A gas turbine turbine blade cooling effect test system

Abstract

The application discloses a gas turbine turbine blade cooling effect test system and relates to the technical field of gas turbines. The system comprises a main air subsystem, a fuel supply and combustion subsystem, a test section assembly, a cooling air subsystem, an exhaust heat management subsystem and a central measurement and control subsystem. The main air subsystem provides combustion-supporting air; the fuel supply and combustion subsystem generates high-temperature fuel gas using natural gas, hydrogen or a mixed fuel thereof; the test section assembly is used for installing test blades, and the inlet section, test section and exhaust section thereof can be quickly replaced for different blades; the cooling air subsystem provides multiple independent adjustable cooling air flows; the exhaust heat management subsystem performs multi-stage cooling and purification on exhaust gas; and the central measurement and control subsystem integrates control and data acquisition. The application can realize fuel flexible adaptation, test section quick replacement, independent regulation and control of cooling air flows and efficient exhaust heat management, and can safely and efficiently complete the cooling effect test of turbine blades under full-temperature and medium-temperature working conditions.

Description

Technical Field

[0001] This application relates to the field of gas turbine technology, specifically to a gas turbine blade cooling effect testing system. Background Technology

[0002] The inlet gas temperature of modern heavy-duty gas turbines generally exceeds 1400℃, far exceeding the tolerance limit of high-temperature alloy materials. Therefore, hollow air-cooled blade designs are widely adopted, using internal precision cooling channels to control the blade metal temperature within a safe range of 600℃ to 900℃ using cooling gas. Thus, in the development of heavy-duty gas turbines with power ratings of 300MW and above, accurate verification of blade cooling effectiveness is essential. This typically requires constructing a test system capable of simulating real-world operating conditions to conduct detailed measurements of blade cooling efficiency, temperature distribution, and flow resistance characteristics under full-temperature and intermediate-temperature conditions. This testing is the fundamental basis for the design, optimization, and finalization of the blade cooling structure.

[0003] However, existing turbine blade cooling effect testing systems, especially full-temperature testing systems, still have several limitations. Traditional systems often use a single fuel, making it difficult to flexibly simulate the actual situation of gas turbines using multiple fuels. Furthermore, the systems lack the ability to independently and precisely adjust multiple cooling air streams, making it difficult to meet the refined research needs of complex blade cooling structures. Test section structures are typically designed for specific blades, resulting in poor versatility and long cycles and high costs when changing test objects. In terms of exhaust heat management, the cooling efficiency and structural adaptability of existing systems for high-temperature gas need improvement, affecting operational safety and test stability. Simultaneously, the integration and control of the entire testing system's combustion, cooling, and measurement and control subsystems are complex, lacking efficient coordination, increasing operational difficulty and data uncertainty risks. These factors collectively restrict the rapid iteration of cooling technology and research on the adaptability of new fuels.

[0004] Existing patent CN111855186A discloses a turbine rotor blade cooling effect testing device. Through modular test section components, auxiliary blade components, and piping design, it aims to improve the versatility of the testing device, thereby shortening the testing cycle and reducing testing costs. Existing patent CN114858470A discloses a turbine blade cooling effect testing system and method. This system integrates a static testing device with an existing aero-engine gas generator as a heat source, along with an independent cooling air source and control system, aiming to reduce system construction costs and improve the flexibility and ease of use of the device layout. The above-mentioned existing solutions mainly focus on optimizing versatility and cost, but do not fundamentally solve key technical problems such as limited fuel adaptability, insufficient independent and precise control of multiple cooling air streams, and the safe and efficient handling of high-heat-load exhaust gas during full-temperature / medium-temperature tests.

[0005] In summary, existing test systems still have significant shortcomings in terms of fuel flexibility, cooling control precision, test section versatility, exhaust thermal management, and system integration. In particular, there is a lack of an integrated test platform that can be compatible with multiple fuels, achieve precise control of the cooling gas path, and has efficient thermal management capabilities. Summary of the Invention

[0006] To address the aforementioned problems in the prior art, this application proposes a test system for the cooling effect of gas turbine blades. The specific technical solution is as follows: A gas turbine blade cooling effect testing system includes: The main air subsystem is used to provide combustion air; A fuel supply and combustion subsystem, connected to the main air subsystem, is used to mix and burn natural gas, hydrogen, or a mixture thereof with combustion air to generate high-temperature fuel gas. The test section assembly, connected to the fuel supply and combustion subsystem, is used to mount the blade model to be tested and to form a high-temperature gas passage. A cooling air subsystem, separate from the main air subsystem and connected to the test section assembly, is used to provide cooling airflow; An exhaust thermal management subsystem, connected to the test section assembly, is used to cool and purify the high-temperature gas flowing out of the test section; The central measurement and control subsystem is connected to the main air subsystem, the fuel supply and combustion subsystem, the cooling air subsystem, and the exhaust thermal management subsystem, respectively, and is used to coordinate operation, control key parameters, and collect and process test data.

[0007] Furthermore, the fuel supply and combustion subsystem includes a fuel gas supply source, a fuel control and ignition device, and a burner; the fuel gas supply source provides natural gas, hydrogen, or a mixture thereof; the fuel control and ignition device is used to regulate the fuel flow rate and ratio and perform ignition; the inlet of the burner is connected to the outlet of the fuel control and ignition device and the main air subsystem.

[0008] Furthermore, the test section assembly adopts a modular design, including an intake section, a test blade test section, and an exhaust section that are detachably connected in sequence along the airflow direction; the test blade model is installed inside the test blade test section; the test blade test section adopts a double-wall structure.

[0009] Furthermore, thermocouples are arranged on the surface of the blade model under test, and the signal wires of the thermocouples are led out through a preset interface on the test section cylinder of the test blade and connected to the central measurement and control subsystem.

[0010] Furthermore, both the intake section and the exhaust section are configured with a double-layer water-cooled structure and are respectively connected to an independent cooling water pump and a circulating water tank.

[0011] Furthermore, the cooling pipe of the exhaust section is connected to the inlet of the exhaust thermal management subsystem via a branch, and a regulating valve is provided on the branch; a temperature sensor is provided at the inlet of the exhaust thermal management subsystem for feedback control of the opening of the regulating valve.

[0012] Furthermore, the cooling air subsystem includes an air compressor, a main regulating valve, and at least three branch lines; the outlet of the air compressor is split into the at least three branch lines after passing through the main regulating valve; each branch line is equipped with a branch flow regulating valve, a flow meter, a pressure sensor, and a temperature sensor.

[0013] Furthermore, the exhaust thermal management subsystem includes an exhaust pipe and an exhaust gas treatment device. The exhaust pipe is equipped with a water spray device, and the exhaust gas treatment device is connected to the outlet of the exhaust pipe.

[0014] Furthermore, a temperature sensor is installed at the tail end of the exhaust pipe; the signal from the temperature sensor is fed back to the central measurement and control subsystem to adjust the opening of the water supply valve of the spray water device.

[0015] Furthermore, an exhaust back pressure valve is provided at the tail end of the exhaust pipe to regulate the system back pressure of the exhaust pipe.

[0016] Furthermore, the exhaust pipe adopts a segmented design, including an adjustable-angle front pipe section and an axially straight rear pipe section.

[0017] Furthermore, the central measurement and control subsystem includes a control cabinet, a data acquisition and conversion card, and a computer monitoring station; the control cabinet is electrically connected to each actuator in the system for centralized control; the data acquisition and conversion card is electrically connected to each sensor and flow meter in the system for data signal acquisition; the computer monitoring station is communicatively connected to the control cabinet and the data acquisition and conversion card for command issuance, data reception, and processing.

[0018] By applying the above-described technical solution of this application, at least the following technical effects are achieved: 1. This application fundamentally overcomes the limitation of traditional test systems that rely on a single fuel source by employing a combustion chamber using natural gas, hydrogen, or a mixture thereof as fuel, and equipping it with fuel control and ignition devices. This design enables the system to flexibly and accurately simulate the actual combustion conditions of heavy-duty gas turbines using different fuels (especially future-oriented hydrogen-rich or pure hydrogen fuels), providing a crucial experimental means for studying the impact of fuel composition changes on the thermal load and cooling requirements of turbine blades.

[0019] 2. This application adopts a modular test section design, with the intake section, test blade test section, and exhaust section forming a unified component. This allows for targeted design and rapid overall replacement based on the geometry and cooling structure of different blades, while maintaining standardized interfaces with the main air path and cooling air path. This "one main unit, multiple test sections" model significantly shortens the system modification and preparation cycle caused by changes in the test object, reduces redundant construction costs, and achieves efficient reuse of the test platform and rapid iteration of testing activities.

[0020] 3. This application constructs a multi-stage, coordinated thermal management scheme for the high-heat-load exhaust gas generated during testing. From initial water cooling in the exhaust section to deep spray cooling in the exhaust pipe, combined with a segmented, adjustable exhaust pipe design, it effectively reduces local heat load and ensures stable airflow. In particular, the closed-loop control of the spray water volume based on feedback from the temperature sensor at the end of the exhaust pipe, and the independent control of the exhaust back pressure, together achieve precise management of exhaust temperature and pressure, protecting downstream equipment and ensuring that the entire testing process is conducted in a controllable and safe environment.

[0021] 4. This application establishes a completely independent cooling air subsystem, which provides at least three independently adjustable cooling air branches, each equipped with complete adjustment, measurement, and sensing devices. This design enables precise and independent control of the flow rate, pressure, and temperature of each branch in the complex cooling channels inside the blade, accurately replicating the cooling air distribution state of the blade during actual operation. This provides indispensable controllability for verifying the design effectiveness of advanced cooling structures and obtaining accurate cooling efficiency data.

[0022] 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

[0023] 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 schematic diagram of the framework of a gas turbine blade cooling effect test system proposed in this application is shown; Figure 2 A partial structural schematic diagram of a gas turbine blade cooling effect test system proposed in this application is shown.

[0024] Reference numerals: 10-Air compressor, 11-Regulating valve, 12-Flow meter, 13-Pressure sensor, 14-Temperature sensor, 20-Fuel supply source, 21-Fuel control and ignition device, 22-Burner, 30-Intake section, 31-Cooling water pump, 32-Circulating water tank, 33-Temperature sensor, 34-Regulating valve, 35-Total pressure sensor, 36-Total temperature sensor, 40-Test blade test section, 41-Test blade model, 50-Exhaust gas Section, 51-Cooling water pump, 52-Circulating water tank, 53-Temperature sensor, 54-Regulating valve, 55-Temperature sensor, 56-Regulating valve, 60-Air compressor, 61-Regulating valve, 62-Flow regulating valve, 63-Flow meter, 63-Temperature sensor, 65-Pressure sensor, 70-Exhaust pipe, 71-Tail gas treatment device, 72-Temperature sensor, 73-Exhaust back pressure valve, 80-Control cabinet, 81-Data acquisition and conversion card, 82-Computer monitoring console. Detailed Implementation

[0025] 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.

[0026] 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.

[0027] Addressing the common technical problems in existing turbine blade cooling effect testing systems, such as limited fuel adaptability, insufficient precision in multi-path cooling airflow control, poor versatility of test sections, and low exhaust gas treatment efficiency under high heat loads, this application proposes a gas turbine blade cooling effect testing system. This system aims to simulate the extreme gas environment at the turbine inlet of a heavy-duty gas turbine, exceeding 1400°C, and can accurately measure the cooling performance of the blades under full-temperature and intermediate-temperature conditions.

[0028] like Figure 1The diagram illustrates a turbine blade cooling effect testing system provided in this embodiment of the invention. Its subsystems are connected and coordinated according to the gas flow and cooling flow paths. The system mainly includes: a main air subsystem for providing a stable and controllable combustion airflow; a fuel supply and combustion subsystem for burning natural gas, hydrogen, or mixtures thereof to generate high-temperature gas; a test section assembly for mounting test blades and forming a high-temperature gas flow channel; a cooling air subsystem for providing multiple independently adjustable cooling airflows to the interior of the test blades and the test section; an exhaust heat management subsystem for cooling and purifying the high-temperature exhaust gas after the test; and a central monitoring and control subsystem for integrating and controlling the entire operation process and collecting and processing test data. In terms of workflow, the main air subsystem is connected to the fuel supply and combustion subsystem to provide the gas source. The high-temperature gas generated by combustion flows sequentially through the test section assembly. The cooling air subsystem is independently connected to the corresponding interface in the test section assembly. The exhaust heat management subsystem is connected downstream of the test section assembly. The central monitoring and control subsystem is signal-connected to all the above subsystems.

[0029] Specifically, the main air subsystem includes an air compressor 10 as the air source. The air output from the air compressor 10 is delivered through a main air path, on which a regulating valve 11, a flow meter 12, a pressure sensor 13, and a temperature sensor 14 are sequentially arranged along the airflow direction. By adjusting the regulating valve 11 and monitoring the parameters of the flow meter 12, pressure sensor 13, and temperature sensor 14, a stable and controllable mainstream air working fluid is formed to provide an air source for downstream combustion.

[0030] Specifically, the fuel supply and combustion subsystem includes a fuel supply source 20, a fuel control and ignition device 21, and a burner 22. The fuel supply source 20 provides natural gas, hydrogen, or a mixture thereof. The fuel control and ignition device 21 regulates and controls the fuel flow rate and ratio, and performs ignition. The inlet of the burner 22 is connected to the outlet of the fuel control and ignition device 21 and the main air path of the main air subsystem, mixing and burning the fuel with combustion air to generate high-temperature gas that meets the target test temperature. This subsystem achieves centralized control of fuel supply and combustion start / stop through the fuel control and ignition device 21, enabling the entire cooling effect test system to have flexible fuel adaptability and accurately simulate the effects of different fuel compositions on blade thermal load and cooling effect.

[0031] Specifically, the test section assembly is the core area for installing test blades and measuring cooling effects, and sequentially includes an inlet section 30, a test blade test section 40, and an exhaust section 50 along the airflow direction. The inlet section 30 is connected to the outlet of the burner 22, used to smoothly transition the gas flow from the burner outlet to a test section conforming to the geometry of the blade channel. The inlet of the test blade test section 40 is connected to the outlet of the inlet section 30, and its outlet is connected to the inlet of the exhaust section 50. The test blade test section 40 is used to install and fix the test blade model and forms the core test channel through which high-temperature gas flows; the exhaust section 50 is used to receive and exhaust the high-temperature gas flowing through the test blade test section 40, and transport it to the downstream exhaust thermal management subsystem for further processing.

[0032] In this embodiment, the intake section 30 preferably adopts a double-layer water-cooled structure. The intake section 30 is connected to a cooling pipeline, which includes a cooling water pump 31 and a circulating water tank 32. Cooling water is pumped from the circulating water tank 32 by the cooling water pump 31 and delivered to the interlayer inlet of the intake section 30. After cooling through the interlayer, it flows out from the downstream interlayer outlet and finally returns to the circulating water tank 32 for further cooling and circulation. Specifically, on the return water section downstream of the interlayer outlet of the intake section 30, a temperature sensor 33 and a regulating valve 34 are provided to monitor the temperature of the cooling water flowing out of the intake section 30 and adjust the circulation flow rate. Furthermore, an installation interface is provided on the end wall of the intake section 30 for installing a total pressure sensor 35 and a total temperature sensor 36. Preferably, the total pressure sensor 35 is arranged in one row, and the total temperature sensor 36 is arranged in three rows to obtain a more comprehensive distribution of airflow parameters on the intake cross-section.

[0033] Optional, see below Figure 2 As shown, the inlet section 30 can be designed as a two-section combined structure, including a front section pipe and a rear section pipe, to adapt to the profile transition requirements from the burner outlet to the blade inlet. Specifically, the front section pipe is a transition section, with its inlet adapted to the shape of the burner 22 outlet, having a tapered cross-section, and its outlet having the required shape for the downstream rear section pipe; the rear section pipe is a stabilization section, having a uniform cross-section, and its outlet shape matches the inlet profile of the test blade test section 40. This combined design allows the high-temperature gas flow to transition more smoothly from the circular cross-section of the burner outlet to the rectangular or specific profile required by the blade, effectively reducing flow losses and improving airflow uniformity, thereby providing more stable and realistic inlet conditions for the downstream test section.

[0034] In this embodiment, a test blade model 41 is installed inside the test blade test section 40. The cylinder of the test blade test section 40 encloses the test blade model 41, placing it in the main channel of the high-temperature combustion gas. A large number of thermocouples are densely arranged on the surface of the test blade model 41 for real-time monitoring of its outer wall temperature distribution. The signal wires of the thermocouples are led out through pre-set sealed electrical interfaces at both ends of the cylinder of the test blade test section 40 and ultimately connected to the data acquisition and conversion card of the central measurement and control subsystem. The test blade test section 40 can be designed as a single-wall structure or a double-wall structure according to testing requirements. In a preferred embodiment, the test blade test section 40 adopts a double-wall structure, with the interlayer cooling air sourced from the cooling air subsystem. Simultaneously, the cooling gas required for the internal cooling channel of the test blade model 41 is also supplied by the cooling air subsystem through a dedicated interface. The entire test blade test section 40 adopts a modular design, allowing for complete replacement according to different test blade models 41. This modular design ensures the standardization of the mechanical and electrical interfaces between the test section and the main system, making the switching between tests for different blades more convenient and efficient.

[0035] In this embodiment, the exhaust section 50 is connected downstream of the test section 40 for the test blade. The exhaust section 50 is configured with a double-walled structure to provide initial cooling for the high-temperature combustion gas exiting the test section. The exhaust section 50 is connected to an independent circulating cooling pipeline. This pipeline has a cooling water pump 51 and a circulating water tank 52 in the section near the downstream end of the exhaust section 50, and a temperature sensor 53 and a regulating valve 54 in the section near the upstream end of the exhaust section 50. The cooling water in this pipeline flows in the opposite direction to the cooling water in the intake section 30. The cooling water in the exhaust section 50 uses a counter-current cooling design: cooling water is pumped from the circulating water tank 52 by the cooling water pump 51, first delivered to the inlet of the jacket layer near the downstream end of the exhaust section 50, then flows upstream through the entire jacket layer, absorbing heat before exiting from the outlet near the upstream end of the jacket layer, and finally returning to the circulating water tank 52 to complete the circulation. The temperature sensor 53 and the regulating valve 54 are used to monitor the temperature of the cooling water exiting the jacket layer and to regulate the circulation flow rate, respectively. Temperature measuring points are set in the internal passage of the exhaust section 50 for installing temperature sensors 55 to monitor the gas temperature of the exhaust section 50.

[0036] Furthermore, the cooling pipes of the exhaust section 50 are not only used for its own cooling but also extend downstream to the exhaust pipe 70 via branch pipes, providing a cooling water source for the spray water device installed in the exhaust pipe 70. One end of this branch pipe is connected to a pipe section near the downstream of the exhaust section 50, and the other end is connected to the water supply valve of the spray water device in the exhaust pipe. A regulating valve 56 is installed on this branch pipe to regulate the flow rate of cooling water to the spray water device. This design allows for the coordinated use of the cooling water source from the exhaust section 50 to the exhaust pipe 70, achieving more efficient and continuous system thermal management. The exhaust pipe downstream of the exhaust section 50 can be designed in sections to accommodate the outlet flow direction of different test sections.

[0037] Specifically, the cooling air subsystem provides multiple independent and controllable cooling air sources for the internal cooling channels of the test blade model and the test blade test section assembly. This subsystem includes an air compressor 60. The outlet pipe of the air compressor 60, after being regulated by a regulating valve 61, splits into at least three independent cooling air branches. Each cooling air branch is equipped with a branch flow regulating valve 62, a branch flow meter 63, a branch temperature sensor 64, and a branch pressure sensor 65, thereby enabling independent monitoring and precise control of the flow rate, pressure, and temperature parameters of each cooling air branch. These cooling air branches are connected to corresponding interfaces of the test blade test section 40, providing cooling air sources for the internal cooling channels of the test blade model 41 and the double-walled structure of the test blade test section 40 body.

[0038] Specifically, the exhaust thermal management subsystem is used for final cooling, pressure regulation, and purification of the high-temperature fuel gas after initial cooling. This subsystem includes an exhaust pipe 70 and a tail gas treatment device 71. The exhaust pipe 70 is connected to the outlet of the exhaust section 50 and contains a spray water device. A temperature sensor 72 and an exhaust back pressure valve 73 are installed at the tail end of the exhaust pipe 70. The temperature sensor 72 provides real-time feedback of the fuel gas temperature after spray cooling, compares it with a preset temperature value, and dynamically adjusts the opening of the spray water device's water supply valve accordingly, thereby precisely controlling the amount of water sprayed into the exhaust pipe 70. The fully cooled gas-liquid mixture is then pressure-regulated by the exhaust back pressure valve 73 and finally enters the tail gas treatment device 71 for purification treatment before being discharged into the atmosphere after meeting standards. The spray water and other cooling return water generated during the operation of this subsystem are collected, treated, and recycled. (See reference...) Figure 2As shown, in a preferred embodiment, the exhaust pipe 70 adopts a segmented design, including a front pipe section whose angle and direction can be flexibly adjusted, and a rear straight pipe section connected to the exhaust gas treatment device 71. The inlet of the front pipe section is connected to the outlet of the exhaust section 50, and its outlet is configured to axially discharge air and connect to the rear straight pipe section. This design can adapt to the outlet flow direction of different test sections, effectively reducing local flow resistance and heat load.

[0039] Specifically, the central monitoring and control subsystem is used for data acquisition and coordinated operation of the entire cooling effect test system. This subsystem includes a control cabinet 80, a data acquisition and conversion card 81, and a computer monitoring console 82. The control cabinet 80 is electrically connected to all regulating valves, water pumps, and fuel control and ignition devices 21 in the system, for centralized control of their start / stop and operating parameters. The data acquisition and conversion card 81 is electrically connected to all pressure sensors, temperature sensors, and flow meters distributed throughout the system, for real-time acquisition of pressure, temperature, and flow signals. The computer monitoring console 82 is communicatively connected to both the control cabinet 80 and the data acquisition and conversion card 81, for sending control commands, receiving and processing acquired data, and realizing automated monitoring, data recording, and comprehensive analysis of the entire cooling effect test process.

[0040] The test process of the gas turbine blade cooling effect test system proposed in this application is as follows: Install the corresponding test section components according to the test blade model, including the intake section 30, the test blade test section 40, and the exhaust section 50. Start the main air supply subsystem to supply a stable airflow. Simultaneously, start the fuel supply and combustion subsystem. Based on the set temperature target and fuel ratio, precisely adjust and ignite the fuel through the fuel control and ignition device 21 to generate a stable high-temperature gas flow in the burner 22. Simultaneously start the cooling air subsystem. According to the blade cooling design requirements, independently set and adjust the flow and pressure of multiple cooling air streams leading to the interior of the test blade model 41 and the interlayer of the test blade test section 40 through the main regulating valve 61 and each branch flow regulating valve 62. The high-temperature gas flows through the test section components to heat the test blade model 41, while the cooling air flows through its internal channels and interlayer for cooling. The central measurement and control subsystem coordinates the above process through the control cabinet 80 and monitors and records all pressure, temperature, flow parameters, and test blade wall temperature distribution data throughout the process via the data acquisition and conversion card 81 and the computer monitoring console 82. After the test, the high-temperature combustion gas flows sequentially through the exhaust section 50 for initial cooling, then enters the exhaust thermal management subsystem, where it is finally cooled by a water spray device and its pressure is regulated by the exhaust back pressure valve. Finally, it is purified by the tail gas treatment device 71 before being safely discharged. By analyzing the collected data, the cooling effect characteristics of the blade under specific operating conditions can be obtained.

[0041] It should be noted that, in this document, relational terms such as "and" 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.

[0042] 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 test system for the cooling effect of gas turbine blades, characterized in that, include: The main air subsystem is used to provide combustion air; A fuel supply and combustion subsystem, connected to the main air subsystem, is used to mix and burn natural gas, hydrogen, or a mixture thereof with combustion air to generate high-temperature fuel gas. The test section assembly, connected to the fuel supply and combustion subsystem, is used to mount the blade model to be tested and to form a high-temperature gas passage. A cooling air subsystem, separate from the main air subsystem and connected to the test section assembly, is used to provide cooling airflow; An exhaust thermal management subsystem, connected to the test section assembly, is used to cool and purify the high-temperature gas flowing out of the test section; The central measurement and control subsystem is connected to the main air subsystem, the fuel supply and combustion subsystem, the cooling air subsystem, and the exhaust thermal management subsystem, respectively, and is used to coordinate operation, control key parameters, and collect and process test data.

2. The gas turbine blade cooling effect test system according to claim 1, characterized in that: The fuel supply and combustion subsystem includes a fuel supply source (20), a fuel control and ignition device (21), and a burner (22); the fuel supply source (20) provides natural gas, hydrogen, or a mixture thereof; the fuel control and ignition device (21) is used to regulate the fuel flow rate and ratio and perform ignition; the inlet of the burner (22) is connected to the outlet of the fuel control and ignition device (21) and the main air subsystem.

3. The gas turbine blade cooling effect test system according to claim 1, characterized in that: The test section assembly adopts a modular design, including an intake section (30), a test blade test section (40), and an exhaust section (50) that are detachably connected in sequence along the airflow direction; the test blade model (41) is installed inside the test blade test section (40); the test blade test section (40) adopts a double-wall structure.

4. The gas turbine blade cooling effect test system according to claim 3, characterized in that: The surface of the blade model (41) to be tested is provided with thermocouples, and the signal wires of the thermocouples are led out through a preset interface on the cylinder of the test section (40) of the test blade and connected to the central measurement and control subsystem.

5. The gas turbine blade cooling effect test system according to claim 3, characterized in that: Both the intake section (30) and the exhaust section (50) are configured with a double-layer water-cooled structure and are respectively connected to an independent cooling water pump and a circulating water tank.

6. The gas turbine blade cooling effect test system according to claim 5, characterized in that, The cooling pipe of the exhaust section (50) is connected to the inlet of the exhaust thermal management subsystem via a branch. A regulating valve (55) is provided on the branch to regulate the flow rate of cooling water to the exhaust thermal management subsystem.

7. The gas turbine blade cooling effect test system according to claim 1, characterized in that: The cooling air subsystem includes an air compressor (60), a main regulating valve (61), and at least three branch lines; the outlet of the air compressor (60) is split into the at least three branch lines after passing through the main regulating valve (61); each branch line is equipped with a branch flow regulating valve (62), a flow meter (63), a pressure sensor (64), and a temperature sensor (65).

8. The gas turbine blade cooling effect test system according to claim 1, characterized in that: The exhaust thermal management subsystem includes an exhaust pipe (70) and an exhaust gas treatment device (71). The exhaust pipe (70) is equipped with a water spraying device, and the exhaust gas treatment device (71) is connected to the outlet of the exhaust pipe (70).

9. The gas turbine blade cooling effect test system according to claim 8, characterized in that: A temperature sensor (72) is provided at the tail end of the exhaust pipe (70); the signal of the temperature sensor (72) is fed back to the central measurement and control subsystem to adjust the opening of the water supply valve of the spray water device.

10. The gas turbine blade cooling effect test system according to claim 8, characterized in that: The exhaust pipe (70) is also equipped with an exhaust back pressure valve (73) at its tail end, which is used to adjust the system back pressure of the exhaust pipe (70).

11. The gas turbine blade cooling effect test system according to claim 8, characterized in that: The exhaust pipe (70) adopts a segmented design, including an adjustable front pipe section and an axially straight rear pipe section.

12. The gas turbine blade cooling effect test system according to claim 1, characterized in that: The central measurement and control subsystem includes a control cabinet (80), a data acquisition and conversion card (81), and a computer monitoring station (82). The control cabinet (80) is electrically connected to each actuator in the system for centralized control. The data acquisition and conversion card (81) is electrically connected to each sensor and flow meter in the system for acquiring data signals. The computer monitoring station (82) is communicatively connected to the control cabinet (80) and the data acquisition and conversion card (81) for issuing commands, receiving data, and processing data.

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