Double-station turbine blade thermal shock test device and test method thereof

Abstract

The invention relates to a double-station turbine blade thermal shock test device and a test method thereof, and the device comprises a flame gas heating system which is used for generating high-temperature flame through gas combustion to simulate transient thermal shock when an aero-engine is started; the double-station pushing platform comprises a frame, a front testing station and two rear independent testing stations, wherein the front testing station and the two rear independent testing stations are installed on the frame. The airflow cooling system is used for quickly cooling the high-temperature test piece; the infrared temperature measuring device is used for detecting the surface temperature of the blade in real time and feeding back the surface temperature to the flame gas heating system to realize closed-loop temperature control; the image acquisition device is used for acquiring appearance characteristic data of cracks on the surface of the blade in the test process; and a base. Compared with the prior art, the device has the advantages that the device has remarkable advantages in the aspects of test function integrity, working condition simulation accuracy, test efficiency and the like, and comprehensive test support can be provided for research and development of aero-engine hot end components.

Description

Technical Field

[0001] The invention relates to a dual-station turbine blade thermal shock test device and a test method thereof, belonging to the technical field of aviation engine component testing. Background Art

[0002] In modern aero-engine technology, turbine blades, as core hot-end components, are crucial for overall engine performance and service life. With turbine inlet temperatures exceeding 2200K in new-generation aero-engines, the thermal loads on blade materials are approaching their melting point. In actual service, turbine blades are subject to extreme thermal shock conditions. During engine startup, the blade surface temperature can surge from room temperature to 1700°C in 3-5 seconds. In extreme situations, such as emergency shutdown, the cooling rate can exceed 1500°C / min. These drastic temperature transients can generate transient thermal stresses up to 800 MPa within the blades, leading to typical thermal shock fatigue damage such as thermal barrier coating delamination and microcrack initiation. Turbine blade thermal shock testing equipment, through precisely controlled temperature cycling and thermal stress loading, accurately simulates the extreme temperature transients experienced in actual aero-engine operation, enabling scientific evaluation of the high-temperature strength properties and service life of blade coating systems. It has become a key technical tool for evaluating the mechanical properties of thermal barrier coatings and high-temperature composite materials, and optimizing structural design.

[0003] Currently, most existing turbine blade thermal shock test equipment is a single-station design that can only test one blade at a time, resulting in low test efficiency and difficulty in ensuring comparative analysis of different blades under the same thermal load conditions. In addition, existing equipment has deficiencies in temperature control accuracy, cooling medium uniformity, and automation. For example: (1) Heating methods are limited. Some test benches use resistance furnaces for heating, which have a slow heating rate (usually <100°C / min) and are difficult to simulate the actual engine operating conditions; (2) Cooling uniformity is poor. Traditional spray cooling can easily lead to local overcooling or insufficient cooling of the blade, affecting data reliability; (3) Data comparability is low. When multiple tests are performed at a single station, fluctuations in environmental parameters can lead to a large dispersion of test results. Summary of the Invention

[0004] To address the problems of existing single-station thermal shock testing equipment for turbine blades, such as low efficiency, insufficient thermal load control accuracy, and poor data comparability, this invention provides a dual-station thermal shock testing equipment for turbine blades. This equipment utilizes a dual-station design, combined with flame gas heating, gas cooling, and control technology, to simultaneously conduct thermal shock fatigue tests on two specimens, significantly improving test efficiency and data reliability.

[0005] In order to overcome the defects of the prior art, the present invention provides a dual-station turbine blade thermal shock test device. The technical solution of the present invention is:

[0006] A dual-station turbine blade thermal shock test device and test method thereof, comprising:

[0007] A flame gas heating system (1) is used to generate a high-temperature flame by burning gas to simulate the transient thermal shock during the start-up of an aircraft engine;

[0008] A dual-station pushing platform (2) comprises a frame, a front test station (203) and two rear independent test stations (207) mounted on the frame, wherein the front test station (203) is used to perform high-temperature heating on a blade test piece, and the rear test station is used to perform cooling on the blade test piece; the front test station (203) and the two rear independent test stations (207) are linked and controlled by a synchronization unit;

[0009] An air flow cooling system (3) is used to quickly cool down the high-temperature test piece, and a pure gas source is provided by a high-pressure nitrogen bottle and a mass flow controller is used to adjust the flow rate;

[0010] An infrared temperature measuring device (4) is used to detect the blade surface temperature in real time and feed it back to the flame gas heating system (1) to achieve closed-loop temperature control;

[0011] An image acquisition device (5) is used to acquire crack morphology characteristic data on the blade surface during the test;

[0012] The base (6), the flame gas heating system (1), the double-station pushing platform (2), the air flow cooling system (3), the infrared temperature measuring device (4) and the image acquisition device (5) are all installed on the base (6) and connected to the control box.

[0013] The flame gas heating system (1) includes a flame spray gun (101), a flame spray gun mounting bracket (102), a vertical lifting platform (103), a vertical lifting platform mounting seat (104) and an electric horizontal slide (105), wherein the vertical lifting platform mounting seat (104) is slidably mounted on the electric horizontal slide (105) and driven by the electric horizontal slide (105); the vertical lifting platform (103) is mounted on the upper part of the vertical lifting platform mounting seat (104), and the flame spray gun (101) is mounted on the vertical lifting platform (103) through the flame spray gun mounting bracket (102), the vertical lifting platform (103) is used to adjust the vertical height of the flame spray gun (101), and the electric horizontal slide (105) is used to adjust the horizontal distance of the flame spray gun (101) to achieve precise ablation of the blade test piece by the flame.

[0014] The front test station (203) comprises a front test top plate, a test blade (201), a front blade clamping tool (202), a linear bearing (204) and a support platform (214), wherein the support platform (214) is mounted on the frame and forms a gap with the bottom of the frame; a plurality of lifting columns are provided at the bottom of the front test top plate, each of the lifting columns is slidably matched with the support platform (214) through a linear bearing (204); the support platform (214) is driven by a lifting drive unit; a front blade clamping tool (202) is mounted on the front test top plate, the upper part of the front blade clamping tool (202) is fixedly mounted with the front test blade (210) by screws, and the lower part is mounted on the front test top plate by bolts; the bottom of the support platform (214) is slidably mounted on a support platform linear guide rail (213).

[0015] The lifting drive unit comprises a mounting bracket (215), a cam bearing follower (218), a guide plate and a guide groove (209); a mounting bracket (215) arranged in a vertical direction is also installed at the bottom of the front test top plate; the lower end of the mounting bracket (215) passes through the support platform (214) and is then installed with a cam bearing follower (218); the guide plate is installed on the frame, and a V-shaped guide groove is provided along the length direction of the frame, and the cam bearing follower (218) is rollingly installed in the V-shaped guide groove.

[0016] The rear test station (207) comprises a rear test top plate, a rear blade clamping tool (206), a rear test blade (205), a rodless cylinder (211), a T-shaped mounting frame (212) and a test station linear guide rail (210); the test station linear guide rail (210) is mounted on the frame, and the rear test top plate is slidably mounted on the test station linear guide rail (210); the rodless cylinder (211) is mounted on the outside of the frame, and the sliding part of the rodless cylinder (211) is connected to the rear test top plate through the T-shaped mounting frame (212), driving the rear test top plate to move forward, backward and stay; the rear blade clamping tool (206) is mounted on the rear test top plate, the upper part of the rear blade clamping tool (206) is fixedly mounted with the rear test blade (205) by screws, and the lower part is mounted on the rear test top plate by bolts.

[0017] The synchronization unit includes a synchronization belt (208), an upper connecting piece (217), a lower connecting piece (216) and a synchronization pulley. Several synchronization pulleys are installed on the inner wall of the frame. The synchronization belt (208) passes through all the synchronization pulleys in sequence. The upper part of the synchronization belt is connected to the rear test top plate through the upper connecting piece (217); the lower part of the synchronization belt is connected to the support platform (214) through the lower connecting piece (216).

[0018] The cooling medium of the airflow cooling system (3) is high-pressure nitrogen, and the cooling rate is precisely controlled by a mass flow controller, so that the cooling airflow evenly covers the blade surface.

[0019] The image acquisition device (5) is a high-speed camera or a microscopic imaging system, which is used to capture the initiation and expansion process of cracks on the blade surface in real time and record the crack length and morphological characteristics.

[0020] A test method based on the dual-station turbine blade thermal shock test device comprises the following steps:

[0021] S1. Sample clamping: The first test blade (201) is mounted on the front blade clamping fixture (202) of the front test station (203), and the second test blade (205) is mounted on the rear blade clamping fixture (206) of the rear test station (207);

[0022] S2. Initial positioning: adjusting the horizontal position of the flame spray gun (101) by the electric horizontal slide (105), and adjusting the vertical height of the flame spray gun (101) by the vertical lift (103) so that it is aligned with the first test blade (201) on the front test station (203);

[0023] S3. Heating stage: The flame gas heating system (1) is started to transiently heat the first test blade (201) by generating a high-temperature flame through gas combustion. At the same time, the surface temperature of the blade is monitored in real time using an infrared temperature measuring device (4), and the temperature data is fed back to the flame gas heating system (1), forming a closed-loop control to accurately achieve the target temperature;

[0024] S4. Synchronous switching of workstations: When the first test blade (201) reaches the preset temperature, the double-workstation pushing platform (2) is controlled by the synchronization unit, driving the rodless cylinder (211) to drive the rear test station (207) to move forward along the test station linear guide rail (210), and at the same time, the front test station (203) is pulled backward along the support platform linear guide rail (213) by the synchronous belt (208), so that the first test blade (201) enters the cooling area and the second test blade (205) enters the heating area;

[0025] S5. Cooling stage: Start the airflow cooling system (3), adjust the flow rate of high-pressure nitrogen through the mass flow controller, and uniformly and quickly cool the first test blade (201), while repeating step S3 to heat the second test blade (205);

[0026] S6. Data acquisition: During the heating and cooling process, the crack initiation and propagation process on the surface of the first test blade (201) and the second test blade (205) is captured in real time by the image acquisition device (5), and the crack length and morphological characteristics are recorded;

[0027] S7. Cyclic test: Repeat steps S3 to S6, alternating heating and cooling of the test blades on the double station until the preset number of thermal shock cycles is completed;

[0028] S8. Result analysis: Based on the temperature data from the infrared temperature measuring device (4) and the crack characteristic data from the image acquisition device (5), the thermal shock fatigue resistance of the blade material is evaluated.

[0029] The linkage control of the synchronization unit is specifically as follows:

[0030] When the rodless cylinder (211) drives the rear test station (207) to move forward along the linear guide rail (210), the rear test top plate of the rear test station (207) is driven to move via the T-shaped mounting bracket (212);

[0031] The synchronous belt (208) is connected to the rear test top plate of the rear test station (207) through the upper connecting member (217) and is connected to the support platform (214) through the lower connecting member (216), so that the front test station (203) and the rear test station (207) move synchronously in opposite directions;

[0032] During the movement, the cam bearing follower (218) slides along the V-shaped guide groove (209), driving the front test station (203) to move vertically up and down, ensuring that the center distance between the front test station and the rear test station is 660±5mm and the vertical spacing is 120±1mm.

[0033] The advantages of this invention include: a unique dual-station design that allows simultaneous thermal shock fatigue testing of two specimens, significantly improving testing efficiency and data reliability. Furthermore, the turbine blade thermal shock testing apparatus provided by this invention provides guidance for evaluating the fatigue resistance of thermal barrier coating systems under extreme thermal shock conditions. It is also suitable for fatigue life performance testing of turbine blades made of various material systems, including high-temperature alloys and ceramic-based composites.

[0034] In summary, compared with the existing technology, the present invention has significant advantages in terms of test function integrity, working condition simulation accuracy and test efficiency, and can provide comprehensive test support for the research and development of aircraft engine hot end components. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 It is a schematic diagram of the main structure of the present invention.

[0036] Figure 2 yes Figure 1 Schematic diagram of the structure of the medium flame gas heating system.

[0037] Figure 3 yes Figure 1 Schematic diagram of the structure of the medium-duplex pushing platform.

[0038] Figure 4 yes Figure 1 Schematic diagram of the structure of the test station and synchronous belt installation method.

[0039] Figure 5 yes Figure 1 Schematic diagram of the connection structure between the middle test station and the cam bearing guide groove structure. DETAILED DESCRIPTION

[0040] The present invention will be further described below with reference to specific embodiments, and the advantages and features of the present invention will become clearer as the description proceeds. However, these embodiments are merely exemplary and do not constitute any limitation to the scope of the present invention. It should be understood by those skilled in the art that the details and forms of the technical solutions of the present invention may be modified or replaced without departing from the spirit and scope of the present invention, and such modifications and replacements fall within the scope of protection of the present invention.

[0041] See also Figures 1 to 5 The present invention relates to a dual-station turbine blade thermal shock test device, comprising:

[0042] Flame gas heating system 1, used to generate high-temperature flames by burning gas to simulate the transient thermal shock during the start-up of an aircraft engine;

[0043] The dual-station pushing platform 2 includes a frame and a front test station 203 and two rear independent test stations 207 mounted on the frame. The front test station 203 is used to heat the blade test piece at high temperature, and the rear test station is used to cool the blade test piece. The front test station 203 and the two rear independent test stations 207 are linked and controlled by a synchronization unit.

[0044] Air flow cooling system 3, used to quickly cool down the high-temperature test piece, provides a pure gas source through a high-pressure nitrogen bottle and uses a mass flow controller to adjust the flow;

[0045] Infrared temperature measuring device 4, used to detect the blade surface temperature in real time and feed it back to the flame gas heating system 1 to achieve closed-loop temperature control;

[0046] Image acquisition device 5, used to collect crack morphology characteristic data on the blade surface during the test;

[0047] The base 6, the flame gas heating system 1, the double-station pushing platform 2, the airflow cooling system 3, the infrared temperature measuring device 4 and the image acquisition device 5 are all installed on the base 6 and connected to the control box.

[0048] Based on the above structure, the following advantages are achieved:

[0049] 1. Efficient Dual-Station Collaborative Testing: The dual-station push platform 2's front test station 203 and rear test station 207 allow simultaneous alternating heating and cooling of two blade specimens, significantly improving testing efficiency. The two stations are controlled in tandem by a synchronization unit, ensuring seamless transitions between heating and cooling phases and eliminating the time wasted associated with traditional single-station equipment.

[0050] 2. Accurate Thermal Load Simulation: The flame gas heating system 1 utilizes a flame spray gun 101, a vertical lift platform 103, and a motorized horizontal slide 105. The vertical height and horizontal distance of the flame spray gun can be precisely adjusted to ensure the location and intensity of high-temperature flame ablation on the blades are consistent with actual aircraft engine operating conditions. An infrared temperature measurement device 4 provides real-time temperature feedback and closed-loop control of the heating system, ensuring a heating rate of at least 1500°C / min and a target temperature error within ±20°C, accurately simulating transient thermal shock.

[0051] 3. Uniform and Rapid Cooling and Data Reliability: Airflow Cooling System 3 utilizes high-pressure nitrogen cylinders and mass flow controllers to provide pure, controllable cooling airflow, achieving a cooling rate of 1500±100°C / min. This airflow evenly covers the blade surface, eliminating the localized overcooling or insufficient cooling issues associated with traditional spray cooling. Combined with dual-station synchronous switching, this ensures comparative analysis of different samples under the same thermal load conditions, significantly improving data consistency and reliability.

[0052] 4. Dynamic crack monitoring and life assessment: The image acquisition device 5 (such as a high-speed camera or a microscopic imaging system) captures the crack initiation and propagation process on the blade surface in real time at a sampling frequency of not less than 1000 frames per second. Combined with infrared temperature measurement data, it can quantitatively analyze the correlation between crack length, morphological characteristics and thermal stress load, providing a scientific evaluation basis for the thermal shock fatigue resistance of thermal barrier coating systems and high-entropy alloys.

[0053] 5. Modular Integration and High Stability: All functional modules (such as the flame gas heating system 1 and the dual-station push platform 2) are integrated into a high-temperature alloy base 6 and are centrally controlled by a control box. The frame is constructed of high-temperature resistant materials and features a mechanical linkage design with cam bearing followers 218 and V-shaped guide grooves 209, ensuring stable motion during station switching and preventing test interference.

[0054] The present invention solves the problems of low efficiency, large thermal load simulation deviation, and high data discreteness of traditional single-station equipment by combining dual-station collaborative testing, closed-loop temperature control, high-speed cooling, and dynamic monitoring technology, providing an efficient, accurate, and repeatable testing platform for the research and development of aero-engine turbine blade materials.

[0055] The flame gas heating system 1 includes a flame spray gun 101, a flame spray gun mounting bracket 102, a vertical lifting platform 103, a vertical lifting platform mounting seat 104 and an electric horizontal slide 105. The vertical lifting platform mounting seat 104 is slidably mounted on the electric horizontal slide 105 and is driven by the electric horizontal slide 105; the vertical lifting platform 103 is mounted on the upper part of the vertical lifting platform mounting seat 104, and the flame spray gun 101 is mounted on the vertical lifting platform 103 through the flame spray gun mounting bracket 102. The vertical lifting platform 103 is used to adjust the vertical height of the flame spray gun 101, and the electric horizontal slide 105 is used to adjust the horizontal distance of the flame spray gun 101 to achieve precise ablation of the blade test piece by the flame.

[0056] The structural advantages of the flame gas heating system 1 are as follows:

[0057] 1. Three-dimensional precise positioning capability: The vertical height of the flame spray gun 101 is adjusted by the vertical lifting platform 103, and the horizontal distance is adjusted by the electric horizontal slide 105 to achieve precise positioning of the flame spray gun in three-dimensional space, ensuring that the ablation position, angle and intensity of the high-temperature flame on the blade test piece are highly consistent with the actual operating conditions of the aircraft engine.

[0058] 2. Dynamic Adaptive Adjustment: The electric horizontal slide 105 and vertical lift 103 are driven by servo motors, offering programmable control of movement speed and displacement, enabling rapid response and micron-level precision adjustment. This design accommodates blade specimens of varying sizes and curvatures, meeting the demands of simulating complex ablation paths while avoiding the limitations of traditional fixed spray guns.

[0059] 3. Stability in high-temperature environments: The vertical lift platform mounting base 104 and the electric horizontal slide 105 are made of high-temperature resistant alloy material, combined with linear guide rails and ball screw transmission structures. They can maintain stable operation in high-temperature environments (>1700°C) and have excellent resistance to thermal deformation, ensuring that the spray gun position does not drift during the test.

[0060] 4. Modularity and Maintainability: The flame spray gun 101 is modularly connected to the vertical lift platform 103 via the flame spray gun mounting bracket 102, enabling quick disassembly, replacement, or repair. The electric slide and lift platform are independently controlled, ensuring that a local failure does not affect overall system operation, reducing maintenance costs.

[0061] 5. Closed-loop control compatibility

[0062] The flame gas heating system 1 works in conjunction with the infrared temperature measuring device 4 to dynamically adjust the vertical height and horizontal distance of the flame spray gun based on real-time temperature feedback, achieving closed-loop control of the ablation intensity (e.g., heating rate ≥ 1500°C / min, temperature fluctuation ≤ ±20°C), and accurately simulating transient thermal shock.

[0063] Through high-precision mechatronic design, this structure solves the problems of rough positioning and poor heat source stability in traditional heating systems, provides a controllable and repeatable thermal load loading method for turbine blade thermal shock testing, and significantly improves the accuracy of test data and the authenticity of operating condition simulation.

[0064] The front test station 203 includes a front test top plate, a test blade 201, a front blade clamping tool 202, a linear bearing 204 and a support platform 214. The support platform 214 is installed on the frame and forms a gap with the bottom of the frame; a plurality of lifting columns are provided at the bottom of the front test top plate, and each of the lifting columns slides with the support platform 214 through a linear bearing 204; the support platform 214 is driven by a lifting drive unit; a front blade clamping tool 202 is installed on the front test top plate, and the upper part of the front blade clamping tool 202 is fixed with the front test blade 210 by screws, and the lower part is installed on the front test top plate by bolts; the bottom of the support platform 214 is slidably installed on the support platform linear guide rail 213.

[0065] The lifting drive unit includes a mounting bracket 215, a cam bearing follower 218, a guide plate and a guide groove 209. A mounting bracket 215 arranged in the vertical direction is also installed at the bottom of the front test top plate. The lower end of the mounting bracket 215 passes through the support platform 214 and is installed with a cam bearing follower 218; the guide plate is installed on the frame, and a V-shaped guide groove is provided along the length direction of the frame. The cam bearing follower 218 is rollingly installed in the V-shaped guide groove.

[0066] The structural advantages of the front test station 203 are as follows:

[0067] 1. High-precision vertical motion control

[0068] The support platform 214 cooperates with the lifting column through the linear bearing 204 to achieve smooth, low-friction movement of the front test station 203 in the vertical direction, ensuring the positioning consistency of the test blade 201 during the heating and cooling process and avoiding the influence of mechanical vibration on the test results.

[0069] 2. Modular quick clamping design: The front blade clamping fixture 202 adopts a split structure. The upper part fixes the test blade 201 with screws, and the lower part is connected to the test top plate with bolts. It supports rapid disassembly and replacement, adapts to the testing requirements of different types of blades, significantly shortens sample preparation time, and improves test efficiency.

[0070] 3. Mechanical linkage synergy

[0071] By linking with the rear test station 207 through synchronization units (such as the cam bearing follower 218 and the V-shaped guide groove 209), the vertical lifting and horizontal movement of the support platform 214 can accurately match the double-station switching logic, ensuring that the two stations do not interfere with each other during alternating testing, thereby improving test safety.

[0072] This structure solves the problems of rough positioning, sensitivity to thermal deformation, and low sample changing efficiency of traditional test stations through high-precision motion control, modular clamping, multi-degree-of-freedom adaptation and high-temperature stability design. It provides a high-reliability and high-repeatability test environment for turbine blade thermal shock testing, significantly improving data comparability and test efficiency.

[0073] The rear test station 207 includes a rear test top plate, a rear blade clamping tool 206, a rear test blade 205, a rodless cylinder 211, a T-shaped mounting frame 212 and a test station linear guide 210. The test station linear guide 210 is installed on the frame, and the rear test top plate is slidably installed on the test station linear guide 210; the rodless cylinder 211 is installed on the outside of the frame, and the sliding part of the rodless cylinder 211 is connected to the rear test top plate through the T-shaped mounting frame 212, driving the rear test top plate to move forward, backward and stay; the rear blade clamping tool 206 is installed on the rear test top plate, and the upper part of the rear blade clamping tool 206 is fixed with the rear test blade 205 by screws, and the lower part is installed on the rear test top plate by bolts.

[0074] The structural advantages of the post-test station 207 are as follows:

[0075] 1. Efficient and precise horizontal drive: Driven by a rodless cylinder 211, the test top plate moves along the test station linear guide 210. Combined with the control box, it enables precise positioning of the test station during forward, reverse, and dwell times, significantly shortening station switching cycles and meeting the requirements of high-frequency thermal shock testing. A T-shaped mounting bracket 212 reinforces the rigid connection between the drive mechanism and the top plate, preventing vibration or deflection caused by inertia during movement.

[0076] 2. Modular clamping and rapid sample change: The rear blade clamping fixture 206 adopts a split design. The upper part fixes the rear test blade 205 with screws, and the lower part is connected to the rear test top plate with bolts. It supports the removal and installation of the sample within 10 seconds, adapting to the batch testing needs of multiple blade models and improving test efficiency.

[0077] 3. Collaborative linkage and safety protection: The synchronous belt 208 and the synchronization unit (such as the upper connecting piece 217 and the lower connecting piece 216) are linked with the front test station 203 to ensure synchronous reverse movement of the two stations (center distance 660±5mm). During the movement, the cam bearing follower 218 and the V-shaped guide groove 209 are used to automatically adjust the vertical spacing (120±1mm) to avoid station collision and ensure test safety.

[0078] The setting of this structure provides an efficient, stable and repeatable cooling test environment for turbine blade thermal shock testing, significantly improving the efficiency and data consistency of dual-station collaborative testing.

[0079] The synchronization unit includes a synchronous belt 208, an upper connecting piece 217, a lower connecting piece 216 and a synchronous pulley. Several synchronous pulleys are installed on the inner wall of the frame. The synchronous belt 208 passes through all the synchronous pulleys in sequence. The upper part of the synchronous belt is connected to the rear test top plate through the upper connecting piece 217; the lower part of the synchronous belt is connected to the support platform 214 through the lower connecting piece 216.

[0080] The cooling medium of the airflow cooling system 3 is high-pressure nitrogen, and the cooling rate is precisely controlled by a mass flow controller, so that the cooling airflow evenly covers the blade surface.

[0081] The image acquisition device 5 is a high-speed camera or a microscopic imaging system, which is used to capture the initiation and expansion process of cracks on the blade surface in real time and record the crack length and morphological characteristics.

[0082] The present invention also relates to a test method based on the dual-station turbine blade thermal shock test device, comprising the following steps:

[0083] S1. Sample clamping: The first test blade 201 is mounted on the front blade clamping fixture 202 of the front test station 203, and the second test blade 205 is mounted on the rear blade clamping fixture 206 of the rear test station 207;

[0084] S2 initial positioning: the horizontal position of the flame spray gun 101 is adjusted by the electric horizontal slide 105, and the vertical height of the flame spray gun 101 is adjusted by the vertical lift 103 so that it is aligned with the first test blade 201 on the front test station 203;

[0085] S3. Heating Phase: Flame gas heating system 1 is activated, generating a high-temperature flame through gas combustion to transiently heat first test blade 201. Infrared temperature measurement device 4 monitors the blade surface temperature in real time and feeds this temperature data back to flame gas heating system 1, forming a closed-loop control loop to accurately achieve the target temperature.

[0086] S4. Synchronous station switching: When the first test blade 201 reaches the preset temperature, the synchronization unit controls the dual-station push platform 2, driving the rodless cylinder 211 to move the rear test station 207 forward along the test station linear guide 210. Simultaneously, the synchronous belt 208 pulls the front test station 203 backward along the support platform linear guide 213, causing the first test blade 201 to enter the cooling zone and the second test blade 205 to enter the heating zone.

[0087] S5 cooling stage: start the airflow cooling system 3, adjust the flow rate of high-pressure nitrogen by the mass flow controller, the first test blade 201 is uniformly and rapidly cooled, and step S3 is repeated to heat the second test blade 205;

[0088] S6. Data acquisition: During the heating and cooling process, the image acquisition device 5 captures the crack initiation and propagation process on the surface of the first test blade 201 and the second test blade 205 in real time, and records the crack length and morphological characteristics;

[0089] S7. Cyclic test: Repeat steps S3 to S6, alternating heating and cooling of the test blades on the double station until the preset number of thermal shock cycles is completed;

[0090] S8. Result analysis: Based on the temperature data from the infrared temperature measuring device 4 and the crack characteristic data from the image acquisition device 5, the thermal shock fatigue resistance of the blade material is evaluated.

[0091] The linkage control of the synchronization unit is specifically as follows:

[0092] When the rodless cylinder 211 drives the rear test station 207 to move forward along the linear guide rail 210, it drives the rear test top plate of the rear test station 207 to move through the T-shaped mounting bracket 212;

[0093] The synchronous belt 208 is connected to the rear test top plate of the rear test station 207 through the upper connecting member 217 and is connected to the support platform 214 through the lower connecting member 216, so that the front test station 203 and the rear test station 207 move synchronously in opposite directions;

[0094] During the movement, the cam bearing follower 218 slides along the V-shaped guide groove 209, driving the front test station 203 to rise and fall vertically, ensuring that the center distance between the front test station and the rear test station is 660±5mm and the vertical spacing is 120±1mm.

[0095] The present invention solves the problems of low efficiency of traditional equipment, large deviation in working condition simulation, and high data discreteness through dual-station collaborative testing, high-precision thermal load loading, uniform cooling and dynamic monitoring technology. It provides an efficient, accurate and repeatable test platform for thermal shock and fatigue performance testing of aircraft engine turbine blades, significantly accelerating the research and development process of hot end components.

[0096] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution and inventive concept of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A dual-station turbine blade thermal shock test device, characterized in that: include: A flame gas heating system (1) is used to generate a high-temperature flame by burning gas to simulate the transient thermal shock during the start-up of an aircraft engine; A dual-station pushing platform (2) comprises a frame, a front test station (203) and two rear independent test stations (207) mounted on the frame, wherein the front test station (203) is used to perform high-temperature heating on a blade test piece, and the rear test station is used to perform cooling on the blade test piece; the front test station (203) and the two rear independent test stations (207) are linked and controlled by a synchronization unit; An air flow cooling system (3) is used to quickly cool down the high-temperature test piece, and a pure gas source is provided by a high-pressure nitrogen bottle and a mass flow controller is used to adjust the flow rate; An infrared temperature measuring device (4) is used to detect the blade surface temperature in real time and feed it back to the flame gas heating system (1) to achieve closed-loop temperature control; An image acquisition device (5) is used to acquire crack morphology characteristic data on the blade surface during the test; The base (6), the flame gas heating system (1), the double-station pushing platform (2), the air flow cooling system (3), the infrared temperature measuring device (4) and the image acquisition device (5) are all installed on the base (6) and connected to the control box.

2. The dual-station turbine blade thermal shock test device according to claim 1, characterized in that: The flame gas heating system (1) includes a flame spray gun (101), a flame spray gun mounting bracket (102), a vertical lifting platform (103), a vertical lifting platform mounting seat (104) and an electric horizontal slide (105), wherein the vertical lifting platform mounting seat (104) is slidably mounted on the electric horizontal slide (105) and driven by the electric horizontal slide (105); the vertical lifting platform (103) is mounted on the upper part of the vertical lifting platform mounting seat (104), and the flame spray gun (101) is mounted on the vertical lifting platform (103) through the flame spray gun mounting bracket (102), the vertical lifting platform (103) is used to adjust the vertical height of the flame spray gun (101), and the electric horizontal slide (105) is used to adjust the horizontal distance of the flame spray gun (101) to achieve precise ablation of the blade test piece by the flame.

3. The dual-station turbine blade thermal shock test device according to claim 1 or 2, characterized in that: The front test station (203) comprises a front test top plate, a test blade (201), a front blade clamping fixture (202), a linear bearing (204) and a support platform (214), wherein the support platform (214) is mounted on the frame and forms a gap with the bottom of the frame; A plurality of lifting columns are provided at the bottom of the front test top plate, and each of the lifting columns is slidably matched with the support platform (214) via a linear bearing (204); the support platform (214) is driven by a lifting drive unit; a front blade clamping fixture (202) is installed on the front test top plate, the upper part of the front blade clamping fixture (202) is fixedly mounted with the front test blade (210) via screws, and the lower part is mounted on the front test top plate via bolts; the bottom of the support platform (214) is slidably mounted on a support platform linear guide rail (213).

4. The dual-station turbine blade thermal shock test device according to claim 3, characterized in that: The lifting drive unit comprises a mounting bracket (215), a cam bearing follower (218), a guide plate and a guide groove (209); a mounting bracket (215) arranged in a vertical direction is also installed at the bottom of the front test top plate; the lower end of the mounting bracket (215) passes through the support platform (214) and is then installed with a cam bearing follower (218); the guide plate is installed on the frame, and a V-shaped guide groove is provided along the length direction of the frame, and the cam bearing follower (218) is rollingly installed in the V-shaped guide groove.

5. The dual-station turbine blade thermal shock test device according to claim 4, characterized in that: The rear test station (207) comprises a rear test top plate, a rear blade clamping tool (206), a rear test blade (205), a rodless cylinder (211), a T-shaped mounting frame (212) and a test station linear guide rail (210); the test station linear guide rail (210) is mounted on the frame, and the rear test top plate is slidably mounted on the test station linear guide rail (210); the rodless cylinder (211) is mounted on the outside of the frame, and the sliding part of the rodless cylinder (211) is connected to the rear test top plate through the T-shaped mounting frame (212), driving the rear test top plate to move forward, backward and stay; the rear blade clamping tool (206) is mounted on the rear test top plate, the upper part of the rear blade clamping tool (206) is fixedly mounted with the rear test blade (205) by screws, and the lower part is mounted on the rear test top plate by bolts.

6. The dual-station turbine blade thermal shock test device according to claim 5, characterized in that: The synchronization unit includes a synchronization belt (208), an upper connecting member (217), a lower connecting member (216) and a synchronization pulley. Several synchronization pulleys are installed on the inner wall of the frame. The synchronization belt (208) passes around all the synchronization pulleys in sequence. The upper part of the synchronization belt is connected to the rear test top plate through the upper connecting member (217); the lower part of the synchronization belt is connected to the support platform (214) through the lower connecting member (216).

7. The dual-station turbine blade thermal shock test device according to claim 6, characterized in that: The cooling medium of the airflow cooling system (3) is high-pressure nitrogen, and the cooling rate is precisely controlled by a mass flow controller, so that the cooling airflow evenly covers the blade surface.

8. The dual-station turbine blade thermal shock test device according to claim 1, characterized in that: The image acquisition device (5) is a high-speed camera or a microscopic imaging system, which is used to capture the initiation and expansion process of cracks on the blade surface in real time and record the crack length and morphological characteristics.

9. A test method based on the dual-station turbine blade thermal shock test device according to any one of claims 1 to 8, characterized in that: The following steps are involved: S1. Sample clamping: The first test blade (201) is mounted on the front blade clamping fixture (202) of the front test station (203), and the second test blade (205) is mounted on the rear blade clamping fixture (206) of the rear test station (207); S2. Initial positioning: adjusting the horizontal position of the flame spray gun (101) by the electric horizontal slide (105), and adjusting the vertical height of the flame spray gun (101) by the vertical lift (103) so that it is aligned with the first test blade (201) on the front test station (203); S3. Heating stage: The flame gas heating system (1) is started to transiently heat the first test blade (201) by generating a high-temperature flame through gas combustion. At the same time, the surface temperature of the blade is monitored in real time using an infrared temperature measuring device (4), and the temperature data is fed back to the flame gas heating system (1), forming a closed-loop control to accurately achieve the target temperature; S4. Synchronous switching of workstations: When the first test blade (201) reaches the preset temperature, the double-workstation pushing platform (2) is controlled by the synchronization unit, driving the rodless cylinder (211) to drive the rear test station (207) to move forward along the test station linear guide rail (210), and at the same time, the front test station (203) is pulled backward along the support platform linear guide rail (213) by the synchronous belt (208), so that the first test blade (201) enters the cooling area and the second test blade (205) enters the heating area; S5. Cooling stage: Start the airflow cooling system (3), adjust the flow rate of high-pressure nitrogen through the mass flow controller, and uniformly and quickly cool the first test blade (201), while repeating step S3 to heat the second test blade (205); S6. Data acquisition: During the heating and cooling process, the crack initiation and propagation process on the surface of the first test blade (201) and the second test blade (205) is captured in real time by the image acquisition device (5), and the crack length and morphological characteristics are recorded; S7. Cyclic test: Repeat steps S3 to S6, alternating heating and cooling of the test blades on the double station until the preset number of thermal shock cycles is completed; S8. Result analysis: Based on the temperature data from the infrared temperature measuring device (4) and the crack characteristic data from the image acquisition device (5), the thermal shock fatigue resistance of the blade material is evaluated.

10. The test method according to claim 9, characterized in that In step S4, the linkage control of the synchronization unit is specifically as follows: When the rodless cylinder (211) drives the rear test station (207) to move forward along the linear guide rail (210), the rear test top plate of the rear test station (207) is driven to move via the T-shaped mounting bracket (212); The synchronous belt (208) is connected to the rear test top plate of the rear test station (207) through the upper connecting member (217) and is connected to the support platform (214) through the lower connecting member (216), so that the front test station (203) and the rear test station (207) move synchronously in opposite directions; During the movement, the cam bearing follower (218) slides along the V-shaped guide groove (209), driving the front test station (203) to move vertically up and down, ensuring that the center distance between the front test station and the rear test station is 660±5mm and the vertical spacing is 120±1mm.

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