Double-station turbine blade thermal shock test device

Abstract

The utility model relates to a double-station turbine blade thermal shock test device, which comprises a flame gas heating system 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 a rear testing station, wherein the front testing station and the rear testing station 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 aero-engine hot-end component testing device has the advantages that the aero-engine hot-end component testing device has remarkable advantages in the aspects of testing function integrity, working condition simulation accuracy, testing efficiency and the like, and comprehensive testing support can be provided for research and development of aero-engine hot-end components.

Description

Technical Field

[0001] This utility model relates to a dual-station turbine blade thermal shock testing device, belonging to the field of aero-engine component testing technology. Background Technology

[0002] In the field of modern aero-engine technology, turbine blades, as core hot-end components, directly determine the overall performance and service life of the engine. With the turbine inlet temperature of new-generation aero-engines exceeding 2200K, the thermal load on blade materials is approaching their melting point limit. During actual service, turbine blades must withstand extreme thermal shock conditions: during engine startup, the blade surface temperature can rise rapidly from room temperature to 1700℃ within 3-5 seconds; and in extreme situations such as emergency shutdown, the cooling rate can exceed 1500℃ / min. This drastic temperature transient generates transient thermal stresses up to 800MPa within the blade, leading to typical thermal shock fatigue damage such as thermal barrier coating peeling and microcrack initiation. Turbine blade thermal shock testing equipment, through precise control of temperature cycling and thermal stress loading, can accurately simulate the extreme temperature transient processes in actual aero-engine operation, enabling scientific evaluation of the high-temperature strength characteristics and service life of the blade coating system. It has now become a key technical means for assessing the mechanical properties of thermal barrier coatings and high-temperature composite materials, and optimizing structural design.

[0003] Currently, most existing turbine blade thermal shock testing devices are single-station designs, which can only test one blade at a time, resulting in low testing efficiency and difficulty in ensuring comparative analysis of different blades under the same thermal load conditions. In addition, existing equipment has shortcomings in terms of temperature control accuracy, cooling medium uniformity, and automation level, such as: (1) limited heating methods, with some test benches using resistance furnace heating, resulting in slow heating rates (usually <100℃ / min), making it difficult to simulate the actual working conditions of the engine; (2) poor cooling uniformity, with traditional spray cooling easily leading to local overcooling or insufficient cooling of the blades, affecting the reliability of the data; (3) low data comparability, with environmental parameter fluctuations leading to large dispersion of test results during multiple tests at a single station. Utility Model Content

[0004] To address the problems of low efficiency, insufficient thermal load control accuracy, and poor data comparability in existing turbine blade thermal shock testing devices, this invention provides a dual-station turbine blade thermal shock testing device. This device, through its dual-test station design and the integration of flame heating, gas cooling, and control technology, can simultaneously conduct thermal shock fatigue tests on two samples, significantly improving testing efficiency and data reliability.

[0005] To overcome the shortcomings of existing technologies, this utility model provides a dual-station turbine blade thermal shock testing device. The technical solution of this utility model is as follows:

[0006] A dual-station turbine blade thermal shock testing device includes:

[0007] Flame gas heating system (1) is used to simulate the transient thermal shock during the start-up of an aircraft engine by generating a high-temperature flame through gas combustion.

[0008] The dual-station push platform (2) includes a frame and a front test station (203) and a rear test station (207) installed 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 rear test station (207) are linked and controlled by a synchronization unit.

[0009] The airflow cooling system (3) is used to rapidly cool down the high-temperature test piece. It provides a pure gas source through a high-pressure nitrogen cylinder and uses a mass flow controller to regulate the flow rate.

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

[0011] Image acquisition device (5) is used to acquire crack morphology data on the surface of the blade during the experiment;

[0012] The flame gas heating system (1), dual-station push platform (2), airflow cooling system (3), infrared temperature measuring device (4) and 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 gun (101), a flame gun mounting bracket (102), a vertical lifting platform (103), a vertical lifting platform mounting base (104), and an electric horizontal slide (105). The vertical lifting platform mounting base (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 base (104). The flame gun (101) is mounted on the vertical lifting platform (103) through the flame gun mounting bracket (102). The vertical lifting platform (103) is used to adjust the vertical height of the flame gun (101), and the electric horizontal slide (105) is used to adjust the horizontal distance of the flame gun (101) to achieve precise ablation of the blade test piece by the flame.

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

[0015] 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) is also installed at the bottom of the front test top plate, which is arranged vertically. The lower end of the mounting bracket (215) passes through the support platform (214) and is equipped 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 of the frame. The cam bearing follower (218) is rolled in the V-shaped guide groove.

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

[0017] The synchronization unit includes a timing belt (208), an upper connector (217), a lower connector (216), and timing pulleys. Several timing pulleys are installed on the inner wall of the frame. The timing belt (208) passes around all the timing pulleys in sequence. The upper part of the timing belt is connected to the rear test top plate through the upper connector (217), and the lower part of the timing belt is connected to the support platform (214) through the lower connector (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, used to capture the initiation and propagation process of cracks on the blade surface in real time, and record the crack length and morphological characteristics.

[0020] The advantages of this invention are: its unique dual-station design allows for simultaneous thermal shock fatigue testing of two samples, significantly improving testing efficiency and data reliability. Furthermore, the turbine blade thermal shock testing device provided by this invention offers guidance for evaluating the fatigue resistance of thermal barrier coating systems under extreme thermal shock conditions, and is also applicable to fatigue life performance testing of turbine blades made of various material systems such as high-temperature alloys and ceramic matrix composites.

[0021] In summary, compared with the existing technology, this utility model has significant advantages in terms of the completeness of testing functions, the accuracy of operating condition simulation, and the efficiency of testing, and can provide comprehensive testing support for the research and development of hot-end components of aero engines. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the main structure of this utility model.

[0023] Figure 2 yes Figure 1 Schematic diagram of the structure of the medium-flame gas heating system.

[0024] Figure 3 yes Figure 1 Schematic diagram of the dual-station push platform structure.

[0025] Figure 4 yes Figure 1 Schematic diagram of the installation method of the test station and synchronous belt.

[0026] Figure 5 yes Figure 1 A schematic diagram of the connection structure between the test station and the cam bearing guide groove. Detailed Implementation

[0027] 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 a result of the description. However, these embodiments are merely exemplary and do not constitute any limitation on the scope of the present invention. Those skilled in the art should understand that modifications or substitutions can be made to the details and form of the technical solution of the present invention without departing from the spirit and scope of the present invention, but all such modifications and substitutions fall within the protection scope of the present invention.

[0028] See Figures 1 to 5 This utility model relates to a dual-station turbine blade thermal shock testing device, comprising:

[0029] Flame gas heating system 1 is used to simulate the transient thermal shock during the start-up of an aircraft engine by generating a high-temperature flame through gas combustion.

[0030] The dual-station push platform 2 includes a frame and a front test station 203 and a rear test station 207 installed 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 rear test station 207 are linked and controlled by a synchronization unit.

[0031] The airflow cooling system 3 is used to rapidly cool down the high-temperature test piece. It provides a pure gas source through a high-pressure nitrogen cylinder and uses a mass flow controller to regulate the flow rate.

[0032] Infrared temperature measuring device 4 is used to detect the surface temperature of the blade in real time and feed it back to the flame gas heating system 1 to achieve closed-loop temperature control;

[0033] Image acquisition device 5 is used to acquire crack morphology feature data on the blade surface during the experiment;

[0034] The flame gas heating system 1, the dual-station push 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.

[0035] Based on the above structural design, the following advantages are achieved:

[0036] 1. High-efficiency dual-station collaborative testing: The dual-station push platform 2, with its front testing station 203 and rear testing station 207, allows for simultaneous alternating heating and cooling of two blade samples, significantly improving testing efficiency. The two stations are linked and controlled by a synchronization unit, ensuring seamless switching between heating and cooling phases and avoiding the time wastage associated with traditional single-station equipment.

[0037] 2. Precise Thermal Load Simulation: The flame combustion heating system 1 employs a combination of a flame gun 101, a vertical lifting platform 103, and an electric horizontal slide 105. This allows for precise adjustment of the flame gun's vertical height and horizontal distance, ensuring that the ablation location and intensity of the high-temperature flame on the blades are consistent with the actual operating conditions of an aero-engine. An infrared temperature measurement device 4 provides real-time temperature data feedback and performs closed-loop control of the heating system, ensuring a heating rate of no less than 1500℃ / min and a target temperature error controlled within ±20℃, accurately simulating transient thermal shock.

[0038] 3. Uniform and rapid cooling and data reliability: The airflow cooling system 3 provides a pure and controllable cooling airflow through a high-pressure nitrogen cylinder and a mass flow controller, achieving a cooling rate of 1500±100℃ / min. The airflow uniformly covers the blade surface, avoiding the localized overcooling or undercooling problems of traditional spray cooling. Combined with dual-station synchronous switching, it ensures that different samples can be compared and analyzed under the same thermal load conditions, significantly improving data consistency and reliability.

[0039] 4. Dynamic crack monitoring and life assessment: The image acquisition device 5 (such as a high-speed camera or microscopic imaging system) captures the initiation and propagation process of cracks on the blade surface in real time at a sampling frequency of no less than 1000 frames / second. Combined with infrared thermometry data, the correlation between crack length, morphological characteristics and thermal stress load can be quantitatively analyzed, providing a scientific basis for evaluating the thermal shock fatigue resistance of thermal barrier coating systems and high-entropy alloys.

[0040] 5. Modular Integration and High Stability: All functional modules (flame gas heating system 1, dual-station push platform 2, etc.) are integrated on the high-temperature alloy base 6 and uniformly controlled through the control box. The frame is made of high-temperature resistant material, and the mechanical linkage design of the cam bearing follower 218 and V-shaped guide groove 209 ensures stable motion trajectory during station switching and avoids test interference.

[0041] This invention solves the problems of low efficiency, large thermal load simulation deviation, and high data dispersion of traditional single-station equipment by combining dual-station collaborative testing, closed-loop temperature control, high-speed cooling and dynamic monitoring technologies, and provides an efficient, accurate and repeatable test platform for the research and development of turbine blade materials for aero-engines.

[0042] The flame gas heating system 1 includes a flame gun 101, a flame gun mounting bracket 102, a vertical lifting platform 103, a vertical lifting platform mounting base 104, and an electric horizontal slide 105. The vertical lifting platform mounting base 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 base 104. The flame gun 101 is mounted on the vertical lifting platform 103 via the flame gun mounting bracket 102. The vertical lifting platform 103 is used to adjust the vertical height of the flame gun 101, and the electric horizontal slide 105 is used to adjust the horizontal distance of the flame gun 101 to achieve precise ablation of the blade test specimen by the flame.

[0043] The structural advantages of the flame gas heating system 1 are as follows:

[0044] 1. Three-dimensional precise positioning capability: By adjusting the vertical height of the flame gun 101 through the vertical lifting platform 103 and adjusting the horizontal distance through the electric horizontal slide 105, the flame gun can be precisely positioned 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 working conditions of the aero-engine.

[0045] 2. Dynamic Adaptive Adjustment: The electric horizontal slide 105 and vertical lifting stage 103 are driven by servo motors, allowing for programmable control of movement speed and displacement, supporting rapid response and micron-level precision adjustment. This design can adapt to blade samples of different sizes and curvatures, meeting the simulation requirements of complex ablation paths and avoiding the limitations of traditional fixed spray guns.

[0046] 3. High-temperature environment stability: The vertical lifting platform mounting base 104 and the electric horizontal slide 105 are made of high-temperature resistant alloy material. With the help of linear guide rails and ball screw transmission structure, they can still maintain stable operation in high-temperature (>1700℃) environments. They have excellent resistance to thermal deformation and ensure that the position of the spray gun does not drift during the test.

[0047] 4. Modularity and Maintainability: The flame gun 101 is modularly connected to the vertical lifting platform 103 via the flame gun mounting bracket 102, supporting quick disassembly, replacement, or maintenance. The electric slide and lifting platform are independently controlled, so local failures do not affect the overall system operation, reducing maintenance costs.

[0048] 5. Closed-loop control compatibility

[0049] The flame gas heating system 1 works in conjunction with the infrared temperature measuring device 4. It can dynamically adjust the vertical height and horizontal distance of the flame gun according to the real-time temperature feedback, so as to realize the closed-loop control of the ablation intensity (such as heating rate ≥1500℃ / min, temperature fluctuation ≤±20℃) and accurately simulate transient thermal shock.

[0050] This structure, through high-precision mechatronics design, solves the problems of rough positioning and poor heat source stability in traditional heating systems, providing a controllable and repeatable thermal load loading method for turbine blade thermal shock testing, significantly improving the accuracy of test data and the realism of operating condition simulation.

[0051] The front test station 203 includes a front test top plate, a front test blade 201, a front blade clamping fixture 202, a linear bearing 204, and a support platform 214. The support platform 214 is mounted on the frame and forms a gap with the bottom of the frame. Several lifting columns are provided at the bottom of the front test top plate, and each lifting column is slidably engaged with the support platform 214 through the linear bearing 204. The support platform 214 is driven by a lifting drive unit. The front blade clamping fixture 202 is installed on the front test top plate. The front test blade 210 is fixedly installed on the upper part of the front blade clamping fixture 202 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 mounted on a support platform linear guide rail 213.

[0052] 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 vertically 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 fitted with the cam bearing follower 218. The guide plate is installed on the frame and has a V-shaped guide groove along the length of the frame. The cam bearing follower 218 is rotatably installed in the V-shaped guide groove.

[0053] The structural advantages of the aforementioned front testing station 203 are as follows:

[0054] 1. High-precision vertical motion control

[0055] The support platform 214, in conjunction with the lifting column via the linear bearing 204, enables the front test station 203 to move smoothly and with low friction in the vertical direction, ensuring the consistent positioning of the front test blade 201 during heating and cooling processes and avoiding the impact of mechanical vibration on the test results.

[0056] 2. Modular quick clamping design: The front blade clamping fixture 202 adopts a split structure. The upper part is fixed to the front test blade 201 by screws, and the lower part is connected to the test top plate by bolts. It supports quick disassembly and replacement, adapts to the testing requirements of different blade models, significantly shortens the sample preparation time, and improves the testing efficiency.

[0057] 3. Mechanical linkage and coordination

[0058] By linking the synchronization unit (such as the cam bearing follower 218 and the V-shaped guide groove 209) with the subsequent test station 207, the vertical lifting and horizontal movement of the support platform 214 can accurately match the dual-station switching logic, ensuring that the two stations do not interfere with each other during alternating testing and improving test safety.

[0059] This structure solves the problems of rough positioning, thermal deformation sensitivity, and low sample change efficiency of traditional test stations by using high-precision motion control, modular clamping, multi-degree-of-freedom adaptation, and high-temperature stability design. It provides a highly reliable and repeatable test environment for turbine blade thermal shock testing, significantly improving data comparability and test efficiency.

[0060] The rear testing station 207 includes a rear testing top plate, a rear blade clamping fixture 206, a rear test blade 205, a rodless cylinder 211, a T-shaped mounting bracket 212, and a testing station linear guide rail 210. The testing station linear guide rail 210 is mounted on the frame, and the rear testing top plate is slidably mounted on the testing station linear guide rail 210. The rodless cylinder 211 is mounted outside the frame, and the sliding part of the rodless cylinder 211 is connected to the rear testing top plate through the T-shaped mounting bracket 212, driving the rear testing top plate to move forward, backward, and stop. The rear blade clamping fixture 206 is mounted on the rear testing top plate. The upper part of the rear blade clamping fixture 206 is fixedly mounted with the rear test blade 205 by screws, and the lower part is mounted on the rear testing top plate by bolts.

[0061] The structural advantages of the post-testing station 207 are as follows:

[0062] 1. Highly efficient and precise horizontal drive: Driven by a rodless cylinder 211, the test top plate moves along the linear guide rail 210 of the test station. Combined with the control box, precise positioning of the station's forward, backward, and stationary movements can be achieved, significantly shortening the station switching cycle and meeting the requirements of high-frequency thermal shock testing. The T-shaped mounting bracket 212 enhances the rigid connection between the drive mechanism and the top plate, preventing vibration or displacement caused by inertia during movement.

[0063] 2. Modular clamping and quick sample change: The rear blade clamping fixture 206 adopts a split design. The upper part is fixed to the rear test blade 205 by screws, and the lower part is connected to the rear test top plate by bolts. It supports the disassembly and installation of the sample within 10 seconds, adapts to the batch testing needs of multiple blade models, and improves the testing efficiency.

[0064] 3. Synergistic Linkage and Safety Protection: The synchronous belt 208 and the synchronous unit (such as the upper connector 217 and the lower connector 216) are linked with the front test station 203 to ensure that the two stations move synchronously in opposite directions (center distance 660±5mm). During the movement, the vertical distance (120±1mm) is automatically adjusted by the cooperation of the cam bearing follower 218 and the V-shaped guide groove 209 to avoid station collisions and ensure test safety.

[0065] 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.

[0066] The synchronization unit includes a timing belt 208, an upper connector 217, a lower connector 216, and timing pulleys. Several timing pulleys are installed on the inner wall of the frame. The timing belt 208 sequentially passes over all the timing pulleys. The upper part of the timing belt is connected to the rear test top plate via the upper connector 217; the lower part of the timing belt is connected to the support platform 214 via the lower connector 216.

[0067] 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.

[0068] The image acquisition device 5 is a high-speed camera or a microscopic imaging system, used to capture the initiation and propagation process of cracks on the blade surface in real time, and record the crack length and morphological characteristics.

[0069] The working principle of this utility model is as follows:

[0070] S1. Sample clamping: Install the front test blade 201 on the front blade clamping fixture 202 of the front test station 203, and install the rear test blade 205 on the rear blade clamping fixture 206 of the rear test station 207.

[0071] S2. Initial positioning: Adjust the horizontal position of the flame gun 101 by using the electric horizontal slide table 105, and adjust the vertical height of the flame gun 101 by using the vertical lifting table 103, so that it is aligned with the front test blade 201 on the front test station 203.

[0072] S3. Heating stage: Start the flame gas heating system 1, generate a high-temperature flame through gas combustion to transiently heat the front test blade 201, and at the same time use the infrared temperature measuring device 4 to monitor the blade surface temperature in real time and feed the temperature data back to the flame gas heating system 1 to form a closed-loop control to accurately reach the target temperature.

[0073] S4. Synchronous switching of workstations: After the current test blade 201 reaches the preset temperature, the dual-workstation push platform 2 is controlled by the synchronous unit to drive the rodless cylinder 211 to move the rear test station 207 forward along the test station linear guide rail 210. At the same time, the synchronous belt 208 pulls the front test station 203 backward along the support platform linear guide rail 213, so that the front test blade 201 enters the cooling area and the rear test blade 205 enters the heating area.

[0074] S5. Cooling stage: Start the airflow cooling system 3, adjust the flow rate of high-pressure nitrogen through the mass flow controller, and cool the front test blade 201 uniformly and rapidly. At the same time, repeat step S3 to heat the rear test blade 205.

[0075] S6. Data acquisition: During the heating and cooling process, the crack initiation and propagation process on the surface of the front test blade 201 and the rear test blade 205 is captured in real time by the image acquisition device 5, and the crack length and morphological characteristics are recorded.

[0076] S7. Cyclic test: Repeat steps S3 to S6, alternately heating and cooling the test blades on the dual station until the preset number of thermal shock cycles is completed;

[0077] S8. Results Analysis: Based on the temperature data from the infrared thermometer 4 and the crack characteristic data from the image acquisition device 5, the thermal shock fatigue resistance of the blade material is evaluated.

[0078] The linkage control steps of the synchronization unit are as follows:

[0079] When the rodless cylinder 211 drives the rear test station 207 to move forward along the linear guide rail 210, it also drives the rear test top plate of the rear test station 207 to move through the T-shaped mounting bracket 212.

[0080] The synchronous belt 208 is connected to the rear test top plate of the rear test station 207 via the upper connector 217, and to the support platform 214 via the lower connector 216, so that the front test station 203 and the rear test station 207 move synchronously in opposite directions.

[0081] 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 distance is 120±1mm.

[0082] This invention solves the problems of low efficiency, large deviation in operating condition simulation, and high data dispersion of traditional equipment by using dual-station collaborative testing, high-precision thermal load loading, uniform cooling, and dynamic monitoring technologies. It provides an efficient, accurate, and repeatable test platform for testing the thermal shock fatigue performance of aero-engine turbine blades, significantly accelerating the research and development process of hot-end components.

[0083] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A two-station hot-air shock test device for turbine blades, characterized in that include: Flame gas heating system (1) is used to simulate the transient thermal shock during the start-up of an aircraft engine by generating a high-temperature flame through gas combustion. The dual-station push platform (2) includes a frame and a front test station (203) and a rear test station (207) installed 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 rear test station (207) are linked and controlled by a synchronization unit. The airflow cooling system (3) is used to rapidly cool down the high-temperature test piece. It provides a pure gas source through a high-pressure nitrogen cylinder and uses a mass flow controller to regulate the flow rate. Infrared temperature measuring device (4) is used to detect the surface temperature of the blade in real time and feed it back to the flame gas heating system (1) to achieve closed-loop temperature control; Image acquisition device (5) is used to acquire crack morphology data on the blade surface during the experiment; The flame gas heating system (1), dual-station push platform (2), airflow cooling system (3), infrared temperature measuring device (4) and image acquisition device (5) are all installed on the base (6) and connected to the control box.

2. The dual station turbovane thermal shock test apparatus of claim 1, wherein, The flame gas heating system (1) includes a flame gun (101), a flame gun mounting bracket (102), a vertical lifting platform (103), a vertical lifting platform mounting base (104), and an electric horizontal slide (105). The vertical lifting platform mounting base (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 base (104). The flame gun (101) is mounted on the vertical lifting platform (103) through the flame gun mounting bracket (102). The vertical lifting platform (103) is used to adjust the vertical height of the flame gun (101), and the electric horizontal slide (105) is used to adjust the horizontal distance of the flame gun (101) to achieve precise ablation of the blade test piece by the flame.

3. A two-station turbovane thermal shock test apparatus according to claim 1 or 2, characterised in that, The aforementioned front test station (203) includes a front test top plate, a front test blade (201), a front blade clamping fixture (202), a linear bearing (204), and a support platform (214). The support platform (214) is mounted on the frame and forms a gap with the bottom of the frame. Several lifting columns are provided at the bottom of the front test top plate, and each lifting column is slidably engaged with the support platform (214) through the linear bearing (204). The support platform (214) is driven by a lifting drive unit. The front blade clamping fixture (202) is installed on the front test top plate. The front test blade (201) is fixedly mounted on the upper part of the front blade clamping fixture (202) by screws, and the lower part is mounted on the front test top plate by bolts. The support platform (214) is slidably mounted on a support platform linear guide rail (213) at the bottom.

4. The dual station turbovane thermal shock test apparatus of claim 3, wherein, 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) is also installed at the bottom of the front test top plate, which is arranged vertically. The lower end of the mounting bracket (215) passes through the support platform (214) and is equipped 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 of the frame. The cam bearing follower (218) is rolled in the V-shaped guide groove.

5. The dual station turbovane thermal shock test apparatus of claim 4 wherein, The rear test station (207) includes a rear test top plate, a rear blade clamping fixture (206), a rear test blade (205), a rodless cylinder (211), a T-shaped mounting bracket (212), and a test station linear guide rail (210). The test station linear guide rail (210) is installed on the frame, and the rear test top plate is slidably installed on the test station linear guide rail (210). The rodless cylinder (211) is installed outside the frame, and the sliding part of the rodless cylinder (211) is connected to the rear test top plate through the T-shaped mounting bracket (212) to drive the rear test top plate to move forward, backward, and stop. The rear blade clamping fixture (206) is installed on the rear test top plate. The upper part of the rear blade clamping fixture (206) is fixedly installed with the rear test blade (205) by screws, and the lower part is installed on the rear test top plate by bolts.

6. The dual station turbovane thermal shock test apparatus of claim 5 wherein, The synchronization unit includes a timing belt (208), an upper connector (217), a lower connector (216), and timing pulleys. Several timing pulleys are installed on the inner wall of the frame. The timing belt (208) passes around all the timing pulleys in sequence. The upper part of the timing belt is connected to the rear test top plate through the upper connector (217). The lower part of the timing belt is connected to the support platform (214) through the lower connector (216).

7. The dual station turbovane thermal shock test apparatus of claim 6 wherein, 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 turbovane thermal shock test apparatus of claim 1 wherein, The image acquisition device (5) is a high-speed camera or a microscopic imaging system, used to capture the initiation and propagation process of cracks on the blade surface in real time, and record the crack length and morphological characteristics.

Images