Cold air system for turbine performance tester and control method thereof

Abstract

The application provides a cold air system for a turbine performance tester and a control method thereof. The cold air system comprises a temperature control module, a flow pressure control module and a connection panel. The temperature control module is used to provide cold air with different temperatures and comprises a plurality of gas supply pipelines. One end of each gas supply pipeline is connected to a gas source, and the other end is connected to the connection panel. The flow pressure control module is used to adjust the flow and pressure of the outlet gas and to distribute the cold air, and comprises a plurality of gas supply pipelines. One end of each gas supply pipeline is connected to the connection panel, and the other end is connected to a turbine test piece. The connection panel has a plurality of interfaces. The interfaces of the connection panel on the temperature control module side and the interfaces of the connection panel on the flow pressure control module side are connected by hoses. The application improves the modularization degree and expandability of the cold air system. The control method combines the intelligent following control of the cold air and the main gas through feedforward and feedback, significantly shortens the working condition adjustment time, and makes the impact change of the working condition on the test piece more gentle.

Description

Technical Field

[0001] This invention relates to the field of turbine engine testing technology, and more specifically to a cooling system and its control method for a turbine performance tester. Background Technology

[0002] Turbine performance testing primarily involves introducing gas at a specific temperature and pressure, along with a certain flow rate and temperature ratio of cool air, into the test component to assess its efficiency and flow characteristics. The turbine test apparatus mainly provides high-temperature airflow to the main flow channel through the main gas system, and provides cool air to the guide vanes, moving blades, and various cavities through the cool air system for cooling, axial force balancing, and sealing. (Note: Cool air refers to air with a temperature lower than the surface temperature of the turbine blades. Because the main flow channel temperature for turbine component testing is relatively high, the cool air introduced into the blades generally needs to maintain a certain temperature ratio with the main flow channel temperature. The cool air used for balancing and sealing is generally at room temperature. The cool air system is the system that provides cooling air to the test blades.) As turbine component development enters a more advanced stage, higher demands are placed on the precision control of the cool air during testing.

[0003] The existing design schemes for cooling systems used in turbine performance testing equipment have the following problems:

[0004] (1) Insufficient scalability and flexibility: Changes to the flow path topology rely on hard connection modifications such as welding, which are time-consuming and result in long test preparation cycles and low equipment utilization. The system structure is fixed, making it difficult to quickly adapt to new flow paths, integrate special monitoring units (such as particle and humidity sensors), or meet complex test requirements such as independent control of multiple cavities and active gap control.

[0005] (2) Single control dimension: It mainly focuses on the control of cold air supply to the test piece, and lacks effective means to control the cold air exhaust of the test piece. The internal structure of the test piece is complex, and the cavity pressure can not be fully controlled within the range of test requirements by relying solely on the supply pressure, which limits the simulation capability of certain test conditions.

[0006] (3) Insufficient automation: The cooling system usually relies on manual control. For high-pressure turbine tests, the cooling air flow rate requirement for the blades is high, with the cooling air flow rate entering the first-stage guide vane approaching 20% ​​and the cooling air flow rate entering the first-stage moving blade approaching 10%. Usually, during the test, adjusting the cooling flow after the main parameters are adjusted will have a significant impact on the state of the test piece, such as the inlet pressure and axial force. Usually, the main flow needs to be adjusted again to achieve the inlet pressure required by the test piece. Due to the flow rate requirement, the cooling air path needs to be adjusted again, and this process needs to be repeated multiple times to achieve the required operating condition. The control between the main air and the cooling air is not synchronized and lacks follow-up, resulting in a long adjustment time between operating points. Moreover, when abnormal situations occur, the cooling system does not have enough time to make adjustments. For example, the axial force control and the sealing air of the front and rear bearings are difficult to adjust in time, and are prone to exceeding limits. It is also difficult to achieve dynamic balance of multiple airflows.

[0007] (4) The cooling system and the main air system are controlled in isolation and cannot be linked. After the main air parameters are changed, the cooling system needs to be manually adjusted one by one, which is cumbersome and has a serious lag, resulting in an extremely long adjustment cycle at the operating point. When an abnormality occurs during the test, the system lacks a rapid automatic protection mechanism, relies on the operator's experience, and has a high safety risk.

[0008] In view of this, the inventors of this application have designed a cooling system and control method for a turbine performance tester in order to overcome the above-mentioned technical problems. Summary of the Invention

[0009] The technical problem to be solved by the present invention is to overcome the shortcomings of the existing design of the cooling system for turbine performance testers, and to provide a cooling system for turbine performance testers and its control method.

[0010] The present invention solves the above-mentioned technical problems through the following technical solution:

[0011] This invention provides a cooling system for a turbine performance tester, characterized in that the cooling system includes a temperature control module, a flow and pressure control module, and a connection panel; the temperature control module is used to provide cooling air at different temperatures, and includes multiple air supply pipelines; one end of each air supply pipeline is connected to an air source, and the other end is connected to the connection panel; the flow and pressure control module is used to adjust the outlet flow rate and pressure and distribute the cooling air, and also includes multiple air supply pipelines; one end of each air supply pipeline is connected to the connection panel, and the other end is connected to the turbine test piece; the connection panel has multiple interfaces, and the interfaces on the temperature control module side and the flow and pressure control module side are connected via flexible hoses.

[0012] According to one or more embodiments of the present invention, the air conditioning system is electrically or communicatively connected to an air conditioning system co-controller.

[0013] According to one or more embodiments of the present invention, the multiple gas supply lines of the temperature control module include a first gas supply line, and a normal temperature gas distribution tank is provided on the first gas supply line.

[0014] According to one or more embodiments of the present invention, the multiple gas supply lines of the temperature control module include a second gas supply line, on which a gas collection tank and a heater are sequentially arranged along the airflow direction.

[0015] According to one or more embodiments of the present invention, the multiple gas supply lines of the temperature control module include a third gas supply line, wherein a heater and a cooler are sequentially arranged along the airflow direction on the third gas supply line.

[0016] According to one or more embodiments of the present invention, each gas delivery pipeline of the flow and pressure control module is provided with a flow meter, a pressure sensor, a temperature sensor and a gas distributor in sequence along the gas flow direction.

[0017] According to one or more embodiments of the present invention, the flow and pressure control module is further provided with a test specimen cavity exhaust control pipeline, the inlet of which is connected to the turbine test specimen, and an air pump is provided on the test specimen cavity exhaust control pipeline.

[0018] According to one or more embodiments of the present invention, each gas supply pipeline of the temperature control module and each gas supply pipeline of the flow and pressure control module are provided with a gas supply regulating valve.

[0019] According to one or more embodiments of the present invention, the test specimen cavity exhaust control pipeline is provided with a test specimen cavity exhaust regulating valve.

[0020] According to one or more embodiments of the present invention, the cooling system co-controller is electrically or communicatively connected to the controller of the main gas system, and is electrically or communicatively connected to the gas supply regulating valve, the flow meter, the pressure sensor, and the temperature sensor. After receiving a signal from the main gas system controller indicating that the main gas system's operating condition is about to change from the current operating condition to the target operating condition, the cooling system co-controller adjusts the gas supply regulating valves on each gas supply pipeline to the estimated opening degree. Then, based on the signal feedback from the flow meter and / or the pressure sensor and / or the temperature sensor, it fine-tunes the control, so that the cooling system cooperates with the main gas system to enable the test specimen to reach the target operating condition.

[0021] According to one or more embodiments of the present invention, a cavity pressure sensor is provided in the cavity of the turbine test piece. The cooling system co-controller is electrically or communicatively connected to the cavity pressure sensor and the pressure sensor. The cooling system co-controller is electrically or communicatively connected to the gas supply regulating valve, the vacuum pump, and the test piece cavity exhaust regulating valve on the test piece cavity exhaust control pipeline. The cooling system co-controller compares the cavity pressure set value with the actual value. If pressure needs to be increased, the gas supply regulating valve is increased; if pressure needs to be decreased, the gas supply regulating valve is decreased. Alternatively, the vacuum pump is started and the test piece cavity exhaust regulating valve is adjusted.

[0022] The present invention also provides a control method for a cooling system for a turbine performance tester, characterized in that the control method is used to control the cooling system for a turbine performance tester as described above; the control method includes main gas-cooled gas following control, supply-exhaust coordinated chamber pressure control, and safety monitoring and interlocking control.

[0023] According to one or more embodiments of the present invention, the main gas-cooled gas following control includes: real-time monitoring of the main gas flow rate of the main gas system and the flow rate of the cooling gas system; calculating the target flow rate value of the cooling gas system based on the preset flow rate relationship between the main gas system and the cooling gas system, and adjusting the flow rate of the cooling gas system to the target flow rate value; and then fine-tuning the control based on sensor signal feedback, so that the cooling gas system cooperates with the main gas system to make the test piece reach the target operating condition.

[0024] According to one or more embodiments of the present invention, the gas supply-exhaust coordinated chamber pressure control includes: real-time monitoring of the actual pressure of the turbine test specimen chamber; when pressure needs to be increased, increasing the gas supply regulating valve; when pressure needs to be reduced, reducing the gas supply pressure to control the chamber pressure to decrease and stabilize near the target value; when reducing the gas supply pressure cannot guarantee that the chamber pressure is stabilized near the target value; starting the vacuum pump and adjusting the test specimen chamber exhaust regulating valve.

[0025] According to one or more embodiments of the present invention, the safety monitoring and interlocking control includes: real-time monitoring of the cooling gas supply pressure and calculation of the sealing pressure difference and axial force of the turbine test piece, and obtaining the blade tip clearance of the turbine test piece; maintaining the sealing pressure difference of the turbine test piece less than the limit value, maintaining the axial force of the turbine test piece less than the limit value, and maintaining the blade tip clearance of the turbine test piece within a set range; real-time monitoring of the cooling gas supply pressure and measurement of the target cavity pressure of the turbine test piece, and maintaining the cavity pressure of the turbine test piece within a limit range.

[0026] The positive and progressive effects of this invention are as follows:

[0027] The present invention provides a cooling system and control method for a turbine performance tester, which achieves the following:

[0028] First, improve the modularity and scalability of the air conditioning system through hardware design, so that it can flexibly adapt to the needs of various new and complex test projects.

[0029] Second, by using a cooling system control method that combines feedforward and feedback to intelligently follow the cooling and main air, the operating condition adjustment time is significantly shortened.

[0030] Third, by adding a test specimen cavity exhaust control loop and combining it with control logic, active control of the test specimen cavity pressure is achieved.

[0031] IV. An automated control system integrating initialization, collaborative control, and intelligent protection was constructed to improve the accuracy, efficiency, and safety of the experiment. Attached Figure Description

[0032] The above 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, wherein:

[0033] Figure 1 This is a schematic diagram of an embodiment of the cooling system for the turbine performance tester of the present invention.

[0034] Figure 2 This is a schematic diagram of the connection panel in one embodiment of the cooling system for the turbine performance tester of the present invention.

[0035] Figure 3 This is a schematic diagram of the air distribution tank in one embodiment of the cooling system for the turbine performance tester of the present invention.

[0036] Figure 4 This is a schematic diagram of the arrangement of the gas distribution tank in one embodiment of the cooling system for the turbine performance tester of the present invention.

[0037] Figure 5 This is a schematic diagram of the control logic of an embodiment of the cooling system control method for a turbine performance tester of the present invention.

[0038] Figure 6 This is a schematic diagram of the initialization configuration process of an embodiment of the cooling system control method for a turbine performance tester of the present invention.

[0039] Figure 7 This is a schematic diagram of the automatic control timing of an embodiment of the cooling system control method for a turbine performance tester of the present invention.

[0040] [Attached image labels]

[0041] 100. Temperature control module

[0042] 110. Ambient temperature gas separator

[0043] 120. Gas collection tank

[0044] 130. Refrigerator

[0045] 140. Heater

[0046] 200. Flow and pressure control module

[0047] 210. Flow meter

[0048] 220. Pressure sensor

[0049] 230. Temperature sensor

[0050] 240. Gas distributor

[0051] 300. Connection panel

[0052] 310. Hose

[0053] 320. Interface

[0054] 400. Gas pipeline

[0055] 410. First gas pipeline

[0056] 420. Second gas pipeline

[0057] 430. Third gas pipeline

[0058] 440. Gas supply regulating valve

[0059] 450. Switch valve

[0060] 460. Vent control valve

[0061] 500. Test specimen cavity exhaust control pipeline

[0062] 510. Air pump

[0063] 520. Test specimen cavity exhaust regulating valve

[0064] 600. Gas source

[0065] 700, Turbine Test Specimen Detailed Implementation

[0066] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0067] Reference will now be made in detail to preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts. Furthermore, although the terminology used herein is selected from commonly known and used terms, some terms mentioned in this specification may have been chosen by the applicant at his or her discretion, and their detailed meanings are explained in the relevant sections of the description herein. Moreover, the invention should be understood not only by the actual terminology used, but also by the meaning implied by each term. Also, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale.

[0068] See Figures 1-4 The present invention provides a cooling system for a turbine performance tester, the cooling system comprising a temperature control module 100, a flow and pressure control module 200, and a connection panel 300.

[0069] The temperature control module 100 is used to provide air at different temperatures. The temperature control module 100 includes multiple air supply lines 400. One end of the air supply line 400 is connected to the air source 600, and the other end of the air supply line 400 is connected to the connection panel 300.

[0070] The flow and pressure control module 200 is used to regulate the outlet flow and pressure and to distribute the cold air. The flow and pressure control module 200 includes multiple air supply lines 400. One end of the air supply line 400 is connected to the connection panel 300, and the other end of the air supply line 400 is connected to the turbine test piece 700.

[0071] The connection panel 300 has multiple interfaces 320. The interfaces 320 of the connection panel 300 on the side of the temperature control module 100 and the interfaces 320 of the connection panel 300 on the side of the flow and pressure control module 200 are connected by a hose 310.

[0072] The cooling system for a turbine performance tester of this invention features a connection panel 300 with multiple interfaces 320. Through the flexible selection and connection of these interfaces 320, the interfaces 320 of the temperature control module 100 and the flow and pressure control module 200 can be arbitrarily matched, enabling the reconfiguration of the cooling system. In other words, this invention is a reconfigurable cooling system. This achieves a modular design, allowing for rapid changes in flow path topology and function through the standardized interfaces 320 and flexible connections with hoses 310, adapting to different testing requirements for the cooling supply system.

[0073] Preferably, the interface 320 and hose 310 used to connect the connection panel 300 are metal hoses, and the flow path can be quickly connected and reconfigured through the connection panel 300 on the intake side, the connection panel 300 on the exhaust side, the standardized interface 320 and the metal hose.

[0074] Preferably, the cooling system of the turbine performance tester of the present invention uses the connecting panel 300 as a "breakpoint", so that when the end of the original ordinary cooling air supply pipeline is connected to the exhaust port of the target cavity, its role is no longer that of the air supply pipeline, but can continue to play the throttling role of the valve in the pipeline, allowing the exhaust airflow of the target cavity of the test piece to flow backward in the pipeline and be discharged from the flange port of the adapter panel, thus becoming an exhaust control pipeline.

[0075] In a preferred embodiment of the cooling system for the turbine performance tester of the present invention, the cooling system is electrically or communicatively connected to a cooling system co-controller.

[0076] The cooling system for the turbine performance tester of this invention is connected to the cooling system co-controller via electrical or communication connection. Through the configuration of various control logics of the cooling system co-controller, active functions such as main air-cooled air intelligent following control, supply-exhaust coordinated chamber pressure control, and full-process automation and intelligent protection of the cooling system can be achieved.

[0077] See Figure 1 As a preferred embodiment of the cooling system for the turbine performance tester of the present invention, the multiple gas supply lines 400 of the temperature control module 100 include a first gas supply line 410, on which a normal temperature gas distribution tank 110 is provided.

[0078] The first gas supply line 410 is typically used to provide cold air at room temperature.

[0079] See Figure 1 As a preferred embodiment of the cooling system for the turbine performance tester of the present invention, the multiple air supply lines 400 of the temperature control module 100 include a second air supply line 420, on which an air collection tank 120 and a heater 140 are sequentially arranged along the airflow direction.

[0080] The second gas line 420 is typically used to provide air at a higher temperature than normal.

[0081] See Figure 1 As a preferred embodiment of the cooling system for the turbine performance tester of the present invention, the multiple air supply lines 400 of the temperature control module 100 include a third air supply line 430, on which a heater 140 and a cooler 130 are arranged sequentially along the airflow direction.

[0082] The third gas supply line 430, through the coordinated action of the heater 140 and the cooler 130, can provide cold air at different temperatures. The cooler 130 and heater 140 of the third gas supply line can be used independently. When the heater 140 overshoots, in addition to the heater 140's own PID regulation, the cooler 130 can be activated to provide the heater 140 with a lower-temperature airflow, assisting the heater 140 in temperature control.

[0083] The temperature control module 100 can realize multi-functional temperature control. The three gas supply lines 400 integrate a normal temperature gas tank, an electric heater, and a cooler 130 to provide cold air with a wide temperature range to meet different test requirements.

[0084] See Figure 1 As a preferred embodiment of the cooling system for the turbine performance tester of the present invention, each gas pipeline 400 of the flow and pressure control module 200 is provided with a flow meter 210, a pressure sensor 220, a temperature sensor 230 and a gas distribution tank 240 in sequence along the airflow direction.

[0085] It should be noted that the main function of the flow and pressure control module 200 is to control the flow and pressure of the medium in the pipeline. A regulating valve can be installed on the gas transmission pipeline 400, and a high-precision, high-quality flow meter 210 is installed before the regulating valve to measure the flow rate of the pipeline. Temperature sensors 230 and pressure sensors 220 are installed on the pipeline to detect temperature and pressure parameters at specific locations on the pipeline. Simultaneously, a multi-outlet gas distribution tank 240 is installed at the end of the flow control module, such as... Figure 3 As shown, the gas distribution tank 240 is equipped with 4 to 6 gas outlets according to the flow rate that the flow path can withstand. The gas outlets are designed according to the standard of aviation pipe fittings to facilitate connection with the test piece.

[0086] Preferably, the gas distribution tank 240 should be arranged on both sides of the turbine test piece 700 as much as possible, such as Figure 4 As shown, the cooling air requirements of the turbine test piece 700 at the front, middle, and rear should be fully considered, and the air distribution tank 240 should be arranged reasonably. A reasonable arrangement can effectively reduce the crossing of metal hoses on site and facilitate connection and inspection. The air distribution tank 240 will be connected to the test piece through metal hoses according to the test requirements.

[0087] See Figure 1 As a preferred embodiment of the cooling system for the turbine performance tester of the present invention, the flow and pressure control module 200 is further provided with a test specimen cavity exhaust control pipeline 500. The inlet of the test specimen cavity exhaust control pipeline 500 is connected to the turbine test specimen 700, and an air pump 510 is provided on the test specimen cavity exhaust control pipeline 500.

[0088] Preferably, the vacuum pump 510 is an electric vacuum pump, and the test specimen cavity exhaust control pipeline 500 may also be equipped with a test specimen cavity exhaust regulating valve 520. This test specimen cavity exhaust control pipeline 500, which is equipped with an electric vacuum pump and a control valve, is used to cooperate with the pipeline of the flow and pressure control module 200 to control the exhaust pressure of a certain flow path of the turbine test specimen 700, so as to achieve precise control of the airflow and cavity pressure of that path.

[0089] See Figure 1 As a preferred embodiment of the cooling system for the turbine performance tester of the present invention, each air supply pipeline 400 of the temperature control module 100 and each air supply pipeline 400 of the flow and pressure control module 200 are provided with an air supply regulating valve 440.

[0090] Preferably, the regulating valve is a pneumatic regulating valve, which controls the flow rate and pressure of the medium in the pipeline.

[0091] See Figure 1 As a preferred embodiment of the cooling system for the turbine performance tester of the present invention, the test specimen cavity exhaust control pipeline 500 is provided with a test specimen cavity exhaust regulating valve 520.

[0092] It should be noted that the test specimen cavity exhaust regulating valve 520 is used in conjunction with the air pump 510 to control the exhaust pressure of a certain flow path of the test specimen.

[0093] The flow and pressure control module 200 integrates a flow meter 210, a regulating valve, and a sensor on each gas delivery line 400 to achieve independent closed-loop control of flow and pressure. A specially added exhaust control loop with an electric suction pump provides the hardware foundation for chamber pressure control.

[0094] Preferably, the cooling system for the turbine performance tester of the present invention includes a cooling system co-controller that works with all sensors and actuator signals. This cooling system co-controller is the physical core for realizing the intelligent control method described below.

[0095] In a preferred embodiment of the cooling system for the turbine performance tester of the present invention, the cooling system co-controller is electrically or communicatively connected to the controller of the main gas system, and the cooling system co-controller is electrically or communicatively connected to the gas supply regulating valve 440, the flow meter 210, the pressure sensor 220, and the temperature sensor 230.

[0096] After receiving a signal from the main gas system controller indicating that the main gas system's operating condition is about to change from the current operating condition to the target operating condition, the cooling system co-control controller feeds forward to adjust the gas supply regulating valves 440 on each gas supply pipeline 400 to the estimated opening degree; then, based on the signal feedback from the flow meter 210 and / or the pressure sensor 220 and / or the temperature sensor 230, it controls fine-tuning so that the cooling system cooperates with the main gas system to enable the test piece to quickly reach the target operating condition.

[0097] It should be noted that, since the main air system has a higher status, this invention uses a feedforward + feedback approach to ensure that the air conditioning system parameters will reach the target operating conditions along with the main air system parameters.

[0098] The above design of the air conditioning system co-controller can realize intelligent following control of the main air and the air conditioning, and can execute the following control logic:

[0099] i. Establish mapping relationship: Preset the ratio between the main air flow rate and the target flow rate of each cooling branch.

[0100] It should be noted that this ratio can generally be obtained from the test requirements document. For example, the test requirements document for a turbine test component mentions that the turbine body of the test component requires a total of 5 cooling air channels, A~E, and the ratio of the flow rate of these 5 cooling air channels to the main air flow rate W_inlet should be [a,b,c,d,e]. Among them, a,b,c,d, ande are 5 constants.

[0101] ii. Feedforward-feedback composite control: After receiving the signal of change in the main air flow setpoint, the control valves of each cold air branch are immediately fed forward to adjust to the estimated opening degree, and then the PID closed-loop fine adjustment is performed according to the feedback of the flow meter 210 to achieve synchronous and rapid flow ratio following.

[0102] It should be noted that, in the aforementioned feedforward-feedback composite control, after the entire experiment reaches the first operating condition and completes the data acquisition for the first operating condition (current operating condition), but before preparing to acquire data for the next operating condition point—that is, before acquiring data for the second operating condition (target operating condition)—the control valves of each air conditioning system calculate the air conditioning flow rates W_cool_A, W_cool_B, W_cool_C, W_cool_D, and W_cool_E that the five air conditioning lines in the example above should provide, based on the mapping relationship (e.g., the main air flow rate W_inlet_second operating condition * [a,b,c,d,e]). At this time, the valves in the main air pipeline begin to gradually open or close, adjusting the air intake state of the entire test piece to the second operating condition, and the regulating valves of the air conditioning system also simultaneously adjust towards the target flow rate [W_cool_A, W_cool_B, W_cool_C, W_cool_D, W_cool_E].

[0103] After reaching the adjustment target, the continuous adjustment of the main air system still affects the air conditioning system. However, the degree of mutual influence between the two is now very small. Therefore, feedback control is used for fine-tuning, so that both the main air system and the air conditioning system eventually reach the second operating condition (target operating condition).

[0104] The air conditioning system co-controller can achieve coordinated following control. It is an advanced control strategy that can actively and synchronously follow changes in the main air parameters and make proportional adjustments based on the multiple airflow parameters of the air conditioning system. Its core lies in combining the speed of feedforward with the accuracy of feedback.

[0105] In a preferred embodiment of the cooling system for the turbine performance tester of the present invention, a cavity pressure sensor is installed in the cavity of the turbine test piece 700. The cooling system co-controller is electrically or communicatively connected to the cavity pressure sensor and the pressure sensor 220. The cooling system co-controller is electrically or communicatively connected to the gas supply regulating valve 440, the air pump 510, and the test piece cavity exhaust regulating valve 520.

[0106] The cooling system co-controller compares the set value of the cavity pressure with the actual value. If pressure needs to be increased, the gas supply regulating valve 440 is increased; if pressure needs to be decreased, the gas supply regulating valve 440 is decreased. Alternatively, the vacuum pump 510 is started and the exhaust regulating valve 520 of the test specimen cavity is adjusted.

[0107] It should be noted that the air conditioning system co-controller continuously monitors the actual pressure of the target cavity in the test specimen. The target cavity pressure is controlled through bidirectional adjustment logic: when pressure increase is needed, the gas supply regulating valve 440 of the gas supply line 400 is adjusted; when pressure decrease is needed, one method is to reduce the supply gas pressure, and another is that, due to limitations in flow path capacity, simply reducing the supply gas pressure cannot guarantee that the pressure in each cavity remains stable near the target value. In this case, the exhaust pipe of the test specimen cavity exhaust control line 500 and the suction pump 510 can be activated and adjusted, working in conjunction with the test specimen cavity exhaust regulating valve 520 to create a slightly negative pressure environment. This achieves active control of the internal pressure of the turbine test specimen 700.

[0108] The above design of the air conditioning system co-controller can realize supply-exhaust coordinated chamber pressure control and execute the following control logic:

[0109] i. Obtain the cavity pressure value by means of a cavity pressure sensor placed in the cavity of the test piece.

[0110] ii. The air conditioning system co-controller compares the set value and actual value of the cavity pressure. If pressure needs to be increased, the gas supply regulating valve is adjusted. If pressure needs to be reduced, especially when the exhaust back pressure needs to be lower than atmospheric pressure, the vacuum pump and the exhaust regulating valve of the test specimen cavity are started and adjusted. The active and precise control of the cavity pressure is achieved through bidirectional adjustment logic.

[0111] More preferably, the cooling system for the turbine performance tester of the present invention can also achieve full-process automation and intelligent protection, with the following specific functions:

[0112] i. Initial Configuration: Automatically completes pipeline configuration verification and equipment self-test according to the test items (see...). Figure 6 ).

[0113] ii. Dynamic balance maintenance: During steady-state operation, continuously fine-tune each regulating valve to maintain parameter stability.

[0114] iii. Safety Interlock: When critical parameters (such as axial force, sealing pressure differential, blade tip clearance, etc.) reach alarm values, the controller triggers preset safety logic (such as returning to the previous safe position, activating the venting light, etc.) to achieve active safety protection (see [link]). Figure 5 , Figure 7 ).

[0115] A specific embodiment of the cooling system for the turbine performance tester of the present invention is as follows:

[0116] The hardware system diagram of the air conditioning system in this embodiment is as follows: Figure 1 As shown, the main equipment of the system includes a switching valve 450, a vent regulating valve 460, a gas supply regulating valve 440 of the temperature control module 100, a normal temperature gas distribution tank 110, a gas collection tank 120, a cooler 130, a heater, a connection panel 300 on the intake side, a connection panel 300 on the exhaust side, a hose 310, a flow meter 210, a gas supply regulating valve 440 of the flow and pressure control module 200, a pressure sensor 220, a temperature sensor 230, a gas distribution tank 240, a vacuum pump 510, and a turbine test piece 700.

[0117] The gas source 600 station provides ambient temperature cold air at a certain pressure to the air conditioning system. After opening the switch valve 450, an venting pipeline is set up, and the venting flow rate is regulated by the venting regulating valve 460. The front-end temperature control modules 100 of the air conditioning system are all fixedly connected, equipped with two ambient temperature gas tanks, five heaters 140, and one cooler 130, enabling the temperature control module 100 to simultaneously provide ambient temperature gas, high temperature gas, and refrigeration temperature control functions. To ensure temperature control accuracy, a mixing mode is not used.

[0118] A temperature sensor 230 is installed approximately 1 meter from the outlet of heater 140 to provide temperature feedback for heater 140. Multiple air outlets are provided at each end to facilitate connection with downstream piping and increase connection flexibility.

[0119] The front end of the heater 140 is connected to the cooler 130. This configuration can complete the variable temperature temperature ratio test. The wide temperature range of 253K~500K can be controlled by combining the cooler 130 and the heater 140.

[0120] It should be noted that not all heaters 140 are connected to the cooler 130. The inventors conducted an in-depth analysis based on the test requirements and comprehensively considered the system's responsiveness to the test requirements as well as the system construction cost. Ultimately, they chose to use only two heaters 140 connected to the cooler 130.

[0121] Structural details of the connecting panel 300 are as follows Figure 2 As shown, the outlet flange of the heater 140, the outlet flange of the ambient temperature gas tank, and the outlet flange of the refrigerator 130 are integrated into a connection panel 300. The inlet flange of the gas pipeline 400 of the flow and pressure control module 200 is also integrated into a connection panel 300. Sufficient distance must be reserved between the two connection panels 300 for installing a flexible metal hose. The flange specifications on the two connection panels 300 should be limited to three sizes to increase the versatility and ease of connection of the flexible metal hose. One end of the flexible metal hose is a loose flange joint, and the body is a double-layer braided stainless steel hose 310, supporting ±45° free deflection; it also uses a metal-wound graphite sealing ring to ensure zero leakage in the temperature range of 253K~500K.

[0122] Before the test, the number of cold air flow paths required for the turbine test piece 700 and the parameters of each path are input into the test control platform. The appropriate equipment is selected and flexibly matched through the pipeline controller to form a mapping table. At the same time, the required flow rate, temperature requirements and power of the cold air flow path are determined, and it is determined whether multiple air supply is needed to meet the cold air requirements of a certain path of the test piece. The equipment required for the temperature control module 100 to participate in the test is then determined.

[0123] Preferably, such as Figure 5 As shown, the cooling system for the turbine performance tester of the present invention also includes a piping configuration manager. The flow and pressure control module 200 of the cooling system of the present invention has multiple air delivery pipes 400 (e.g., Figure 1 The diagram shows 14 gas supply lines (400). In actual testing of a specific turbine prototype, only a few of these gas lines may be needed. Whether the flow rate or pressure of these individual gas lines needs to be controlled requires in-depth analysis of the test specifications. (Refer to...) Figure 6 The initial configuration flowchart for the air conditioning system piping is as follows: After receiving the task assignment, perform the following operations:

[0124] a) Confirm that the turbine test piece 700 requires a total of P lines of cooling air, of which X lines are required to provide a relatively accurate flow rate during the test. Select the same number of suitable lines from the cooling air system to supply air to the turbine test piece 700. At the same time, these lines are configured in flow control mode, with the flow rate reaching the target value as the control standard.

[0125] b) Confirm that the turbine test piece 700 requires a total of P lines of cooling air, of which Y lines are required to provide a suitable pressure during the test to ensure sealing, axial force, etc. Select the same number of suitable pipes from the cooling air system to supply air to the turbine test piece 700. At the same time, these pipes are configured in pressure control mode to control parameters such as sealing pressure difference, axial force, and blade tip clearance to reach the target values.

[0126] c) Confirm that the test piece requires a total of P cool air lines, of which Z lines are for controlling the cavity exhaust pressure of the turbine test piece 700. Select the same number of suitable lines from the cool air system for cavity pressure exhaust control. At the same time, these lines are configured in cavity pressure control mode, with parameters such as sealing pressure difference, axial force, and blade tip clearance reaching the target values ​​as control standards.

[0127] The above information needs to be used to create a piping configuration mapping table, which will then be loaded into the air conditioning system co-controller.

[0128] As described above, the cooling system for the turbine performance tester of the present invention has the following advantages:

[0129] I. System Architecture: The modular and reconfigurable air conditioning system hardware integrates air supply and active exhaust circuits, providing a physical basis for multi-dimensional air conditioning control. The adapter panel allows the air supply control pipeline to be switched to exhaust control pipeline at any time. The temperature control module 100 can simultaneously provide the test specimen with airflow at multiple temperatures, including heating, cooling, and ambient temperature.

[0130] II. System control strategy: The present invention provides a main air-cooled air intelligent following control strategy for the air conditioning system. This strategy achieves synchronous adjustment of the main air and the cooling system through the feedforward channel and ensures accuracy through the feedback channel, thus solving the problem of rapid response under dynamic coupling of multiple systems.

[0131] Third, it features innovation in system control: This invention provides a method for active control of test specimen cavity pressure through coordinated air supply and exhaust circuits. By employing bidirectional adjustment logic, it achieves precise control of the internal cavity parameters of the test specimen, breaking through the traditional mode of controlling only inlet parameters.

[0132] IV. System Integration Innovation: This invention's air conditioning system integrates a complete intelligent automation logic covering initialization, operation, and safety monitoring. By integrating the above innovative strategies into an organic whole, it achieves a shift from manual adjustment to "proactive safety" control.

[0133] Fifth, the pipeline configuration manager enables flexible configuration of multiple cooling air channels, which can accurately match pipeline resources according to the needs of the test task. This design significantly improves the adaptability and control accuracy of the system, which can not only meet the different requirements of different test pieces for cooling air parameters, but also avoid resource waste through modular configuration.

[0134] See Figures 5-7 The present invention also provides a control method for a cooling system for a turbine performance tester, the control method being used to control the cooling system for a turbine performance tester as described above; the control method includes main air-cooled air following control, supply-exhaust coordinated chamber pressure control, and safety monitoring and interlocking control.

[0135] As a preferred embodiment of the cooling system control method for the turbine performance tester of the present invention, the main gas-cooled gas following control includes:

[0136] Real-time monitoring of the main air flow rate of the main air system and the air conditioning system flow rate.

[0137] The target flow rate of the cooling system is calculated based on the preset flow rate relationship between the main air system and the cooling system, and the flow rate of the cooling system is adjusted to the target flow rate.

[0138] As a preferred embodiment of the cooling system control method for a turbine performance tester, the supply-exhaust coordinated chamber pressure control includes:

[0139] Real-time monitoring of the actual pressure in chamber 700 of the turbine test piece.

[0140] When pressure needs to be increased, adjust the gas supply regulating valve 440; when pressure needs to be decreased, reduce the gas supply pressure to control the chamber pressure to decrease and stabilize near the target value. When reducing the gas supply pressure cannot guarantee that the chamber pressure will stabilize near the target value, start and adjust the electric vacuum pump and the test piece chamber exhaust regulating valve 520.

[0141] As a preferred embodiment of the control method for the cooling system of a turbine performance tester, the safety monitoring and interlocking control includes:

[0142] The system monitors the air supply pressure in real time and calculates the various sealing pressure differences and axial force of the turbine test piece 700, and obtains the blade tip clearance of the turbine test piece 700; it maintains that the various sealing pressure differences of the turbine test piece 700 are less than the limit value, maintains that the axial force of the turbine test piece 700 is less than the limit value, and maintains that the blade tip clearance of the turbine test piece 700 is within the set reasonable range.

[0143] The system monitors the cold air supply pressure in real time and measures the target cavity pressure of the turbine test piece 700, while maintaining the cavity pressure of the turbine test piece 700 within the limit range.

[0144] It should be noted that pressure measuring points are arranged inside the cavity of the turbine test piece 700 for measuring the cavity pressure.

[0145] Traditional system control typically employs sequential adjustment, which is time-consuming. In contrast, the cooling system control method for the turbine performance tester of this invention uses synchronous following adjustment, which is more efficient.

[0146] The implementation steps of a specific embodiment of the cooling system control method for a turbine performance tester of the present invention are as follows:

[0147] I. System Initialization Configuration

[0148] Before the test, the operator configures the test tasks on the host computer. The piping configuration manager generates a cooling system piping configuration table based on the test requirements for multiple cooling air piping lines. This is generally divided into flow control piping, supply pressure control piping, and cavity exhaust control piping. The cooling system co-controller automatically calls preset parameters (such as the flow ratio of each cooling air line, target cavity pressure, and safety threshold) and completes self-checks of the sensors and actuators, putting the cooling system into a ready state.

[0149] like Figure 5 As shown, the cooling system control method for the turbine performance tester of the present invention configures the piping through a piping configuration manager, such as... Figure 1 As shown, the flow and pressure control module 200 of the cooling system of this invention has 14 air supply lines 400. In actual testing of a specific turbine test piece, only a few of these cooling lines may be needed. Whether the flow rate or pressure of these individual cooling lines needs to be controlled requires in-depth analysis of the test specifications. (Refer to...) Figure 6 The initial configuration flowchart for the air conditioning system piping is as follows: After receiving the task assignment, perform the following operations:

[0150] a) Confirm that the turbine test piece 700 requires a total of P lines of cooling air, of which X lines are required to provide a relatively accurate flow rate during the test. Select the same number of suitable lines from the cooling air system to supply air to the turbine test piece 700. At the same time, these lines are configured in flow control mode, with the flow rate reaching the target value as the control standard.

[0151] b) Confirm that the turbine test piece 700 requires a total of P lines of cooling air, of which Y lines are required to provide a suitable pressure during the test to ensure sealing, axial force, etc. Select the same number of suitable pipes from the cooling air system to supply air to the turbine test piece 700. At the same time, these pipes are configured in pressure control mode to control parameters such as sealing pressure difference, axial force, and blade tip clearance to reach the target values.

[0152] c) Confirm that the test piece requires a total of P cool air lines, of which Z lines are for controlling the cavity exhaust pressure of the turbine test piece 700. Select the same number of suitable lines from the cool air system for cavity pressure exhaust control. At the same time, these lines are configured in cavity pressure control mode, with parameters such as sealing pressure difference, axial force, and blade tip clearance reaching the target values ​​as control standards.

[0153] The above information needs to be used to create a piping configuration mapping table, which will then be loaded into the air conditioning system co-controller.

[0154] II. Intelligent Collaborative Control in Operation

[0155] (1) Main air-cooled air following control

[0156] refer to Figure 7 When a command is received to change from the first operating condition (current operating condition) to the second operating condition (target operating condition), the signal is transmitted in real time to the air conditioning system's co-controller. Based on preset flow ratios and sealing / cavity pressure control relationships, the air conditioning system co-controller adjusts the regulating valves of each air conditioning branch to quickly approach the target opening. Based on real-time feedback from the flow meters 210, pressure sensors 220, and temperature sensors 230 of each branch, the air conditioning system controller performs closed-loop fine-tuning of the regulating valves to ensure accurate and stable flow in the flow-controlled pipelines, sufficient pressure supply in the pressure-controlled pipelines, and proper back pressure adjustment in the cavity pressure-controlled pipelines. This achieves rapid, synchronous, and precise following of the main air supply by the air conditioning system.

[0157] (2) Supply-exhaust coordinated chamber pressure control

[0158] The air conditioning system's co-controller continuously monitors the actual pressure in the target cavity of the test specimen. The target cavity pressure is controlled via bidirectional adjustment logic: when pressure increase is needed, the gas supply regulating valve 440 of the gas supply line 400 is adjusted; when pressure decrease is needed, one method is to reduce the supply pressure, and another is that, due to limitations in flow path capacity, simply reducing the supply pressure cannot guarantee that the pressure in each cavity remains stable near the target value. In this case, the suction pump 510 of the test specimen cavity exhaust control line 500 can be activated and adjusted, working in conjunction with the test specimen cavity exhaust regulating valve 520 to create a slightly negative pressure environment. This achieves active control of the internal pressure of the turbine test specimen 700.

[0159] (3) Safety monitoring and interlocking control

[0160] The air conditioning system's co-controller monitors key parameters (such as differential pressure and axial force) in real time throughout the entire process. Once any parameter reaches the alarm value, the system immediately triggers preset safety interlock logic (such as sequentially adjusting valves to the previous safe state, initiating venting, etc.), rather than relying on manual judgment, thereby achieving proactive safety protection.

[0161] In summary, the cooling system and control method for the turbine performance tester of the present invention have the following advantages:

[0162] First, it improves testing efficiency. The modularly designed hardware system can significantly shorten the time required for test preparation and hardware switching due to changes in test subjects.

[0163] Second, relying on a feedforward-feedback composite control architecture, rather than a simple closed-loop control, the synchronous following control of the main gas and cooling gas reduces the operating condition adjustment time by more than 50%. Furthermore, the coordinated changes in the main gas and cooling gas can reduce the impact on the turbine test specimen caused by traditional step-by-step adjustments, making force changes smoother, reducing the vibration risk of the turbine test specimen, and making it more controllable.

[0164] Third, this invention achieves a breakthrough in control capabilities by using a novel "supply-exhaust coordinated chamber pressure control" to change from "supply control" to "chamber pressure control," enabling the air conditioning system to support more complex experiments.

[0165] Fourth, this invention is intelligent and highly secure. Through integrated process control logic, it reduces the risk of human operation and improves the safety and repeatability of the experiment.

[0166] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A cooling system for a turbine performance tester, characterized in that, The air conditioning system includes a temperature control module, a flow and pressure control module, and a connection panel; The temperature control module is used to provide cold air at different temperatures. The temperature control module includes multiple air supply lines. One end of each air supply line is connected to an air source, and the other end of each air supply line is connected to a connection panel. Each gas supply pipeline of the temperature control module and each gas supply pipeline of the flow and pressure control module is equipped with a gas supply regulating valve; The flow and pressure control module is used to adjust the outlet flow and pressure and distribute the cold air. The flow and pressure control module includes multiple air supply lines. One end of each air supply line is connected to the connection panel, and the other end of each air supply line is connected to the turbine test piece. Each gas pipeline of the flow and pressure control module is equipped with a flow meter, a pressure sensor, a temperature sensor, and a gas distributor in sequence along the airflow direction. The flow and pressure control module is also provided with a test specimen cavity exhaust control pipeline. The inlet of the test specimen cavity exhaust control pipeline is connected to the turbine test specimen, and a vacuum pump is provided on the test specimen cavity exhaust control pipeline. The connection panel has multiple interfaces. The interface of the connection panel on the temperature control module side and the interface of the connection panel on the flow and pressure control module side are connected by a hose. Through the flexible selection and connection of the interfaces, the interfaces of the temperature control module and the flow and pressure control module can be arbitrarily matched to realize the reconstruction of the cooling system and quickly change its flow path topology and function to adapt to the cooling supply system for different test requirements. The air conditioning system is electrically or communicatively connected to the air conditioning system co-controller. The air conditioning system co-controller is electrically or communicatively connected to the main gas system controller, and the air conditioning system co-controller is electrically or communicatively connected to the gas supply regulating valve, the flow meter, the pressure sensor, and the temperature sensor. The cooling system co-controller includes a pipeline configuration mapping table, which is formed by inputting the number of cooling air paths required by the turbine test piece and the parameters of each path into the test control platform. After receiving a signal from the main gas system controller indicating that the main gas system's operating condition is about to change from the current operating condition to the target operating condition, the cooling system co-control controller feeds forward to adjust the gas supply regulating valves on each gas supply pipeline to the estimated opening degree; then, based on the signal feedback from the flow meter and / or the pressure sensor and / or the temperature sensor, it controls fine-tuning so that the cooling system cooperates with the main gas system to enable the test specimen to reach the target operating condition; The air conditioning system co-controller achieves coordinated following control, actively and synchronously adjusting the main air parameters according to changes in the multiple airflow parameters of the air conditioning system. The coordinated follow control calculates the target flow value of the cooling system based on the preset flow relationship between the main air system and the cooling system, and adjusts the flow of the cooling system to the target flow value.

2. The cooling system for a turbine performance tester as described in claim 1, characterized in that, The temperature control module has multiple gas supply lines, including a first gas supply line, on which a normal temperature gas distribution tank is installed.

3. The cooling system for a turbine performance tester as described in claim 1, characterized in that, The temperature control module has multiple gas supply lines, including a second gas supply line, on which a gas collection tank and a heater are sequentially arranged along the airflow direction.

4. The cooling system for a turbine performance tester as described in claim 1, characterized in that, The temperature control module has multiple gas supply lines, including a third gas supply line, on which a heater and a cooler are sequentially arranged along the airflow direction.

5. The cooling system for a turbine performance tester as described in claim 1, characterized in that, The test specimen cavity exhaust control pipeline is equipped with a test specimen cavity exhaust regulating valve.

6. The cooling system for a turbine performance tester as described in claim 5, characterized in that, A cavity pressure sensor is installed inside the cavity of the turbine test piece. The cooling system co-controller is electrically or communicatively connected to the cavity pressure sensor and the pressure sensor. The cooling system co-controller is electrically or communicatively connected to the gas delivery regulating valve, the air pump, and the test piece cavity exhaust regulating valve on the test piece cavity exhaust control pipeline. The cooling system co-controller compares the set value of the cavity pressure with the actual value. If pressure needs to be increased, the gas supply regulating valve is increased; if pressure needs to be decreased, the gas supply regulating valve is decreased. Alternatively, the vacuum pump is started and the exhaust regulating valve of the test specimen cavity is adjusted.

7. A method for controlling a cooling system for a turbine performance tester, characterized in that, The control method is used to control the cooling system of the turbine performance tester as described in claims 1-6; the control method includes main gas-cooled gas following control, supply-exhaust coordinated chamber pressure control, safety monitoring and interlocking control.

8. The cooling system control method for a turbine performance tester as described in claim 7, characterized in that, The main air-cooled air following control includes: Real-time monitoring of the main air flow rate of the main air system and the air conditioning system flow rate; The target flow rate of the cooling system is calculated based on the preset flow rate relationship between the main air system and the cooling system, and the flow rate of the cooling system is adjusted to the target flow rate. Then, fine-tuning is controlled based on sensor signal feedback so that the cooling system works in conjunction with the main air system to make the test piece reach the target operating condition.

9. The cooling system control method for a turbine performance tester as described in claim 7, characterized in that, The gas supply-exhaust coordinated chamber pressure control includes: Real-time monitoring of the actual pressure in the turbine test specimen cavity; When pressure needs to be increased, increase the gas supply regulating valve; when pressure needs to be decreased, reduce the gas supply pressure to control the chamber pressure to decrease and stabilize near the target value. If reducing the gas supply pressure cannot guarantee that the chamber pressure will stabilize near the target value, start the vacuum pump and adjust the test specimen chamber exhaust regulating valve.

10. The cooling system control method for a turbine performance tester as described in claim 7, characterized in that, The safety monitoring and interlocking control includes: The system monitors the air supply pressure in real time and calculates the pressure difference of each seal of the turbine test piece, the axial force of the turbine test piece, and obtains the blade tip clearance of the turbine test piece; it maintains that the pressure difference of each seal of the turbine test piece is less than the limit value, maintains that the axial force of the turbine test piece is less than the limit value, and maintains that the blade tip clearance of the turbine test piece is within the set range. The system monitors the cooling air supply pressure in real time and measures the target cavity pressure of the turbine test piece, while maintaining the cavity pressure of the turbine test piece within the specified range.

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