Device, system and design method for heat transfer test of turbine blade in typical working condition of combustion engine

Abstract

The present application relates to the technical field of turbine blade heat transfer test of gas turbine, and particularly discloses a device, a system and a design method for typical gas turbine working condition turbine blade heat transfer modeling test; wherein the design method is based on the similarity principle, selects the drop ratio, the inlet Mach number or the outlet Mach number and the outlet Reynolds number, determines the air pressure, the single channel air flow and the test blade chord length. The test device comprises a body, a support for supporting the body, and a sliding rail in sliding cooperation with the support and for supporting the support; the body comprises a transition section, a flow adjusting device, a test section and an exhaust section which are sequentially communicated; the support is correspondingly arranged with the transition section, the test section and the exhaust section; the test section is provided with a test blade; the present application can realize the normal temperature modeling test for the heat transfer characteristics of the turbine blade of the gas turbine, reflect the heat transfer characteristics of the turbine blade under the typical working condition of the real gas turbine through the normal temperature test, and realize the low-cost and rapid acquisition of the effective reference data for the design work.

Description

Technical Field

[0001] This invention relates to the field of heat transfer testing technology for gas turbine blades, and more specifically, to an apparatus, system, and design method for heat transfer testing of turbine blades under typical gas turbine operating conditions. Background Technology

[0002] In the design of gas turbine blades, highly reliable data from experimental measurements are needed as a reference for cooling design. While conducting tests on a stage test rig with a full ring of blades under high temperature and pressure can obtain data closest to real-world operating conditions, it also carries numerous risks, including safety hazards, high costs, and long testing cycles. Therefore, most engineering studies extract a portion of the blades from the full ring, presenting them as fan-shaped or simplified planar blade cascades, and conduct tests on the heat transfer characteristics of the turbine blades at room temperature based on similarity criteria.

[0003] Compared to high-temperature testing, room-temperature blade cascade testing can simulate the heat transfer characteristics of turbine blades under typical gas turbine operating conditions at room temperature under safe, cost-effective, and cycle-controllable conditions, using similarity theory to obtain highly reliable reference data. This is a sufficient condition to ensure that the test data can be used for design.

[0004] The existing room-temperature blade cascade test equipment or schemes mainly have the following problems:

[0005] In the design, calculation, and construction of existing ambient temperature turbine blade test devices, most of them fail to simultaneously meet the requirements of the main dimensionless criteria (pressure ratio, inlet and outlet Reynolds number, inlet and outlet Mach number) and the actual operating conditions of turbine blades. They also fail to consider the calculation approach and process for the test conditions that meet the similarity requirements. As a result, the test conditions are far from the actual operating conditions of gas turbines. The obtained test data cannot reflect the heat transfer characteristics of turbine blades under actual operating conditions and cannot be used as a valid reference for design work.

[0006] To obtain comprehensive and high-quality heat transfer characteristic data of turbine blades (such as turbulence intensity, velocity distribution, total static pressure, airflow and wall temperature, heat transfer coefficient, film cooling efficiency, and overall cooling efficiency), it is necessary to select the most suitable measurement method (such as probe, thermocouple, infrared thermal imager, etc.) based on specific measurement requirements. Most existing solutions do not consider the requirements of different measurement methods on gas source conditions (such as nitrogen secondary flow, where both main and secondary flows are heated) or measurement equipment (such as the need for infrared glass or optical glass), thus limiting their applicability.

[0007] In real-world environments, the heat transfer characteristics of turbine blades are influenced by numerous complex factors, such as high turbulence at the combustion chamber outlet, combustion chamber swirl, upstream blade wakes and slit jets, and interference between upstream blades and shock waves. In existing designs, the relative positions of most components (stabilization section, contraction section, test section, etc.) on the test rig are essentially fixed, making it difficult to select different inflow control devices (such as mainstream heaters, turbulence grids, swirl simulators, wake simulators, etc.) to change the inflow conditions and simulate the complex and variable influencing factors in real gas turbines, thus limiting scalability. Summary of the Invention

[0008] The technical problem to be solved by the present invention is to provide an apparatus, system and design method for a turbine blade heat transfer modeling test that reproduces typical gas turbine operating conditions at room temperature. Under the condition that the main dimensionless criterion numbers are similar to the actual operating conditions, a room temperature modeling test is carried out on the heat transfer characteristics of the gas turbine blade. The actual gas turbine operating conditions are simulated at room temperature to obtain the heat transfer characteristics of the turbine blade, thereby achieving low-cost and rapid acquisition of effective reference data for design work.

[0009] The solution adopted by this invention to solve the technical problem is:

[0010] on the one hand:

[0011] A design method for a typical gas turbine blade heat transfer test device is proposed. Based on the similarity principle, the drop ratio, inlet Mach number or outlet Mach number and outlet Reynolds number are selected, and the air pressure, single-channel air flow rate and test blade chord length are determined.

[0012] In some possible implementations, the specific steps include:

[0013] Step S1: Assuming the outlet pressure or inlet pressure, calculate the inlet pressure or outlet pressure based on the pressure drop ratio;

[0014] Step S2: Calculate the outlet temperature based on the outlet pressure, inlet pressure, and inlet temperature;

[0015] Step S3: Calculate the exit sound speed and, in conjunction with the exit Mach number, calculate the exit airflow velocity;

[0016] Step S4: Obtain the outlet air viscosity coefficient and outlet air density based on the outlet pressure and outlet temperature;

[0017] Step S5: Calculate the chord length of the test blade based on the outlet Reynolds number, outlet airflow velocity, and outlet air viscosity coefficient; and obtain the geometric scaling ratio compared to a real turbine blade.

[0018] Step S5: Calculate the airflow rate of a single channel based on the outlet cross-sectional area, geometric scaling ratio, outlet airflow velocity, and outlet air density.

[0019] In some possible implementations, step S2 specifically refers to:

[0020] Calculate the outlet temperature using the isentropic flow relationship;

[0021]

[0022] Among them, T out For the outlet temperature, T in For the inlet temperature, Ma in Ma is the entry Mach number. out Here, k is the export Mach number, and k is the specific heat ratio.

[0023] In some possible implementations, step S6 correction is also included, comprising the following steps:

[0024] Step S61: Calculate the inlet sound velocity and, in conjunction with the inlet Mach number, calculate the outlet airflow velocity;

[0025] Step S61: Obtain the inlet air viscosity coefficient and inlet air density based on the inlet pressure and inlet temperature;

[0026] Step S62: Calculate the inlet Reynolds number based on the chord length of the test blade, the inlet air velocity, and the inlet air viscosity coefficient.

[0027] on the other hand:

[0028] A typical gas turbine blade heat transfer test device, based on the design method described above, includes a main body, a support for supporting the main body, and a slide rail that slides with the support and supports the support.

[0029] The main body includes a transition section, an incoming flow regulating device, a test section, and an exhaust section connected in sequence; test blades are installed in the test section; the support is set in a one-to-one correspondence with the transition section, the test section, and the exhaust section.

[0030] In some possible implementations, an observation window and a measuring groove are provided on the test section, the measuring groove being located on the outlet side of the test section; a single-point contact measuring device that slides in conjunction with the sliding length direction of the measuring groove is installed in the measuring groove.

[0031] The length direction of the sliding length of the measuring groove is not parallel to the gas flow direction of the test section.

[0032] In some possible implementations, the test blades are in N groups and form N+1 channels with the same structural dimensions.

[0033] In some possible implementations, the incoming flow regulating device is any one of a heater, a turbulence grid, a vortex simulator, or a wake simulator.

[0034] In some possible implementations, a quartz glass or infrared glass is provided on the observation window; a camera or thermal imager is provided outside the observation window.

[0035] Finally:

[0036] A system for a typical gas turbine blade heat transfer test under operating conditions includes the device described above, a main flow gas supply system connected to the incoming flow regulating device, and a secondary flow gas supply system connected to the main flow gas supply system and the test section respectively.

[0037] The main gas supply system includes a main supply pipeline connected at one end to an air source and at the other end to a turbine blade test device, a main valve and a main flow meter arranged along the gas flow direction and installed on the main supply pipeline, and an airflow bypass arranged on the main supply pipeline and located at the end of the main valve away from the main flow meter; a bypass valve is provided on the airflow bypass.

[0038] The secondary flow gas supply system includes a secondary flow pipe connected to the main supply pipe and located between the gas flow bypass and the main valve, an air secondary flow valve installed on the secondary flow pipe, a secondary flow heater connected to the other end of the secondary flow pipe, a buffer tank connected to the other end of the secondary flow heater, and multiple sets of connecting pipes for connecting the buffer tank and the test section.

[0039] A nitrogen secondary flow valve, a secondary flow meter, and an electrically controlled tee are sequentially installed on each of the connecting pipes along the airflow direction.

[0040] The secondary flow heater is connected to a secondary flow path that is connected to a nitrogen source, and a secondary flow regulating valve is provided on the secondary flow path.

[0041] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0042] The design method of this invention ensures that the main dimensionless criterion numbers are similar to those of real operating conditions, and reflects the heat transfer characteristics of turbine blades under typical operating conditions of real gas turbines through room temperature tests.

[0043] The experimental apparatus of this invention fully considers the needs of various measurement methods and can flexibly select appropriate measurement methods to obtain comprehensive heat transfer characteristics of different parts of turbine blades.

[0044] The present invention is connected to a slide rail fixed on the ground by a bracket, and the relative distance between the parts can be changed to install flow adjustment devices of different sizes and lengths, or to change the flow conditions, or to simulate the flow environment of a real turbine.

[0045] The design method in this invention ensures that the main dimensionless criterion numbers are similar at the same time, simulates the typical operating conditions of a real gas turbine at room temperature, and obtains the heat transfer characteristics of turbine blades. It provides effective reference data that can be used for design work in a low-cost and rapid manner.

[0046] The design method of this invention calculates and obtains multiple combinations of modeling parameters based on the specific inlet and outlet pressure conditions of the test environment, and selects the optimal one.

[0047] The experimental device in this invention can select the most appropriate measurement method according to the measurement location and measurement characteristics, and obtain detailed heat transfer characteristic data of each part of the turbine blade in a comprehensive and accurate manner, thus fully supporting the design work of the turbine blade.

[0048] In this invention, the experimental setup is equipped with different inflow regulation devices to simulate the influence of upstream components and inflow conditions of the turbine under real gas turbine operating conditions, so that the room temperature model test data can be further close to the real inflow conditions of the turbine blades. By using and combining different inflow regulation devices, the interaction between different components and multiple factors and their influence on the heat transfer characteristics of the turbine can be studied. Attached Figure Description

[0049] Figure 1 This is a flowchart illustrating the design method in this invention.

[0050] Figure 2 This is a schematic diagram of the experimental device in this invention;

[0051] Figure 3 This is a schematic diagram of the connection relationship of the test system in this invention;

[0052] Among them: 1-Main gas supply system, 11-Main supply pipeline, 12-Main valve, 13-Main flow meter, 14-Bypass valve, 2-Turbine blade test device, 21-Transition section, 22-Incoming flow regulating device, 23-Test section, 231-Test blade, 232-Observation window, 233-Measuring groove, 24-Exhaust section, 25-Support, 26-Slide rail, 3-Secondary flow gas supply system, 31-Secondary flow pipeline, 32-Secondary flow heater, 33-Buffer tank, 34-Air secondary flow valve, 35-Nitrogen secondary flow valve, 36-Secondary flow regulating valve, 37-Secondary flow meter, 38-Electrically controlled tee. Detailed Implementation

[0053] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. The terms "first," "second," and similar terms used in this application do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Similarly, "a" or "one," etc., do not indicate a quantity limitation, but rather indicate the existence of at least one. In the implementation of this application, "and / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. In the description of the embodiments of this application, unless otherwise stated, "multiple" means two or more. For example, multiple positioning posts refer to two or more positioning posts. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0054] The present invention will now be described in detail.

[0055] Example 1:

[0056] like Figure 1 As shown, a design method for a typical gas turbine blade heat transfer test device is presented. Based on the similarity principle, the drop ratio, inlet Mach number or outlet Mach number and outlet Reynolds number are selected, and the air pressure, single-channel air flow rate and chord length of the test blade 231 are determined.

[0057] In some possible implementations, the specific steps include:

[0058] Step S1: Assuming the outlet pressure or inlet pressure, calculate the inlet pressure or outlet pressure based on the pressure drop ratio;

[0059] For example: assuming the outlet pressure, calculate the inlet pressure based on the pressure drop ratio;

[0060] Alternatively, assuming the inlet pressure, calculate the outlet pressure based on the pressure drop ratio;

[0061] Step S2: Calculate the outlet temperature based on the outlet pressure, inlet pressure, and inlet temperature; where the inlet temperature is a known parameter based on the air source parameters.

[0062] Calculate the outlet temperature using the isentropic flow relationship;

[0063]

[0064] Among them, T out For the outlet temperature, Tin For inlet temperature, Ma in Ma is the entry Mach number. out Here, k is the export Mach number, and k is the specific heat ratio.

[0065] Step S3: Calculate the exit sound speed and, in conjunction with the exit Mach number, calculate the exit airflow velocity; where the exit Mach number is a known parameter based on the actual turbine design conditions.

[0066] Step S4: Obtain the outlet air viscosity coefficient and outlet air density by referring to the table based on the outlet pressure and outlet temperature;

[0067] Step S5: Calculate the 231 chord length of the test blade based on the outlet Reynolds number, outlet airflow velocity, and outlet air viscosity coefficient; and obtain the geometric scaling ratio compared to the real turbine blade; wherein, the outlet Reynolds number is a known parameter based on the real turbine design conditions;

[0068] Step S5: Calculate the airflow rate of a single channel based on the outlet cross-sectional area, geometric scaling ratio, outlet airflow velocity, and outlet air density; the outlet cross-sectional area is a known parameter based on the actual turbine design conditions.

[0069] It also includes step S6 correction; which includes the following steps:

[0070] Step S61: Calculate the inlet sound velocity and, in conjunction with the inlet Mach number, calculate the outlet airflow velocity; wherein, the inlet Mach number is a known parameter based on the actual turbine design conditions;

[0071] Step S61: Obtain the inlet air viscosity coefficient and inlet air density based on the inlet pressure and inlet temperature;

[0072] Step S62: Calculate the inlet Reynolds number based on the chord length of the test blade 231, the inlet air velocity, and the inlet air viscosity coefficient. The obtained inlet Reynolds number is used as a reference for the analysis of test data.

[0073] In step S1, different inlet / outlet pressures of the blade cascade can be selected to obtain different design schemes under the condition that the dimensionless criterion numbers are similar. The scheme adopted in this invention is determined under the assumption that the outlet pressure of the blade cascade is atmospheric pressure. However, the optimal one can be selected according to the specific test conditions.

[0074] This invention selects appropriate dimensionless criterion numbers, conducts a comprehensive and detailed analysis and design calculation process, and, based on the principle of similarity, ensures that the room temperature turbine blade cascade test can accurately reflect the flow characteristics in the turbine blade cascade under real operating conditions.

[0075] Example 2:

[0076] like Figure 2As shown, a typical gas turbine blade heat transfer test device is used for turbine blade heat transfer model test. Based on the design method of the above embodiment 1, it includes a body, a support 25 for supporting the body, and a slide rail 26 that slides with the support 25 and supports the support 25.

[0077] The main body includes a transition section 21, an incoming flow regulating device 22, a test section 23, and an exhaust section 24 connected in sequence; a test blade 231 is installed in the test section 23. The bracket 25 is arranged in a one-to-one correspondence with the transition section 21, the test section 23, and the exhaust section 24;

[0078] The transition section 21, test section 23, and exhaust section 24 are respectively slidably engaged with the slide rail 26 through the corresponding brackets 25; thereby changing the distance between the transition section 21 and the test section 23, and thus enabling connection with different incoming flow adjustment devices 22;

[0079] The incoming flow regulating device 22 can be any one of a heater, a turbulence grid, a swirl simulator, or a wake simulator. The incoming flow regulating device 22 can be used to carry out corresponding tests according to specific test requirements, either by changing the incoming flow conditions or by simulating the flow characteristics and influencing factors generated by different components.

[0080] When the incoming flow regulating device 22 is a heater, it can heat the main flow to meet the requirements of the heat transfer test for the temperature difference between the main flow and the secondary flow;

[0081] When the incoming flow regulating device 22 is a turbulence grid, it can effectively increase the turbulence of the main flow to deal with the strong disturbance caused by the flow, simulating the high turbulence incoming flow environment of the turbine blade under real working conditions.

[0082] When the incoming flow regulating device 22 is a swirl simulator, it can simulate the flow characteristics induced by the swirl in the dry low-NOx combustion chamber widely used in real gas turbines.

[0083] When the incoming flow regulating device 22 is a wake simulator, it can simulate the effects of the wake caused by the upstream blades, the trailing edge film jet, and the interference between the shock wave in the blade cascade channel and the upstream blades under the real turbine multi-row blade structure.

[0084] This invention can effectively enable the flexible selection of different incoming flow adjustment devices 22 to meet different research needs, and simulate the influence of upstream components and other complex factors (such as high turbulence, combustion chamber swirl, upstream blade wake and slit jet, shock wave interference, etc.) on the heat transfer characteristics of turbine blades under real gas turbine environment.

[0085] In some possible implementations, an observation window 232 and a measuring groove 233 are provided on the test section 23, the measuring groove 233 being located on the outlet side of the test section 23; a single-point contact measuring device is installed in the measuring groove 233, which slides in conjunction with the measuring groove 233 in the sliding length direction; the length direction of the measuring groove 233 in the sliding length direction is not parallel to the gas flow direction of the test section 23.

[0086] Different single-point contact measuring devices, such as probes, hot-wire anemometers, and thermocouples, can be installed in the measuring slot 233 to perform single-point contact measurements and move along the length of the measuring slot 233 to carry out measurements at different positions.

[0087] When in use, the probe of the single-point contact measuring device extends into the test section 23 to measure airflow temperature and pressure, pulsation velocity, turbulence intensity, blade temperature, etc.

[0088] The observation window 232 can be fitted with quartz optical glass or infrared optical glass to meet the needs of different visualization non-contact measurement methods, such as pressure-sensitive, temperature-sensitive paint, thermochromic liquid crystal, and infrared thermal imager.

[0089] The setting of observation window 232 and measuring tank 233 allows for the selection of the most suitable method from various heat fluid measurement techniques to conduct corresponding experiments.

[0090] This invention can effectively obtain comprehensive heat transfer characteristic data of turbine blades under typical gas turbine operating conditions (such as turbulence intensity, velocity distribution, total static pressure, airflow and wall temperature, heat transfer coefficient, film cooling efficiency, overall cooling efficiency, etc.). It requires selecting the most suitable measurement method according to specific measurement needs; it meets the measurement requirements of various room temperature heat fluid measurement methods, and specifically obtains comprehensive and high-quality heat transfer characteristic data of different regions of turbine blades to support design work.

[0091] In some possible implementations, the test blades 231 are N groups, forming N+1 channels of the same structural shape and size.

[0092] Furthermore, a horizontally rotatable adjustment plate is provided on the side of the test section 23 near the exhaust section 24, and its position can be adjusted according to the actual situation to ensure the periodicity of flow in multiple channels.

[0093] Finally:

[0094] like Figure 2 , Figure 3As shown, a typical gas turbine blade heat transfer test system includes a turbine blade test device 2 as described in Example 2, a main flow gas supply system 1 connected to the incoming flow regulating device 22, and a secondary flow gas supply system 3 connected to the main flow gas supply system 1 and the test section 23 respectively.

[0095] The main gas supply system 1 includes a main supply pipeline 11 connected at one end to an air source and at the other end to a turbine blade test device 2, a main valve 12 arranged along the gas flow direction and arranged on the main supply pipeline 11, a main flow meter 13, and an airflow bypass arranged on the main supply pipeline 11 and located at the end of the main valve 12 away from the main flow meter 13; a bypass valve 14 is arranged on the airflow bypass.

[0096] Furthermore, the air source is connected to the end of the transition section 21 in the turbine blade test device 2 away from the incoming flow regulating device 22 via the main supply pipe 11.

[0097] The secondary flow gas supply system 3 includes a secondary flow pipe 31 connected to the main supply pipe 11 and located between the airflow bypass and the main valve 12, an air secondary flow valve 34 installed on the secondary flow pipe 31, a secondary flow heater 32 connected to the other end of the secondary flow pipe 31, a buffer tank 33 connected to the other end of the secondary flow heater 32, and multiple sets of connecting pipes for connecting the buffer tank 33 and the test section 23.

[0098] A nitrogen secondary flow valve 35, a secondary flow meter 37, and an electrically controlled tee 38 are sequentially installed on each of the connecting pipes along the airflow direction.

[0099] The secondary flow heater 32 is connected to a secondary flow path that is connected to a nitrogen source, and a secondary flow regulating valve 36 is provided on the secondary flow path.

[0100] Most of the air from the high-pressure air source is supplied to the turbine blade test device 2 through the mainstream gas supply system 1. The flow rate and pressure of the mainstream air are jointly controlled by the main valve 12, the bypass valve 14 and the exhaust valve located in the exhaust section 24 of the turbine blade test device 2. Excess air is discharged to the atmosphere through the airflow bypass.

[0101] Part of the air from the air source enters the secondary flow gas supply system 3 through the secondary flow air valve 34; in addition to air, the secondary flow gas supply system 3 also includes a nitrogen source.

[0102] Secondary flow air or nitrogen flows through the corresponding secondary flow valve and then sequentially through the secondary flow heater 32 and the buffer tank 33. After the buffer tank 33, it can be divided into multiple groups to simulate the cooling air of different parts of the test blade 231. The flow rate of each group of cooling air can be controlled individually by the secondary flow regulating valve 36 and the secondary flow meter 37.

[0103] The electrically controlled tee 38 can quickly close or open the corresponding secondary flow path to meet the needs of rapid changes in the secondary flow state during transient test measurement.

[0104] The measuring devices installed on the observation window 232 or the measuring tank 233 can also be selected from a variety of different thermal fluid measurement methods and means to carry out corresponding tests according to specific test requirements; the gas flowing into the test device (including mainstream air and secondary flow gas) is discharged into the atmosphere after passing through the exhaust section 24 downstream of the test device.

[0105] For pressure-sensitive paint measurement technology: pressure-sensitive paint is sprayed onto the surface of the test blade 231; the mainstream gas is air, and the secondary gas is nitrogen or other oxygen-free gas. By adjusting the power of the secondary gas heater 32, the temperature of the mainstream gas and the secondary gas is the same; the observation window 232 is made of quartz glass, and the signal emitted by the pressure-sensitive paint is recorded by a camera, which can measure the pressure distribution and film cooling efficiency on the surface of the turbine blade.

[0106] For temperature-sensitive paint or thermochromic liquid crystal measurement technology: Temperature-sensitive paint or thermochromic liquid crystal is sprayed onto the surface of the test blade 231; the main gas is air, and the secondary gas can be air or other gases to obtain different density conditions. According to the test requirements, the incoming flow adjustment device 22 is set as a heater, and the power of the heater and the secondary flow heater 32 are adjusted respectively to obtain different test gas flow temperature conditions; the observation window 232 is made of quartz glass. The signal from the temperature-sensitive paint or thermochromic liquid crystal is recorded by a camera, thereby measuring the surface temperature of the turbine blade, which can be used to calculate the convective heat transfer coefficient, film cooling efficiency, or overall cooling efficiency.

[0107] For infrared thermal imaging measurement technology: The surface of the test blade 231 is coated with black matte paint to improve emissivity. The main gas is air, and the secondary gas can be air or other gases to obtain different density conditions. According to the test requirements, the incoming flow regulating device 22 is set as a heater, and different test temperature conditions are obtained through the power of this heater and the secondary flow heater 32. The observation window 232 is infrared glass, such as germanium glass or zinc selenide glass. The infrared radiation emitted by the surface of the test blade 231 is recorded by the thermal imager, thereby measuring the surface temperature of the turbine blade, which can be used to calculate the convective heat transfer coefficient, film cooling efficiency, or overall cooling efficiency.

[0108] This invention is not limited to the specific embodiments described above. The invention extends to any new feature or combination disclosed in this specification, as well as any new method or process step or combination disclosed herein.

Claims

1. A design method for an apparatus for a typical gas turbine blade heat transfer test, characterized in that, Based on the principle of similarity, the pressure ratio, inlet Mach number or outlet Mach number and outlet Reynolds number are selected to determine the air pressure, single-channel air flow rate, and test blade chord length. Specifically, the following steps are included: Step S1: Assuming the outlet pressure or inlet pressure, calculate the inlet pressure or outlet pressure based on the pressure drop ratio; Step S2: Calculate the outlet temperature based on the outlet pressure, inlet pressure, and inlet temperature; Step S3: Calculate the exit sound speed and, in conjunction with the exit Mach number, calculate the exit airflow velocity; Step S4: Obtain the outlet air viscosity coefficient and outlet air density based on the outlet pressure and outlet temperature; Step S5: Calculate the chord length of the test blade based on the outlet Reynolds number, outlet airflow velocity, and outlet air viscosity coefficient; and obtain the geometric scaling ratio compared to a real turbine blade. Step S5: Calculate the airflow rate of a single channel based on the outlet cross-sectional area, geometric scaling ratio, outlet airflow velocity, and outlet air density.

2. The design method of the apparatus for a typical gas turbine blade heat transfer test according to claim 1, characterized in that, Step S2 specifically refers to: Calculate the outlet temperature using the isentropic flow relationship; ; in, For the outlet temperature, Inlet temperature, The Mach number at the entrance. Here, k is the export Mach number, and k is the specific heat ratio.

3. The design method of the apparatus for a typical gas turbine blade heat transfer test according to claim 2, characterized in that, It also includes step S6 correction; which includes the following steps: Step S61: Calculate the inlet sound velocity and, in conjunction with the inlet Mach number, calculate the outlet airflow velocity; Step S61: Obtain the inlet air viscosity coefficient and inlet air density based on the inlet pressure and inlet temperature; Step S62: Calculate the inlet Reynolds number based on the chord length of the test blade, the inlet air velocity, and the inlet air viscosity coefficient.

4. An apparatus for testing the heat transfer of turbine blades under typical gas turbine operating conditions, characterized in that, The design method based on any one of claims 1-3 includes a body, a bracket for supporting the body, and a slide rail that slides with the bracket and supports the bracket. The main body includes a transition section, an incoming flow regulating device, a test section, and an exhaust section connected in sequence; test blades are installed in the test section; the support is set in a one-to-one correspondence with the transition section, the test section, and the exhaust section.

5. The apparatus for a typical gas turbine blade heat transfer test under operating conditions according to claim 4, characterized in that, An observation window and a measuring groove are provided on the test section, and the measuring groove is located on the outlet side of the test section; a single-point contact measuring device that slides in conjunction with the sliding length direction of the measuring groove is installed in the measuring groove. The length direction of the sliding length of the measuring groove is not parallel to the gas flow direction of the test section.

6. The apparatus for a typical gas turbine blade heat transfer test under operating conditions according to claim 4, characterized in that, The test blades consist of N groups, forming N+1 channels with the same structural dimensions.

7. The apparatus for a typical gas turbine blade heat transfer test under operating conditions according to claim 4, characterized in that, The incoming flow regulating device is any one of a heater, a turbulence grid, a vortex simulator, or a wake simulator.

8. The apparatus for heat transfer testing of turbine blades under typical gas turbine operating conditions according to claim 5, characterized in that, The observation window is fitted with quartz glass or infrared glass; a camera or thermal imager is installed outside the observation window.

9. A system for testing the heat transfer of turbine blades under typical gas turbine operating conditions, characterized in that, Includes the apparatus as described in any one of claims 4-8, a main flow gas supply system connected to the incoming flow regulating device, and a secondary flow gas supply system connected to both the main flow gas supply system and the interior of the test section; The main gas supply system includes a main supply pipeline connected at one end to an air source and at the other end to a turbine blade test device, a main valve and a main flow meter arranged along the gas flow direction and installed on the main supply pipeline, and an airflow bypass arranged on the main supply pipeline and located at the end of the main valve away from the main flow meter; a bypass valve is provided on the airflow bypass. The secondary flow gas supply system includes a secondary flow pipe connected to the main supply pipe and located between the gas flow bypass and the main valve, an air secondary flow valve installed on the secondary flow pipe, a secondary flow heater connected to the other end of the secondary flow pipe, a buffer tank connected to the other end of the secondary flow heater, and multiple sets of connecting pipes for connecting the buffer tank and the test section. A nitrogen secondary flow valve, a secondary flow meter, and an electrically controlled tee are sequentially installed on each of the connecting pipes along the airflow direction. The secondary flow heater is connected to a secondary flow path that is connected to a nitrogen source, and a secondary flow regulating valve is provided on the secondary flow path.

Images