from the other of the first fluid line and the second fluid line, in order to heat the wheel, wherein the second temperature is greater than the first temperature.

[0010] In one or more embodiments of the compressor test bench, in the first state, fluid at the first temperature enters the internal space from the first fluid line and flows out of the internal space from the second fluid line; in the second state, fluid at the second temperature enters the internal space from the second fluid line and flows out of the internal space from the first fluid line.

[0011] In one or more embodiments of the compressor test bench, the first fluid line includes a line extending through the front load-bearing casing blades of the compressor to the drum.

[0012] According to another aspect of the present invention, a compressor testing method using a compressor test bench as described above includes: S1: measuring the current rotor tip clearance (C) and the corresponding current compressor performance parameters (P) of the compressor; S2: switching the test bench to a first state or a second state, adjusting the current rotor clearance to another rotor tip clearance, and measuring the compressor performance parameters corresponding to the other rotor tip clearance; S3: repeating S1 and S2 to measure a set of compressor performance parameters (P0, P1, P2, ..., Pn) corresponding to a set of rotor tip clearances (C0, C1, C2, ..., Cn), and obtaining the target rotor tip clearance of the compressor based on the compressor performance parameters.

[0013] According to another aspect of the present invention, a compressor testing method using a compressor test bench as described above includes: A: setting a lower limit value for the compressor rotor tip clearance test and a lower limit value for the compressor performance parameters test; B: measuring the current compressor rotor tip clearance (C) and the corresponding current compressor performance parameters (P); C: when the compressor rotor tip clearance is equal to or less than the corresponding lower limit value, switching the test bench to a first state; when the compressor performance parameters are equal to or less than the corresponding lower limit value, switching the test bench to a second state.

[0014] In one or more embodiments of the compressor testing method, in the first state, a portion of the cryogenic airflow from the inlet stage of the compressor's main duct also flows from the compressor's front disc cavity bleed line into the internal space defined by the drum.

[0015] In one or more embodiments of the compressor testing method, the fluid transmission control system is provided with control valves for controlling the first fluid pipeline and the second fluid pipeline, while the front disc cavity bleed air pipeline has no corresponding control valve.

[0016] According to another aspect of the present invention, a compressor includes: a plurality of stages; a drum fixedly connected to a disc of the plurality of stages, the drum defining an internal space; a first fluid line and a second fluid line, the first fluid line being axially positioned before a first stage of the plurality of stages, and the second fluid line being axially positioned after the last stage of the plurality of stages; the compressor having a first state and a second state: in the first state, a fluid of a first temperature enters the internal space defined by the drum from one of the first fluid line and the second fluid line, and exits the internal space from the other of the first fluid line and the second fluid line, to cool the disc; in the second state, a fluid of a second temperature enters the internal space defined by the drum from one of the first fluid line and the second fluid line, and exits the internal space from the other of the first fluid line and the second fluid line, to heat the disc.

[0017] In one or more embodiments of the compressor, in the first state, fluid at the first temperature enters the internal space from the first fluid line and exits the internal space from the second fluid line; in the second state, fluid at the second temperature enters the internal space from the second fluid line and exits the internal space from the first fluid line.

[0018] In one or more embodiments of the compressor, the first fluid line includes a line extending through the front bearing casing blades of the compressor to the drum. In the first state, a portion of the low-temperature airflow in the inlet stage of the main flow channel of the compressor also flows in from the front disc cavity bleed line of the compressor. The first fluid line and the second fluid line are respectively provided with control valves, while the front disc cavity bleed line has no corresponding control valve.

[0019] According to another aspect of the present invention, a gas turbine engine includes a compressor as described above, and a control system that controls the compressor to switch to either the first state or the second state.

[0020] The beneficial effects of this invention are as follows:

[0021] The structure, which delivers fluid to the drum via first and second fluid lines, enables active control of the compressor rotor tip clearance through heat exchange between the input fluid and the impeller. Compared to existing technologies that use casing heating to control rotor tip clearance, this design eliminates the need for a large, complex shell structure, making the test bench simpler, easier to assemble, and easier to debug. Furthermore, this structure can be applied to actual compressor structures by simply adding first and second fluid lines and a corresponding control system, achieving active control of rotor tip clearance without significant modifications to the existing compressor. Attached Figure Description

[0022] The above-described and other features, properties, and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features. It should be noted that these drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection actually claimed by the present invention.

[0023] in:

[0024] Figure 1 This is a schematic diagram of a compressor test bench;

[0025] Figure 2 This is a schematic diagram of the first state of the compressor test bench;

[0026] Figure 3 This is a schematic diagram of the second state of the compressor test bench;

[0027] Figure 4 This is a schematic diagram of the third state of the compressor test bench;

[0028] Figure 5 A schematic diagram of the steps of a compressor testing method according to one embodiment;

[0029] Figure 6 This is a schematic diagram of the compressor testing method steps according to another embodiment.

[0030] The attached figures are labeled as follows:

[0031] 1-Casing, 2-Rotor blade tip clearance, 3-Front bearing casing support plate blade;

[0032] 4-Stator blades, 5-Rotor blades, 6-Disc, 456-Multiple stages, 45601-First stage, 45602-Last stage;

[0033] 7-Flanges;

[0034] 8-Drum cylinder, 801-Internal space;

[0035] 9-First fluid line, 10-Second fluid line, 11-Front disc cavity bleed air line, 12-Compressor. Detailed Implementation

[0036] Reference will now be made in detail to various embodiments of the invention, examples of which are shown in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0037] In the following description, the terms "front," "rear," "inner," "outer," or other directional terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These are used solely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, this application uses specific terms to describe embodiments of the invention. For example, "one embodiment," "a particular embodiment," and / or "some embodiments" refer to a feature, structure, or characteristic associated with at least one embodiment of the invention. Therefore, it should be emphasized and noted that "one embodiment" or "a particular embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the invention can be appropriately combined.

[0038] refer to Figure 1As shown, the compressor 12 typically includes a casing 1, multiple stages 456, a drum 8, and a front disc bleed line 11. Each stage 456 includes stator blades 4, rotor blades 5, and a rotor disc 6. The stator blades 4 are fixedly connected to the casing 1 and are connected to the grates 7 located on the outer wall of the drum 8 to form a sealing structure. The rotor blades 5 are fixedly connected to the rotor disc 6, and the gap between the blade tips and the inner wall of the casing 1 forms the rotor blade tip gap 2. The front disc bleed line 11 is also fixedly connected to the drum 8 and can deliver fluid to the internal space 801 defined by the drum 8.

[0039] Continue to refer to Figure 1 As shown, in one embodiment, a compressor test bench includes a first fluid line 9 and a second fluid line 10, connected to a compressor 12 to be tested. The first fluid line 9 and the second fluid line are fixedly connected to the drum 8 of the compressor 12, used to deliver fluid to the internal space 801 defined by the drum 8, allowing heat exchange between the fluid and the impeller 6 of the compressor 12. The axial position of the first fluid line 9 is before the first stage 45601 of the compressor 12, and the axial position of the second fluid line 10 is after the last stage 45602 of the compressor 12. The compressor test bench also includes a fluid transfer control system for controlling the fluid input to the first fluid line 9 and the second fluid line 10. The test bench has a first state, a second state, and a third state.

[0040] (1) In the first state, the fluid transmission control system controls the fluid at a first temperature to enter the internal space 801 defined by the drum 8 from one of the first fluid pipe 9 and the second fluid pipe 10, and to flow out of the internal space 801 from the other of the first fluid pipe 9 and the second fluid pipe 10, so as to cool the wheel 6.

[0041] (2) In the second state, the fluid transmission control system controls the fluid at the second temperature to enter the internal space 801 defined by the drum 8 from one of the first fluid pipe 9 and the second fluid pipe 10, and to flow out of the internal space from the other of the first fluid pipe 9 and the second fluid pipe 10, so as to heat the wheel 6, wherein the second temperature is greater than the first temperature;

[0042] (3) In the third state, the first fluid line 9 is closed and the second fluid line 10 is open, as shown in the reference. Figure 4 As shown, the low-temperature airflow from the inlet stage of the compressor's main duct is introduced into the internal space 801 of the drum cavity of the compressor 12 from the air intake pipe 11, cooling the disc core, and the compressor itself achieves active control of the rotor blade tip clearance.

[0043] In existing technologies, test benches control rotor tip clearance by heating the casing. However, through long-term practice, the inventors discovered that, besides the casing, the thermal expansion of the impeller disc is also a significant factor affecting rotor tip clearance. Therefore, by altering the thermal environment of the disc's core region, the thermal expansion of the impeller disc can be changed, thereby achieving active control of rotor tip clearance. This also yields similar results to controlling casing expansion. The structure, which delivers fluid to the drum via first and second fluid lines, enables heat exchange between the input fluid and the impeller disc, thus actively controlling the compressor rotor tip clearance. Compared to existing test benches that use casing heating to control rotor tip clearance, this design eliminates the need for a large, complex shell structure, making the test bench simpler, easier to assemble, and easier to debug. Furthermore, this structure can be applied to actual compressor structures by simply adding first and second fluid lines and a corresponding control system, achieving active control of rotor tip clearance without significant modifications to the existing compressor.

[0044] refer to Figure 2 As shown, in one embodiment, a specific example of the first state of the compressor test bench can be that a fluid at a first temperature enters the internal space 801 from the first fluid line 9 and flows out of the internal space 801 from the second fluid line 10. (See reference...) Figure 3 As shown, a specific example of the second state of the compressor test bench can be that a fluid at a second temperature enters the internal space 801 from the second fluid pipe 10 and flows out of the internal space 801 from the first fluid pipe 9. The meaning of the first temperature and the second temperature does not imply limiting the temperature to a specific value; it can be an approximate temperature value or a temperature range. The inventors have found that the disc cooling / heating effect using the above embodiment is better. This may be because, during operation, the temperature of each stage of the compressor increases from front to back. If, during cooling, the fluid at the first temperature enters from the second pipe, it will first exchange heat with the disc of the last stage, and the fluid will be rapidly heated, making it difficult to achieve a good cooling effect on the discs of the preceding stages. Similarly, if, during heating, the fluid at the second temperature enters from the first pipe, it will first exchange heat with the disc of the first stage, and the fluid will be rapidly cooled, making it difficult to achieve a good heating effect on the discs of the subsequent stages. Furthermore, considering that the temperature of each stage of the compressor increases from front to back during operation, the initial rotor tip clearance of each stage of the compressor is generally larger than that of the later stage. Therefore, the scheme of this implementation will not affect the effect of controlling the rotor tip clearance.

[0045] refer to Figure 1As shown, in one embodiment, an example of the specific structure of the first fluid line 9 may be that the first fluid line 9 includes a line extending through the front support plate blade 3 of the compressor to the drum 8. Utilizing the front support plate blade 3 as the installation space for the first fluid line 9 not only makes the structure stable and compact but also reduces the impact on the compressor flow path.

[0046] In one implementation, reference Figure 5 As shown, the compressor test bench described above is used to conduct compressor tests. To obtain the optimal rotor tip clearance under a certain performance parameter of the compressor, i.e., the target rotor tip clearance, the test steps include:

[0047] S1: Measure the current rotor tip clearance (C) and the corresponding current compressor performance parameters (P) of the compressor;

[0048] S2: Switch the test bench to the first state or the second state, adjust the current rotor clearance to the other rotor tip clearance, and measure the compressor performance parameters corresponding to the other rotor tip clearance;

[0049] S3: Repeat S1 and S2 to measure a set of compressor performance parameters (P0, P1, P2, ..., Pn) corresponding to a set of rotor tip clearances (C0, C1, C2, ..., Cn). Based on the compressor performance parameters, obtain the target rotor tip clearance of the compressor.

[0050] For example, by measuring different compression ratios corresponding to different rotor tip clearances, if a high compression ratio is desired, the rotor tip clearance corresponding to the highest compression ratio is the target rotor tip clearance. It can be understood that the measured data can also be the rotor tip clearance corresponding to other performance parameters, not limited to the compression ratio example described above.

[0051] In another implementation, refer to Figure 6 As shown, the compressor test was conducted using the aforementioned compressor test bench. To ensure the test compressor consistently operated within the performance parameter range desired by the operator, the test procedures included:

[0052] A: Set the lower limit for the test of the compressor rotor tip clearance and the lower limit for the test of the compressor performance parameters;

[0053] B: Measure the current rotor tip clearance (C) and the corresponding current compressor performance parameters (P) of the compressor;

[0054] C: When the compressor rotor tip clearance is equal to or less than the corresponding test lower limit, the test bench is switched to the first state; when the compressor performance parameters are equal to or less than the corresponding test lower limit, the test bench is switched to the second state.

[0055] A1: Set the upper limit value for the test of the compressor rotor tip clearance, and the upper limit value for the test of the compressor performance parameters;

[0056] B1: Measure the current rotor tip clearance (C) and the corresponding current compressor performance parameters (P) of the compressor;

[0057] C1: When the rotor tip clearance of the compressor is equal to or greater than the corresponding upper limit value of the test, the test bench is switched to the second state; when the performance parameters of the compressor are equal to or greater than the corresponding upper limit value of the test, the test bench is switched to the first state.

[0058] refer to Figure 2 , Figure 3 As shown, in one embodiment, an example of the specific steps of the above-described test method further includes, in the first state, the low-temperature airflow in the inlet stage of the compressor's main flow channel also flows from the front disc cavity bleed pipe 11 of the compressor 12 into the internal space 801 of the drum-defined 8. The existing front disc cavity bleed pipe of the compressor is utilized, enhancing the flow of the cooling fluid within the internal space and improving the heat dissipation effect.

[0059] In other embodiments, examples of specific steps in the above-described experimental method include that the fluid transmission control system is equipped with control valves for the first fluid line 9 and the second fluid line 10, while the front disc cavity bleed air line 11 has no corresponding control valve. The inventors have found that the front disc cavity bleed air line 11 is close to the rotating component; adding a control valve thereto would have a certain impact on the compressor's operation and would also increase the difficulty of structural design. (Reference) Figure 3 As shown, since the front disc cavity air bleed pipe 11 has no control valve, a low-temperature airflow will be introduced when heating is required. However, the inventors discovered that since the first fluid pipe 9 located near the front disc cavity air bleed pipe 11 is opened at this time, most of the introduced low-temperature airflow is quickly discharged through the first fluid pipe 9, and the heat exchange with the disc is minimal.

[0060] refer to Figure 1 As shown, in one embodiment, a compressor includes multiple stages 456 and a drum 8, the drum 8 being fixedly connected to the discs 6 of the multiple stages 456, and the drum 8 defining an internal space 801. The compressor also includes the previously described first fluid line 9, second fluid line 10, and front disc cavity bleed line 11. The compressor further has the previously described first, second, and third states of the compressor test bench.

[0061] In one embodiment, an engine includes a compressor as described above and a control system, the control system controlling the compressor to switch between the first state, the second state, or the third state. In another embodiment, the control system includes an engine electronic controller, which may be a full authority digital engine controller.

[0062] Figure 4 The specific implementation shown is an example of the compressor test bench in the third state. At this time, the compressor test bench is in the conventional disk ventilation mode. In this working mode, part of the low-temperature airflow path of the inlet stage in the main channel can be introduced into the internal space 801, the valve of the first fluid pipeline 9 is closed, and the valve of the second fluid pipeline 10 is opened to realize the disk airflow path from front to back, change the disk thermal environment state, cool the disk, reduce the disk temperature, control the expansion degree of the disk 8, and thus control the overall deformation of the rotor system, thereby realizing the active control of the rotor blade tip clearance 2. In addition, in the conventional disk ventilation mode, reducing the disk temperature helps to reduce the probability of disk strength problems.

[0063] Figure 2 The specific implementation shown is an example of the compressor test bench in the first state. When the rotor blade tip clearance 2 is too small, the first fluid pipeline 9 can be opened on the basis of the conventional disk core ventilation in the third state above. More low temperature airflow is supplied by the test bench to further cool the disk cores of each stage, thereby reducing the thermal expansion of each stage of the disk and increasing the rotor blade tip clearance 2.

[0064] Figure 3 The specific implementation shown is an example of the compressor test bench in its first state. When the rotor tip clearance 2 is too large, a portion of the compressor exhaust (high-temperature gas) can be supplied to the second fluid line 10, with the first fluid line 9 serving as the exhaust port. This constructs an airflow from back to front, heating each stage's disk core and allowing the high-temperature, high-pressure airflow to circulate to the corresponding stage's disk 6, thereby enhancing the thermal expansion of each stage's disk 6. This increases the deformation of the disk 6, reducing the rotor tip clearance 2. Similarly, high-temperature gas can also be supplied to the first fluid line 9 primarily to heat the preceding stage's disk core, reducing the preceding stage rotor tip clearance 2.

[0065] In summary, the beneficial effects of the compressor test bench, test method, compressor, and engine described in the above embodiments include, but are not limited to, one or a combination of the following:

[0066] 1. The structure, which delivers fluid to the drum via a first and second fluid pipeline, enables active control of the compressor rotor tip clearance through heat exchange between the input fluid and the impeller. Compared to existing technologies that use casing heating to control rotor tip clearance, this design eliminates the need for a large, complex shell structure, making the test bench simpler, easier to assemble, and easier to debug. Furthermore, this structure can be applied to actual compressor structures by simply adding the first and second fluid pipelines and a corresponding control system, achieving active control of the rotor tip clearance without significant modifications to the existing compressor.

[0067] 2. Employing a front-to-back cooling flow path and a rear-to-front heating flow path provides better cooling / heating effects for the compressor discs. During operation, the temperature of each stage of the compressor increases progressively from front to back. If, during cooling, the fluid at the highest temperature enters through the second pipe, it will first exchange heat with the disc of the last stage, resulting in rapid heating and making it difficult to effectively cool the discs of earlier stages. Similarly, if, during heating, the fluid at the second highest temperature enters through the first pipe, it will first exchange heat with the disc of the first stage, resulting in rapid cooling and making it difficult to effectively heat the discs of later stages. Furthermore, considering that the temperature of each stage of the compressor increases progressively from front to back during operation, the initial rotor tip clearance of each stage is generally larger than that of the later stages. Therefore, this design will not affect the effectiveness of controlling the rotor tip clearance.

[0068] 3. The support plate blades are used as the installation space for the first fluid pipeline, which not only makes the structure stable and compact, but also reduces the impact on the compressor flow path.

[0069] 4. By utilizing the existing front disc cavity air intake pipe of the compressor, the flow of fluid used for cooling or heating in the internal space is enhanced, thereby improving the heat exchange effect.

[0070] 5. The conventional disc ventilation mode not only enables active control of rotor blade tip clearance, but also benefits the improvement of disc strength.

[0071] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A compressor test bench, characterized in that, include: The first fluid line and the second fluid line are connected to the compressor to be tested. The first fluid line and the second fluid line are fixedly connected to the drum of the compressor and are used to transport fluid to the internal space defined by the drum, so that the fluid exchanges heat with the compressor disc. The axial position of the first fluid line is before the first stage of the compressor, and the axial position of the second fluid line is after the last stage of the compressor. A fluid transfer control system is used to control the fluid input to the first fluid pipeline and the second fluid pipeline; The test bench has a first state and a second state: In the first state, the fluid transfer control system controls fluid at a first temperature to enter the internal space defined by the drum from the first fluid pipe and flow out of the internal space from the second fluid pipe to cool the disc; In the second state, the fluid transfer control system controls a fluid at a second temperature to enter the internal space defined by the drum from the second fluid conduit and flow out of the internal space from the first fluid conduit to heat the wheel, wherein the second temperature is greater than the first temperature.

2. The compressor test bench according to claim 1, characterized in that, The first fluid line includes a line extending through the front bearing casing blades of the compressor to the drum.

3. A compressor testing method, characterized in that, The compressor test bench as described in any one of claims 1-2 includes: S1: Measure the current rotor tip clearance (C) and the corresponding current compressor performance parameters (P) of the compressor; S2: Switch the test bench to the first state or the second state, adjust the current rotor tip clearance to another rotor tip clearance, and measure the compressor performance parameters corresponding to the other rotor tip clearance; S3: Repeat S1 and S2 to measure a set of compressor performance parameters (P0, P1, P2, ..., Pn) corresponding to a set of rotor tip clearances (C0, C1, C2, ..., Cn). Based on the compressor performance parameters, obtain the target rotor tip clearance of the compressor.

4. A compressor testing method, characterized in that, The compressor test bench as described in any one of claims 1-2 includes: A: Set the lower limit for the test of the compressor rotor tip clearance and the lower limit for the test of the compressor performance parameters; B: Measure the current rotor tip clearance (C) and the corresponding current compressor performance parameters (P) of the compressor; C: When the compressor rotor tip clearance is equal to or less than the corresponding test lower limit, the test bench is switched to the first state; when the compressor performance parameters are equal to or less than the corresponding test lower limit, the test bench is switched to the second state.

5. The compressor testing method according to claim 3 or 4, characterized in that, In the first state, the inlet stage portion of the low-temperature airflow in the main flow channel of the compressor also flows into the internal space defined by the drum from the air intake pipe of the front disc cavity of the compressor.

6. The compressor testing method according to claim 5, characterized in that, The fluid transmission control system is equipped with control valves for controlling the first fluid pipeline and the second fluid pipeline, but the front disc cavity bleed air pipeline has no corresponding control valve.

7. A compressor, characterized in that, include: Multiple levels; A drum cylinder, which is fixedly connected to the plurality of stages of discs, and the drum cylinder defines an internal space; A first fluid line and a second fluid line, wherein the axial position of the first fluid line is located before the first stage of the plurality of stages, and the axial position of the second fluid line is located after the last stage of the plurality of stages; The compressor has a first state and a second state: In the first state, fluid at a first temperature enters the internal space defined by the drum from the first fluid conduit and flows out of the internal space from the second fluid conduit to cool the disc; In the second state, fluid at a second temperature enters the internal space defined by the drum from the second fluid conduit and flows out of the internal space from the first fluid conduit to heat the disc.

8. The compressor according to claim 7, characterized in that, The first fluid pipeline includes a pipeline that extends through the front bearing casing blades of the compressor to the drum. In the first state, the inlet stage portion of the low-temperature airflow in the main flow channel of the compressor also flows in from the front disc cavity bleed pipeline of the compressor. The first fluid pipeline and the second fluid pipeline are respectively provided with control valves, while the front disc cavity bleed pipeline has no corresponding control valve.

9. A gas turbine engine, characterized in that, It includes a compressor as described in any one of claims 7-8, and a control system, wherein the control system controls the compressor to switch to the first state or the second state.

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