A compressor tester provided with an axial flow turbine

Abstract

The application provides a compressor tester provided with an axial flow turbine and relates to the technical field of compressor testing. The tester is provided with an axial flow turbine between the exhaust end of a compressor cylinder and the air inlet end of an exhaust cylinder. The axial flow turbine comprises turbine moving blades and turbine adjustable guide vanes. The turbine moving blades are arranged on the extension section of a rotor and are used for rotating and working under the action of high-pressure gas to reduce the exhaust temperature and generate reverse axial force. The turbine adjustable guide vanes are arranged on the extension section of the compressor cylinder and are used for adjusting the airflow direction and flow rate entering the turbine moving blades. The tester is also provided with a bleed air system and an automatic adjusting and control system. The application utilizes the working of the axial flow turbine under the action of high-pressure exhaust to reduce the exhaust temperature, reduce thermal stress, and generate reverse axial force opposite to the axial force direction of the rotor. The active and accurate control of the axial force is realized through the coordinated adjustment of the adjustable guide vanes and the bleed air system, the equipment structure is simplified, and the energy consumption and maintenance cost are reduced.

Description

Technical Field

[0001] This application relates to the field of compressor testing technology, and in particular to a compressor tester equipped with an axial turbine. Background Technology

[0002] In modern industry, heavy-duty gas turbines and axial compressors are key power equipment widely used in important fields such as power generation, aviation, and chemical industry. As one of the core components of these devices, the compressor's main function is to compress air or other working gases to a high-pressure state to meet the requirements of subsequent combustion or process flows. During the development of compressors, it is usually necessary to build a compressor test chamber to verify its aerodynamic performance, structural reliability, and other aspects.

[0003] In a compressor testing apparatus, the rotor experiences an axial force from the high-pressure end to the low-pressure end during operation. If this axial force is not effectively balanced, it will cause axial displacement of the rotor, affecting the normal operation of the bearings and potentially leading to equipment failure. To balance this axial force, traditional designs typically install a balance disc at the outlet of the testing apparatus. This disc utilizes the pressure difference between the high pressure of the exhaust gas and the atmospheric environment to generate a counter-axial force, thereby achieving axial force balance.

[0004] However, the above-mentioned scheme using a balance disc has the following problems in practical applications: First, because the gas discharged from the compressor is at a high temperature, to prevent the high-temperature gas from leaking from the exhaust cylinder seal and causing the bearing lubricating oil temperature to rise, it is usually necessary to introduce cold air into the exhaust cylinder seal for cooling. This results in one side of the exhaust cylinder seal being in direct contact with high-temperature gas, while the other side is in contact with low-temperature cold air. This direct contact between high and low temperatures causes high thermal stress at the sealing part. The generation of thermal stress can easily lead to damage to the seal, which in turn causes gas leakage and affects the safe operation of the equipment. Second, the compressor usually has multiple disc cavities with different temperatures inside. During operation, the temperature difference between the disc cavities will cause the rotor to experience sudden heating and cooling on a certain scale. This temperature change causes uneven thermal expansion and contraction of the rotor, resulting in a large temperature gradient. This temperature gradient not only exacerbates the concentration of thermal stress, but also reduces the strength and rigidity of the rotor in the long run, increasing the risk of equipment failure and shortening the service life of the equipment. In addition, to reduce the above-mentioned thermal stress, the existing technology usually needs to introduce a large amount of cold air into the exhaust cylinder seal. The introduction of this type of air conditioning not only increases the energy consumption of the equipment, but also complicates the air conditioning supply system, increasing the maintenance and operating costs of the equipment.

[0005] Existing patent CN109322848A discloses a rotor assembly for a compressor test piece. It balances axial forces and enhances rotor rigidity by using a balance disc coaxial with the compressor blade disk and a central tie rod to tighten the rotor assembly. Existing patent CN118423313A discloses an axial force balancing structure for compressor testing based on self-bleeding air. This structure guides the main flow air into the balance chamber through bleed holes and adaptively adjusts the axial force using the compressor outlet pressure to reduce the risk of thrust bearing overload. While these solutions achieve axial force balance to some extent, they still suffer from problems such as complex structure, insufficient thermal stress control, or limited adjustment capabilities.

[0006] In summary, how to reduce the temperature difference in the compressor outlet area, mitigate the impact of thermal stress, and improve the operational reliability of the test equipment while effectively balancing the axial force has become a pressing technical problem to be solved in this field. Summary of the Invention

[0007] Based on the current state of technology, this application proposes a compressor test apparatus equipped with an axial flow turbine to address issues such as excessive thermal stress in the exhaust cylinder, insufficient axial force balance adjustment capability, and complex equipment structure. By integrating an axial flow turbine at the compressor outlet, the high-pressure exhaust gas is used to reduce exhaust temperature and thermal stress, and the reverse axial force generated by the turbine is used to balance the compressor's axial force. Simultaneously, adjustable guide vanes and an induced draft system enable active and precise adjustment of the axial force. This simplifies the equipment structure, reduces energy consumption, and significantly improves the operational stability and reliability of the test apparatus.

[0008] To achieve the above objectives, a compressor test apparatus equipped with an axial flow turbine is provided, with the following specific technical solution: A compressor test apparatus equipped with an axial flow turbine, comprising: The compressor cylinder has an internal compressor flow channel; The rotor is rotatably supported axially inside the compressor cylinder; The stationary vane is disposed on the inner wall of the compressor cylinder; The moving blades are mounted on the rotor and together with the stationary blades constitute the flow passage of the compressor; An exhaust cylinder is connected to the exhaust end of the compressor cylinder and has an exhaust chamber inside. An axial turbine is disposed between the compressor cylinder and the exhaust cylinder; it is used to reduce the exhaust temperature and generate a reverse axial force opposite to the axial force on the rotor.

[0009] Furthermore, the axial turbine includes turbine blades and turbine adjustable guide vanes, with the turbine adjustable guide vanes disposed on the intake side of the turbine blades.

[0010] Furthermore, the rotor extends toward the exhaust cylinder to form an extension section, and the turbine blades are disposed on the extension section of the rotor and are evenly arranged circumferentially.

[0011] Furthermore, the compressor cylinder extends towards the exhaust cylinder to form an extension section, and the turbine adjustable guide vane is disposed on the extension section of the compressor cylinder and arranged circumferentially along the inner wall of the compressor cylinder.

[0012] Furthermore, the turbine adjustable guide vane includes guide vane blades, guide vane shaft, and adjustment mechanism. The guide vane blades are rotatably mounted on the inner wall of the compressor cylinder via the guide vane shaft. The adjustment mechanism is used to drive the guide vane shaft to rotate, thereby causing the guide vane blades to change their installation angle.

[0013] Furthermore, it also includes an air bleed system located between the compressor cylinder and the axial turbine, the air bleed system being disposed at the exhaust end of the compressor cylinder.

[0014] Furthermore, the bleed air system includes a bleed air groove penetrating the exhaust end wall of the compressor cylinder, a bleed air chamber communicating with the bleed air groove, a bleed air pipe connected to the bleed air chamber, and a bleed air valve installed on the bleed air pipe.

[0015] Furthermore, the air intake groove is an annular groove structure arranged circumferentially along the exhaust end wall of the compressor cylinder; the air intake chamber is a protruding chamber arranged circumferentially along the outer wall of the exhaust end of the compressor cylinder.

[0016] Furthermore, it also includes a balance disc, wherein the rotor has a reduced diameter at a shaft section located inside the exhaust cylinder, and the balance disc is mounted on this shaft section.

[0017] Furthermore, it also includes a cooling air supply system, wherein the inner wall of the exhaust cylinder extends radially inward on both sides of the balance disc to form cooling walls; wherein a cooling channel is provided inside the cooling wall located on the axial rear side.

[0018] Furthermore, the axial flow turbine is configured as a multi-stage turbine, with each stage of the axial flow turbine arranged sequentially along the axial direction.

[0019] Furthermore, it also includes an automatic adjustment and control system, which includes: The sensor unit is used to monitor the operating status parameters of the compressor test chamber in real time. The controller receives the data collected by the sensor unit and outputs control commands according to a preset control strategy. The execution unit adjusts the working state of the compressor tester according to the control command.

[0020] Furthermore, the sensor unit includes an axial force sensor disposed at the rotor bearing, a temperature sensor disposed at the exhaust port of the exhaust cylinder, and a stress sensor disposed on the wall of the exhaust cylinder.

[0021] By applying the above-described technical solution of this application, at least the following technical effects are achieved: 1. This application utilizes an axial turbine installed at the outlet of the compressor tester. By using high-pressure exhaust to drive the turbine to perform work, the total gas temperature is significantly reduced, thereby reducing the temperature difference on the exhaust cylinder wall and effectively reducing thermal stress. When the exhaust temperature drops to a level that does not affect the normal operation of the bearing lubricating oil, the cooling gas supply system at the exhaust cylinder seal can be eliminated or simplified, further reducing the temperature difference and thermal stress, while also simplifying the equipment structure.

[0022] 2. This application utilizes the characteristic that the reverse axial force generated during the operation of an axial turbine is opposite in direction to the axial force on the compressor rotor, thus achieving self-balancing of the axial force. By setting adjustable turbine guide vanes and an induced draft system, the direction and flow rate of the airflow entering the turbine can be precisely adjusted according to different operating conditions, thereby changing the turbine's working efficiency and the magnitude of the generated reverse axial force, achieving active and precise adjustment of the axial force, and ensuring the operational stability of the equipment under varying operating conditions.

[0023] 3. This application utilizes an axial-flow turbine to perform work on the exhaust gas from the compressor, which can offset some of the compressor's power consumption, thereby reducing the power requirement of the test bench motor and improving overall operating efficiency. Simultaneously, eliminating or simplifying the cooling air supply system further reduces equipment energy consumption, resulting in significant economic benefits.

[0024] 4. This application integrates the axial turbine and rotor into a single unit through an integrated design, reducing the number of assembly parts and lowering assembly difficulty and maintenance costs. When the reverse axial force provided by the axial turbine is sufficiently large, the traditional balance disc design can be eliminated, shortening the axial length and reducing equipment weight. Furthermore, the simplification of the exhaust cylinder cooling air supply system further optimizes the equipment structure and improves overall economic efficiency.

[0025] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0026] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments and descriptions of this application are used to explain this application and do not constitute an undue limitation of this application. In the drawings: Figure 1 A structural schematic diagram of a compressor test apparatus equipped with an axial flow turbine, as proposed in this application, is shown; Figure 2A partial schematic diagram of a compressor test apparatus equipped with an axial flow turbine as proposed in this application is shown; Figure 3 A structural schematic diagram of a compressor test apparatus equipped with an axial flow turbine, as proposed in this application, is shown.

[0027] Figure label: 10-Compressor cylinder, 20-Rotor, 30-Stationary vane, 40-Moving vane, 50-Exhaust cylinder, 60-Axial turbine, 70-Turbine moving vane, 80-Turbine adjustable guide vane, 81-Guide vane blade, 82-Guide vane shaft, 90-Intake system, 91-Intake groove, 92-Intake chamber, 93-Intake pipe, 94-Intake valve, 100-Balance disc, 110-Cooling system, 111-Cooling wall. Detailed Implementation

[0028] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0029] The present application will be further described in detail below with reference to specific embodiments, which should not be construed as limiting the scope of protection claimed in the present application.

[0030] This application aims to provide a compressor test apparatus equipped with an axial flow turbine to solve the problems of excessive thermal stress due to temperature difference, complex cooling system, and insufficient axial force adjustment capability caused by the balance disc structure in the prior art. By integrating an axial flow turbine at the compressor outlet end, and cooperating with adjustable turbine guide vanes and an induced draft system, this application can achieve force balance by utilizing the reverse axial force generated by the turbine while reducing the exhaust temperature. This eliminates or simplifies the traditional balance disc and cooling seal structure, significantly improving the operational reliability and economy of the equipment.

[0031] See Figure 1 and Figure 2As shown, this application proposes a compressor test apparatus equipped with an axial flow turbine, comprising: a compressor cylinder 10, a rotor 20, stationary vanes 30, moving vanes 40, an exhaust cylinder 50, and an axial flow turbine 60. The compressor cylinder 10 forms the outer shell of the compressor test apparatus, and its interior forms a compressor flow channel. The rotor 20 is rotatably supported axially within the compressor cylinder 10. Multiple stages of moving vanes 40 are alternately arranged axially on the rotor 20. Multiple stages of stationary vanes 30 are correspondingly arranged on the inner wall of the compressor cylinder 10. The moving vanes 40 and the stationary vanes 30 together constitute the flow passage of the compressor, used to progressively compress the gas entering through the inlet. The exhaust end of the compressor cylinder 10 is connected to an exhaust cylinder 50, which forms an exhaust chamber. The compressed gas is discharged through the exhaust port. The compressor cylinder 10 and the rotor 20 extend axially toward the exhaust cylinder 50 to form extension sections, and the axial turbine 60 is disposed in the extension sections. The axial turbine 60 is used to rotate and do work under the action of the high-pressure gas discharged from the compressor, thereby reducing the exhaust temperature and generating a reverse axial force opposite to the axial force on the rotor 20, so as to balance the axial force generated during the operation of the compressor.

[0032] The compressor test apparatus with an axial turbine proposed in this application also includes a balance disc 100 and a cold air supply system 110, which are common in conventional structures. Specifically, the rotor 20 has a reduced diameter at the shaft section located inside the exhaust cylinder 50. The balance disc 100 is installed at this shaft section and rotates with the rotor 20. Sealing teeth are provided between the top of the balance disc 100 and the inner wall of the exhaust cylinder 50, with a gap reserved. The inner wall of the exhaust cylinder 50 extends radially inward on both sides of the balance disc 100 to form cooling walls 111. Sealing teeth are provided between the ends of the cooling walls 111 and the rotor 20, with a gap reserved. A cold air channel is provided inside the cooling wall located behind the balance disc 100, which is used to introduce cold air. In addition, a gap is reserved between the inner wall of the exhaust cylinder 50 and the shoulder of the rotor 20, through which part of the exhaust gas after being powered by the axial turbine 60 can flow out. While retaining the traditional balance disc and air cooling functions, the exhaust temperature has been significantly reduced due to the cooling effect of the axial turbine 60. Therefore, the amount of air required by the air supply system 110 can be greatly reduced or eliminated, and the heat load on the balance disc 100 is also reduced accordingly. Thus, while ensuring axial force balance and sealing reliability, the operating efficiency and service life of the equipment are further improved.

[0033] In one specific embodiment of the axial flow turbine 60, the axial flow turbine 60 includes turbine blades 70 and turbine adjustable guide vanes 80. The turbine adjustable guide vanes 80 are located on the inlet side of the turbine blades 70 and are used to adjust the direction and flow rate of the airflow entering the turbine blades 70. The turbine blades 70 are used to rotate and perform work under the action of high-pressure gas. The axial flow turbine 60 can be configured as a single-stage or multi-stage turbine. When configured as a multi-stage turbine, each stage of the axial flow turbine 60 is arranged sequentially along the axial direction to improve work efficiency.

[0034] Specifically, the turbine blades 70 are disposed on the extension of the rotor 20 and are evenly arranged circumferentially. In a preferred embodiment, the turbine blades 70 are fixedly connected to the extension of the rotor 20 via tenons and slots. During compressor operation, the high-pressure gas discharged from the compressor exhaust port flows through the turbine blades 70, driving them to rotate and perform work. This reduces the overall gas temperature, thereby lowering the heat load inside the exhaust cylinder 50 and its sealing components. Simultaneously, the turbine blades 70 generate a reverse axial force during rotation, opposite to the axial force of the compressor rotor 20. This reverse axial force acts on the rotor 20, partially or completely offsetting the axial force generated during compressor operation. Furthermore, the work done by the rotating turbine blades 70 can offset some of the compressor's power consumption, reducing the overall power requirement of the test apparatus.

[0035] For details, please refer to Figure 2 As shown, the adjustable turbine guide vane 80 is disposed on the extension section of the compressor cylinder 10 and arranged circumferentially along the inner wall of the compressor cylinder 10. The adjustable turbine guide vane 80 includes guide vane blades 81, guide vane shafts 82, and an adjustment mechanism. Each guide vane blade 81 is rotatably mounted on the wall of the compressor cylinder 10 via the guide vane shafts 82. The adjustment mechanism is used to drive each guide vane shaft 82 to rotate according to control commands, thereby causing each guide vane blade 81 to synchronously change its installation angle. The adjustment mechanism can be an adjustable stator vane adjustment mechanism in the art. By adjusting the angle of the guide vane blades 81, the direction and flow rate of the airflow entering the turbine moving blades 70 can be changed, thereby changing the working efficiency of the axial turbine 60 and the magnitude of the generated reverse axial force, realizing flexible adjustment of the axial force.

[0036] Through the coordinated operation of the turbine adjustable guide vane 80 and the turbine moving blade 70, the direction and flow rate of the airflow entering the turbine moving blade 70 can be adjusted in real time according to different operating conditions of the compressor tester, thereby changing the working efficiency of the axial turbine 60 and the magnitude of the reverse axial force generated, and realizing the active and precise adjustment of the axial force of the compressor rotor 20.

[0037] See Figure 2As shown, the compressor test apparatus is also equipped with an air bleed system 90 for further regulating the airflow entering the axial turbine 60. The air bleed system 90 includes an air bleed groove 91, an air bleed chamber 92, an air bleed pipe 93, and an air bleed valve 94. The air bleed groove 91 is formed on and penetrates the exhaust end wall of the compressor cylinder 10, and is arranged in a circumferential annular groove structure. The air bleed chamber 92 is an outwardly protruding annular cavity arranged circumferentially along the exhaust end wall of the compressor cylinder 10, and is connected to the air bleed groove 91. One end of the air bleed pipe 93 is connected to the air bleed chamber 92, and the other end is connected to the atmosphere or a low-pressure area. The air bleed valve 94 is installed on the air bleed pipe 93 to control the on / off state and opening degree of the air bleed pipe 93. During operation, by adjusting the opening of the bleed air valve 94, the flow rate of air diverted from the compressor exhaust can be controlled, thereby changing the effective air flow rate entering the axial turbine 60, and thus adjusting the working efficiency of the axial turbine 60 and the magnitude of the generated reverse axial force. The opening of the bleed air valve 94 is automatically adjusted according to the operating conditions of the compressor tester. When it is necessary to reduce the air flow rate entering the axial turbine 60, the opening of the bleed air valve 94 is increased, allowing part of the exhaust to be diverted to the atmosphere or low-pressure area through the bleed air groove 91, bleed air chamber 92, and bleed air pipe 93; when it is necessary to increase the air flow rate entering the axial turbine 60, the opening of the bleed air valve 94 is decreased. Through the coordinated control of the bleed air system 90 and the turbine adjustable guide vane 80, precise adjustment of the axial force can be achieved. The turbine adjustable guide vane 80 and the bleed air system 90 work together to achieve precise and rapid adjustment of the axial force to adapt to different operating conditions.

[0038] In this application, the reverse axial force generated by the axial turbine 60 is opposite in direction to the axial force on the compressor rotor 20, and the two cancel each other out. By rationally designing the number of stages, blade angle, and flow area of ​​the axial turbine 60, the reverse axial force and the compressor axial force can be made substantially equal under rated operating conditions, thereby achieving self-balancing of the axial force. Based on this, this application can reduce reliance on traditional balancing structures. As a preferred embodiment, see [reference needed]. Figure 3 As shown, when the reverse axial force generated by the axial turbine 60 is sufficient to balance the axial force of the compressor rotor 20, the balance disc 100 installed at the end of the exhaust cylinder 50 can be eliminated. When changes in operating conditions cause fluctuations in axial force, the balance of axial force can still be maintained by adjusting the turbine adjustable guide vanes 80 and the bleed air system 90. At the same time, since the axial turbine 60 reduces the exhaust temperature by doing work, the heat load at the seal of the exhaust cylinder 50 is significantly reduced, and the cold air supply system 110 introduced for cooling the seal can be eliminated, thereby simplifying the equipment structure and reducing energy consumption and operating costs.

[0039] To achieve intelligent control of the axial turbine 60 and the induced draft system 90, this application also includes an automatic adjustment and control system. This system comprises a sensor unit, a controller, and an execution unit. The sensor unit includes an axial force sensor located at the rotor 20 bearing, a temperature sensor located at the exhaust port, and a stress sensor located on the wall of the exhaust cylinder 50, used to monitor the axial force, exhaust temperature, and thermal stress distribution of the test equipment in real time. The controller receives data collected by the sensor unit and calculates the target adjustment amount according to a preset control strategy or algorithm, outputting control commands to the execution unit. The execution unit includes an actuator driving the adjustable guide vane 80 of the turbine and a valve drive device controlling the induced draft valve 94, used to adjust the guide vane angle and valve opening in real time according to the control commands, thereby changing the working efficiency and the magnitude of the reverse axial force of the axial turbine 60, ensuring that the axial force of the rotor 20 is always maintained within a preset safety threshold range. Furthermore, the controller also has fault diagnosis and early warning functions. When the monitored parameters exceed the normal range, the system automatically issues an early warning signal and can execute protective actions according to preset logic to improve the operational reliability and safety of the equipment.

[0040] This application proposes a compressor test apparatus with an axial flow turbine, which incorporates several structural design optimizations. The rotor 20 and turbine blades 70 are integrated, eliminating the connecting parts between them, reducing assembly steps and the number of components, lowering assembly difficulty and maintenance costs, while simultaneously improving the overall rigidity of the rotating components and the rotor's dynamic characteristics, thus enhancing the test apparatus's operational stability and reliability. The introduction of the axial flow turbine 60 eliminates the traditional balance disc and simplifies the cooling air supply system, thereby shortening the axial length, reducing overall weight, and facilitating transportation and installation. The connection between the compressor cylinder 10 and the exhaust cylinder 50 is also simplified to a direct flange connection, eliminating the need for a complex double-layer structure and further reducing manufacturing costs. Through these structural optimizations, this application effectively balances axial forces, reduces thermal stress in the exhaust cylinder, significantly simplifies the equipment structure, reduces energy consumption and operating and maintenance costs, and effectively solves the technical problems existing in the prior art.

[0041] By applying the above-described technical solution of this application, at least the following technical effects are achieved: 1. This application utilizes an axial turbine installed at the outlet of the compressor tester. By using high-pressure exhaust to drive the turbine to perform work, the total gas temperature is significantly reduced, thereby reducing the temperature difference on the exhaust cylinder wall and effectively reducing thermal stress. When the exhaust temperature drops to a level that does not affect the normal operation of the bearing lubricating oil, the cooling gas supply system at the exhaust cylinder seal can be eliminated or simplified, further reducing the temperature difference and thermal stress, while also simplifying the equipment structure.

[0042] 2. This application utilizes the characteristic that the reverse axial force generated during the operation of an axial turbine is opposite in direction to the axial force on the compressor rotor, thus achieving self-balancing of the axial force. By setting adjustable turbine guide vanes and an induced draft system, the direction and flow rate of the airflow entering the turbine can be precisely adjusted according to different operating conditions, thereby changing the turbine's working efficiency and the magnitude of the generated reverse axial force, achieving active and precise adjustment of the axial force, and ensuring the operational stability of the equipment under varying operating conditions.

[0043] 3. This application utilizes an axial-flow turbine to perform work on the exhaust gas from the compressor, which can offset some of the compressor's power consumption, thereby reducing the power requirement of the test bench motor and improving overall operating efficiency. Simultaneously, eliminating or simplifying the cooling air supply system further reduces equipment energy consumption, resulting in significant economic benefits.

[0044] 4. This application integrates the axial turbine and rotor into a single unit through an integrated design, reducing the number of assembly parts and lowering assembly difficulty and maintenance costs. When the reverse axial force provided by the axial turbine is sufficiently large, the traditional balance disc design can be eliminated, shortening the axial length and reducing equipment weight. Furthermore, the simplification of the exhaust cylinder cooling air supply system further optimizes the equipment structure and improves overall economic efficiency.

[0045] The above are merely several specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in this application, based on the technical solution and inventive concept of this application, should be included within the scope of protection of this application.

[0046] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0047] It should be noted that, in the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

Claims

1. A compressor tester provided with an axial flow turbine, characterized in that, include: Compressor cylinder (10), the compressor flow channel is formed inside it; The rotor (20) is rotatably supported in the compressor cylinder (10) along the axial direction; A stationary vane (30) is disposed on the inner wall of the compressor cylinder (10); The moving blade (40) is disposed on the rotor (20) and together with the stationary blade (30) constitutes the flow passage of the compressor; An exhaust cylinder (50) is connected to the exhaust end of the compressor cylinder (10) and has an exhaust chamber inside. An axial turbine (60) is disposed between the compressor cylinder (10) and the exhaust cylinder (50); it is used to reduce the exhaust temperature and generate a reverse axial force opposite to the axial force on the rotor (20).

2. The compressor test rig provided with an axial flow turbine according to claim 1, characterized in that, The axial turbine (60) includes turbine blades (70) and turbine adjustable guide vanes (80), the turbine adjustable guide vanes (80) being disposed on the intake side of the turbine blades (70).

3. The compressor test apparatus equipped with an axial flow turbine according to claim 2, characterized in that, The rotor (20) extends toward the exhaust cylinder (50) to form an extension section, and the turbine blades (70) are disposed on the extension section of the rotor (20) and are evenly arranged circumferentially.

4. The compressor test facility provided with an axial flow turbine according to claim 2, characterized in that, The compressor cylinder (10) extends to the side of the exhaust cylinder (50) to form an extension section, and the turbine adjustable guide vane (80) is disposed on the extension section of the compressor cylinder (10) and arranged circumferentially along the inner wall of the compressor cylinder (10).

5. The compressor test rig provided with an axial flow turbine according to claim 4, characterized in that, The turbine adjustable guide vane (80) includes a guide vane blade (81), a guide vane shaft (82), and an adjustment mechanism. The guide vane blade (81) is rotatably mounted on the inner wall of the compressor cylinder (10) via the guide vane shaft (82). The adjustment mechanism is used to drive the guide vane shaft (82) to rotate, thereby causing the guide vane blade (81) to change its installation angle.

6. The compressor test apparatus equipped with an axial flow turbine according to claim 1, characterized in that, It also includes an air intake system (90) located between the compressor cylinder (10) and the axial turbine (60), the air intake system (90) being disposed at the exhaust end of the compressor cylinder (10).

7. The compressor test apparatus equipped with an axial flow turbine according to claim 6, characterized in that, The bleed air system (90) includes a bleed air groove (91) that penetrates the exhaust end wall of the compressor cylinder (10), a bleed air chamber (92) that communicates with the bleed air groove (91), a bleed air pipe (93) that connects to the bleed air chamber (92), and a bleed air valve (94) installed on the bleed air pipe (93).

8. The compressor test rig provided with an axial flow turbine according to claim 7, characterized in that The air intake groove (91) is an annular groove structure arranged circumferentially along the exhaust end wall of the compressor cylinder (10); the air intake chamber (92) is a protruding chamber arranged circumferentially along the outer wall of the exhaust end of the compressor cylinder (10).

9. The compressor test facility provided with an axial flow turbine according to claim 1, characterized in that, It also includes a balance disc (100); the rotor (20) has a reduced diameter at a shaft section located inside the exhaust cylinder (50), on which the balance disc (100) is mounted.

10. The compressor test rig provided with an axial flow turbine according to claim 9, characterized in that, It also includes a cold air supply system (110); the inner wall of the exhaust cylinder (50) extends radially inward on both sides of the balance disc (100) to form a cooling wall (111); wherein a cooling channel is provided inside the cooling wall (111) located on the axial rear side.

11. The compressor test rig provided with an axial flow turbine according to any one of claims 1 to 10, characterized in that, The axial flow turbine (60) is configured as a multi-stage turbine, with each stage of the axial flow turbine (60) arranged sequentially along the axial direction.

12. The compressor test facility provided with an axial flow turbine according to claim 1, characterized in that, It also includes an automatic adjustment and control system, which includes: The sensor unit is used to monitor the operating status parameters of the compressor test chamber in real time. The controller receives the data collected by the sensor unit and outputs control commands according to a preset control strategy. The execution unit adjusts the working state of the compressor tester according to the control command.

13. The compressor test rig provided with an axial flow turbine according to claim 12, characterized in that The sensor unit includes an axial force sensor disposed at the bearing of the rotor (20), a temperature sensor disposed at the exhaust port of the exhaust cylinder (50), and a stress sensor disposed on the wall of the exhaust cylinder (50).

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