Turbine blade friction test device and method

Abstract

The invention provides a turbine blade friction test device and method, and belongs to the technical field of turbine blade tests. The testing device comprises a rotating disc, a feeding mechanism, a rotating mechanism and a heating mechanism, the rotating disc is arranged on the rotating mechanism, and the rotating mechanism is used for driving the rotating disc to rotate; the rotating disc is provided with a clamping assembly, and the clamping assembly is used for clamping the turbine blade. The feeding mechanism is arranged on one side of the rotating mechanism, the cartridge receiver is connected with the feeding mechanism, and the feeding mechanism is used for driving the cartridge receiver to move so that the cartridge receiver can make contact with a blade crown of the turbine blade; the heating mechanism is arranged on one side of the rotating disc and used for heating the rotating disc. The test device has the effects of reducing the test cost and improving the reliability and the accuracy of a test result.

Description

Technical Field

[0001] This disclosure relates to the field of turbine blade testing technology, and more specifically, to a turbine blade impact and abrasion testing device and method. Background Technology

[0002] The performance indicators of a turbine, such as efficiency, power, and fuel consumption, are closely related to the radial clearance between the rotor blades and the casing. Studies have shown that for every 0.13 mm increase in radial clearance, the engine's fuel consumption per unit area increases by approximately 0.5%; conversely, for every 0.25 mm decrease in radial clearance, turbine efficiency increases by approximately 1%. Therefore, controlling the radial clearance is crucial for improving turbine performance. However, when the radial clearance is too small, the engine may experience rotor-stator rubbing during transient operation, leading to problems such as rotor-stator contact, wear, and jamming, which severely affects the engine's reliability and service life.

[0003] Therefore, it is often necessary to test the wear between the rotor and stator. Traditional testing devices typically use a method where the rotor blades are fixed and the outer ring rotates to simulate the wear between the blades and the casing. However, this method cannot account for the influence of centrifugal force, and thus cannot fully simulate the wear phenomenon of turbine blades during actual operation. Another testing method often uses the entire turbine for rotor wear testing. While directly using the entire turbine for rotor wear testing can more accurately reflect the actual situation, the testing cost is too high, making it difficult to apply widely.

[0004] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of this disclosure, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0005] The purpose of this disclosure is to overcome the shortcomings of the prior art and provide a turbine blade impact rubbing test apparatus and method. This simulates the impact rubbing process of turbine blades under use, reduces test costs, and improves the reliability and accuracy of test results.

[0006] According to one aspect of this disclosure, a turbine blade abrasion test apparatus is provided for conducting abrasion tests between the turbine blade and the casing; the test apparatus includes a rotating disk, a feeding mechanism, a rotating mechanism, and a heating mechanism; The rotating disk is mounted on the rotating mechanism, and the rotating mechanism is used to drive the rotating disk to rotate. The rotating disk has a clamping assembly for clamping the turbine blades; The feeding mechanism is located on one side of the rotating mechanism, and the housing is connected to the feeding mechanism. The feeding mechanism is used to drive the housing to move so that the housing contacts the blade crown of the turbine blade. The heating mechanism is located on one side of the rotating disk and is used to heat the rotating disk.

[0007] According to one embodiment of this disclosure, the clamping assembly includes a first mounting block, a second mounting block, and a fixing member; The rotating disk has a first mounting groove distributed along its circumference on its peripheral side, and the first mounting block is slidably connected in the first mounting groove. The sliding direction of the first mounting block is perpendicular to the rotation direction of the rotating disk. The first mounting block has a second mounting groove on the side away from the rotating disk, and the second mounting block is slidably connected in the second mounting groove. The sliding direction of the second mounting block is the same as the sliding direction of the first mounting block. The second mounting block has a third mounting groove on the side away from the first mounting block, and the turbine blade is fixed in the third mounting groove by the fastener.

[0008] According to one embodiment of the present disclosure, the first mounting groove has a first opening, a first bottom wall, a first side wall, and a second side wall; Along one side of the first bottom wall to the side of the first opening, the distance between the first sidewall and the second sidewall gradually decreases.

[0009] According to one embodiment of the present disclosure, the first mounting block has a first recess near at least one of the first sidewall and the second sidewall, wherein the first recess is configured to cooperate with its corresponding sidewall.

[0010] According to one embodiment of the present disclosure, the second mounting groove has a second opening, a second bottom wall, a third side wall, and a fourth side wall; Along the second bottom wall side to the second opening side, the distance between the third side wall and the fourth side wall gradually decreases.

[0011] According to one embodiment of this disclosure, the third sidewall and the fourth sidewall have a protrusion on the side that is close to each other; The second mounting block has a second recess on its side wall near the second mounting groove; The second recessed portion is configured to cooperate with the protruding portion.

[0012] According to one embodiment of this disclosure, the feeding mechanism includes a test platform, a feeding motor, a feeding screw, a feeding platform, and a clamping assembly; The feed screw is rotatably connected to the test platform, and the axial direction of the feed screw is perpendicular to the rotation axis of the rotating disk; The feed platform is threadedly connected to the feed screw and slidably connected to the test platform; The feed motor is used to drive the feed screw to rotate; The clamping assembly is located on the feed platform and is used to fix the housing.

[0013] According to one embodiment of this disclosure, the feeding mechanism further includes a force gauge and a cooler; The force gauge is mounted on the feed platform and is used to detect the load on the turbine blades and the casing. The cooler is configured to control the test temperature of the turbine blades and the casing.

[0014] According to one embodiment of the present disclosure, the heating mechanism includes an annular heating tube and a heating bracket; The heating bracket is located on one side of the rotating disk; The annular heating tube is mounted on the heating bracket and is used to heat the rotating disk.

[0015] According to a second aspect of this disclosure, a method for testing turbine blade impact rubbing is provided, the method comprising: Turbine blade samples and casing samples are provided; The turbine blade sample was fixed on the rotating disk; The casing sample is fixed on the feeding mechanism; The heating mechanism provides heat to the rotating disk; The feeding mechanism pushes the casing sample to move, and the casing sample contacts the blade crown of the turbine blade; The rotating mechanism drives the rotating disk to move.

[0016] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and are not intended to limit this disclosure. Attached Figure Description

[0017] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this disclosure and, together with the description, serve to explain the principles of this disclosure. It is obvious that the drawings described below are merely some embodiments of this disclosure, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort.

[0018] Figure 1 This is a schematic diagram of the overall structure of a turbine blade rubbing test device in one embodiment of the present disclosure.

[0019] Figure 2 This is a schematic diagram of a honeycomb structure in one embodiment of the present disclosure.

[0020] Figure 3 This is a schematic diagram of the structure of the rotating disk in one embodiment of the present disclosure.

[0021] Figure 4 for Figure 3 Enlarged view of part A.

[0022] Figure 5 This is a schematic diagram showing the connection between the first mounting block, the second mounting block, and the turbine blades in one embodiment of this disclosure.

[0023] Figure 6 This is an exploded view of the first mounting block, the second mounting block, and the turbine blades in one embodiment of this disclosure.

[0024] Figure 7 This is a schematic diagram showing the arrangement of the heating mechanism in one embodiment of the present disclosure.

[0025] Figure 8 This is a schematic diagram illustrating the steps of a turbine blade impact test method in one embodiment of the present disclosure.

[0026] Explanation of reference numerals in the attached figures: 1. Turbine blade; 2. Casing; 3. Rotating disk; 31. First mounting slot; 311. First opening; 312. First bottom wall; 313. First side wall; 314. Second side wall; 32. Clamping assembly; 321. First mounting block; 3211. Second mounting slot; 32111. Second opening; 32112. Second bottom wall; 32113. Third side wall; 32114. Fourth side wall; 32115. Protrusion; 3212. First recess; 322. Second mounting block; 3 221. Third mounting slot; 3222. Second recess; 323. Fixing component; 3231. Fixing pin; 4. Feeding mechanism; 41. Test platform; 42. Feeding motor; 43. Feeding screw; 44. Feeding platform; 45. Clamping assembly; 46. Force gauge; 47. Cooler; 48. Reducer; 5. Rotation mechanism; 6. Heating mechanism; 61. Heating bracket; 62. Annular heating tube; 7. Honeycomb structure; 71. First angle; 72. First distance; 73. Second distance. Detailed Implementation

[0027] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this disclosure will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and therefore detailed descriptions of them will be omitted. Furthermore, the drawings are merely illustrative of this disclosure and are not necessarily drawn to scale.

[0028] In related technologies, the following methods are commonly used to test the wear between turbine blades and the casing. The first method involves fixing the turbine blades and rotating the casing to achieve a collision between the blades and the casing. This method cannot account for the influence of centrifugal force, thus failing to simulate the actual wear phenomenon of turbine blades during operation. The second method involves conducting a rotor wear test on the entire turbine. While this method reflects the actual situation of the turbine blades, the testing cost is relatively high.

[0029] Based on this, see Figure 1 , Figure 7 The first aspect of this disclosure provides a turbine blade abrasion test apparatus for conducting abrasion tests between a turbine blade 1 and a casing 2. The apparatus includes a rotating disk 3, a feeding mechanism 4, a rotating mechanism 5, and a heating mechanism 6. The rotating disk 3 is mounted on the rotating mechanism 5, which drives the rotating disk 3 to rotate. The rotating disk 3 has a clamping assembly 32 for clamping the turbine blade 1. The feeding mechanism 4 is located on one side of the rotating mechanism 5, and the casing 2 is connected to the feeding mechanism 4. The feeding mechanism 4 drives the casing 2 to move so that the casing 2 contacts the blade crown of the turbine blade 1. The heating mechanism 6 (… Figure 1 The heating mechanism 6 (which is hidden) is located on one side of the rotating disk 3 and is used to heat the rotating disk 3.

[0030] In this embodiment, when performing abrasion tests on turbine blade 1 and casing 2, turbine blade 1 is fixed to rotating disk 3 by clamping assembly 32, and rotating disk 3 is connected to rotating mechanism 5; casing 2 is fixed to feeding mechanism 4, and feeding mechanism 4 pushes casing 2 to the crown of turbine blade 1, so that casing 2 contacts the crown of turbine blade 1; heating mechanism 6 is turned on to heat rotating disk 3, and rotating mechanism 5 is turned on to drive rotating disk 3 to move, thereby simulating the abrasion phenomenon of turbine blade 1 in actual operation, improving the reliability and accuracy of test results.

[0031] The rotating mechanism 5 disclosed in this embodiment can precisely adjust key operating parameters such as rotational speed to drive the turbine blade 1 to achieve controllable rotational motion. This allows for dynamic simulation of the linear velocity of the turbine blade 1's crown during rotation, thus replicating the motion characteristics under real-world operating conditions. It should be noted that the rotating mechanism 5 provided in this embodiment is a structure well-known to those skilled in the art, and will not be described in detail here.

[0032] Furthermore, the rotational speed of the rotating mechanism 5 is adjustable from 0 to 20,000 r / min. This adjustable range simulates the dynamic response of the turbine blade 1 when rotating at high speed. The rotational speed of the turbine blade 1 directly affects the contact force and friction between the turbine blade 1 and the casing 2. Setting the rotation radius of the rotating mechanism 5 to 350 mm and the rim linear velocity to 600 m / s allows for the simulation of the rotational trajectory of the turbine blade 1 under high-speed airflow and the influence of airflow on the turbine blade 1.

[0033] Meanwhile, the relative position between the casing 2 and the turbine blade 1 can be adjusted through the feed mechanism 4, which can reproduce the rubbing contact process between the turbine blade 1 and the casing 2. This design not only simplifies the way the blade rotation is realized, but also makes the test conditions closer to actual service conditions (such as rubbing behavior under different speeds and eccentricities) through dynamic position control capability.

[0034] It should also be noted that, see Figure 1 , Figure 2 A honeycomb structure 7 is maintained in the crown contact between the casing 2 and the turbine blade 1. The honeycomb structure 7 is a regular hexagon, wherein the included angle between the honeycomb structures 7 is a first angle 71, which is 120°; each honeycomb structure 7 has two symmetrically arranged side plates, and the distance between the two sides can be a first distance 72, which is 0.8 mm; the width of the casing 2 can be a second distance 73, wherein the second distance 73 can be 4 mm.

[0035] In some embodiments of this disclosure, see Figure 3 , Figure 4 , Figure 5 , Figure 6The clamping assembly 32 includes a first mounting block 321, a second mounting block 322, and a fixing member 323. The circumferential side of the rotating disk 3 has a first mounting groove 31 distributed along its circumference. The first mounting block 321 is slidably connected to the first mounting groove 31, and the sliding direction of the first mounting block 321 is perpendicular to the rotation direction of the rotating disk 3. The side of the first mounting block 321 away from the rotating disk 3 has a second mounting groove 3211, and the second mounting block 322 is slidably connected to the second mounting groove 3211. The sliding direction of the second mounting block 322 is the same as the sliding direction of the first mounting block 321. The side of the second mounting block 322 away from the first mounting block 321 has a third mounting groove 3221, and the turbine blade 1 is fixed in the third mounting groove 3221 by the fixing member 323.

[0036] It should be noted that the present invention does not impose a specific limitation on the number of the first mounting slots 31. In the accompanying drawings, the number of the first mounting slots 31 is shown as four.

[0037] In some examples, when it is necessary to connect the turbine blade 1 to the rotating disk 3, the turbine blade 1 is fixed in the third mounting groove 3221 by the fastener 323, then the second mounting block 322 is slid into the second mounting groove 3211, and then the first mounting block 321 is slid into the first mounting groove 31 to achieve the connection between the turbine blade 1 and the rotating disk 3.

[0038] In another example, when it is necessary to connect the turbine blade 1 to the rotating disk 3, the first mounting block 321 can be slid into the first mounting groove 31 first, and then the second mounting block 322 can be slid into the second mounting groove 3211. Then, the turbine blade 1 can be fixed in the third mounting groove 3221 by the fastener 323, thereby achieving the purpose of fixing the turbine blade 1 on the rotating disk 3.

[0039] In some embodiments, the fixing member 323 can be a fixing pin 3231. When the turbine blade 1 is mounted on the second mounting block 322, the side of the turbine blade 1 away from the blade crown is inserted into the third mounting groove 3221, and then the fixing pin 3231 is used to pass through the second mounting block 322 and the turbine blade 1 to achieve the purpose of fixing the turbine blade 1 to the second mounting block 322.

[0040] In some implementations, see 3. Figure 4The first mounting groove 31 has a first opening 311, a first bottom wall 312, a first side wall 313, and a second side wall 314. The distance between the first side wall 313 and the second side wall 314 gradually decreases along one side of the first bottom wall 312 to the other side of the first opening 311. This results in a trapezoidal cross-section for the first mounting groove 31. When the first mounting block 321 is installed in the first mounting groove 31, the smaller diameter of the first opening 311 allows for better fixation between the first mounting block 321 and the rotating disk 3, preventing the turbine blade 1 from flying off during the rotation of the rotating disk 3.

[0041] Furthermore, the first mounting block 321 has a first recess 3212 near at least one of the first sidewall 313 and the second sidewall 314, wherein the first recess 3212 is configured to cooperate with its corresponding sidewall.

[0042] Understandably, in some embodiments, the first mounting block 321 has a first recess 3212 near the first sidewall 313, and the first recess 3212 is configured to cooperate with the first sidewall 313. Thus, when the first mounting block 321 is installed in the first mounting groove 31, the first sidewall 313 can abut against the first recess 3212, thereby better securing the first mounting block 321 within the first mounting groove 31.

[0043] In some embodiments, the first mounting block 321 has a first recess 3212 near the second sidewall 314, and the first recess 3212 is configured to cooperate with the second sidewall 314. Thus, when the first mounting block 321 is installed in the first mounting groove 31, the second sidewall 314 can abut against the first recess 3212, thereby better securing the first mounting block 321 in the first mounting groove 31.

[0044] In other implementations, see Figures 3-7 The first mounting block 321 has a first recess 3212 on the side near the first sidewall 313 and the second sidewall 314. The first recess 3212 corresponding to the first sidewall 313 is configured to cooperate with the first sidewall 313, and the first recess 3212 corresponding to the second sidewall 314 is configured to cooperate with the second sidewall 314. Thus, when the first mounting block 321 is installed in the first mounting groove 31, the first recess 3212 on one side abuts against the first sidewall 313, and the first recess 3212 on the other side abuts against the second sidewall 314, which can better fix the first mounting block 321 in the first mounting groove.

[0045] In some embodiments, the second mounting groove 3211 has a second opening 32111, a second bottom wall 32112, a third side wall 32113, and a fourth side wall 32114; wherein, along the second bottom wall 32112 to the second opening 32111, the distance between the third side wall 32113 and the fourth side wall 32114 gradually decreases. This makes the cross-section of the second mounting groove 3211 roughly trapezoidal, so that when the second mounting block 322 is installed in the second mounting groove 3211, the smaller diameter of the second opening 32111 allows for better fixation between the second mounting block 322 and the first mounting block 321.

[0046] In some embodiments, the third sidewall 32113 and the fourth sidewall 32114 have a protrusion 32115 on their adjacent sides; the second mounting block 322 has a second recess 3222 on its sidewall near the second mounting groove 3211; the second recess 3222 and the protrusion 32115 are fitted together. Thus, when the second mounting block 322 extends into the second mounting groove 3211, the second recess 3222 and the protrusion 32115 fit together, making the fixation between the second mounting block 322 and the first mounting block 321 more secure.

[0047] In some implementations, see Figure 1 The feeding mechanism 4 includes a test platform 41, a feed motor 42, a feed screw 43, a feed platform 44, and a clamping assembly 45. The feed screw 43 is rotatably connected to the test platform 41, and its axial direction is perpendicular to the rotation axis of the rotating disk 3. The feed platform 44 is threadedly connected to the feed screw 43 and slidably connected to the test platform 41. The clamping assembly 45 is mounted on the feed platform 44 and is used to fix the casing 2. The feed motor 42 drives the feed screw 43 to rotate. Specifically, when it is necessary to drive the casing 2 to approach and contact the blade crown on the turbine blade 1, the feed motor 42 is turned on. The rotation of the feed motor 42 drives the feed screw 43 to move, which in turn drives the feed platform 44 to move. The movement of the feed platform 44 causes the clamping assembly 45 to move, which in turn drives the casing 2 to move, gradually bringing the casing 2 closer to the turbine blade 1. This achieves the purpose of contact between the casing 2 and the blade crown of the turbine blade 1.

[0048] As an example, see Figure 1 In some embodiments, a reducer 48 can be provided between the feed motor 42 and the feed screw 43. The reducer 48 can control the speed of the feed motor 42 so that the feed motor 42 provides a lower speed and a higher torque to the feed screw 43, thereby enabling precise control of the movement of the feed platform 44.

[0049] It should be noted that in this embodiment, the clamping assembly 45 is used to fix the housing 2, and the specific structure of the clamping assembly 45 is not limited. As an example, the clamping assembly 45 may include opposing fixing plates and fixing bolts for fixing the opposing plates (not specifically shown in the accompanying drawings). The fixing plates can slide on the feed platform 44, and the opposing fixing plates have clamping space for the housing 2. Specifically, when it is necessary to fix the housing 2, the housing 2 is placed between the two fixing plates, the fixing plates are moved, and the fixing plates contact one side of the housing 2. When the fixing plates are pressed against the housing 2, the housing 2 is fixed between the two fixing plates by the fixing bolts.

[0050] In some embodiments, the feed mechanism 4 further includes a force gauge 46 and a cooler 47; the force gauge 46 is mounted on the feed platform 44 and is used to detect the load on the turbine blade 1 and the casing 2; the cooler 47 is configured to control the test temperature of the turbine blade 1 and the casing 2. The cooler 47 can control the temperature changes during the test to ensure that the test device and the turbine blade 1 and the casing 2 operate within a suitable temperature range, avoiding overheating that could affect the test results.

[0051] In this implementation, the force gauge 46 can monitor and measure the changes in test load in real time, ensuring the accuracy of the mechanical data of turbine blade 1 and casing 2 during the impact and rubbing process, and providing a more accurate basis for subsequent data analysis and damage analysis.

[0052] In some implementations, see Figure 7 The test apparatus also includes a heating mechanism 6; the heating mechanism 6 includes an annular heating tube 62 and a heating bracket 61; the heating bracket 61 is located on one side of the rotating disk 3; the annular heating tube 62 is located on the heating bracket 61 and is used to heat the rotating disk 3.

[0053] In this embodiment, the heating mechanism 6 uses an annular heating tube 62 to heat the rotating disk 3, which solves many problems existing in traditional gas heating methods. The annular heating tube 62 has several advantages over traditional heating methods, such as providing better solutions in terms of heating efficiency, accuracy, and uniformity.

[0054] Furthermore, the annular heating tube 62 can evenly distribute heat around the rotating disk 3, ensuring uniform heat distribution during the heating process. This design effectively avoids localized overheating or uneven heating that can occur with traditional gas heating due to uneven flame distribution. In traditional gas heating, it is difficult to achieve a completely uniform flame distribution, which may lead to some areas being overheated while others are underheated, thus affecting the accuracy and consistency of the test results. However, the annular heating tube 62 ensures that all parts of the rotating disk 3 are heated evenly, helping to maintain temperature uniformity throughout the heating process.

[0055] Regarding experimental accuracy, the use of annular heating tube 62 provides more precise temperature control compared to traditional flame heating methods. In this embodiment, both the power and heating time of the annular heating tube 62 are adjustable, allowing operators to finely adjust them according to actual needs to achieve the desired temperature profile. This precise control capability enables the device to more realistically simulate the working state of blades in high-temperature environments, especially under high-temperature, high-speed operating conditions, better meeting the requirements for fine-tuning the heating process.

[0056] Regarding experimental safety, the electric heating method of the annular heating tube 62 avoids the use of open flames, thus making operation safer. Traditional gas heating not only presents problems such as difficulty in flame control and a high risk of fire, but also, because the flame directly contacts the surface of the device, it may damage the equipment or affect the stability of the experiment. The design of using an annular lamp tube heating eliminates this safety hazard, reduces the risk of gas leakage or fire, and thus greatly improves the safety of experimental operations.

[0057] In terms of testing efficiency, the annular heating tube 62 has a higher heating efficiency than traditional gas-fired heating methods. It can reach the required operating temperature more quickly, reducing energy waste and improving overall energy efficiency. Its energy-saving characteristics are particularly prominent during high-temperature testing, helping to reduce testing costs and promoting long-term stable operation of the equipment.

[0058] In summary, the annular heating tube provided by this disclosure outperforms traditional gas heating methods in terms of uniformity, accuracy, and safety during the heating process, significantly improving upon the shortcomings of traditional heating methods. By providing more stable and precise heating control, it not only enhances the safety and efficiency of experiments but also improves the simulation accuracy of blade behavior under high-temperature environments. This heating mechanism 6 is particularly suitable for experimental scenarios requiring high-temperature and high-speed simulation, meeting the requirements for high stability and controllability of the heating process, and can be widely applied to related research and testing in fields such as aerospace and turbine engines.

[0059] As an example, the annular heating tube 62 can be a ring-shaped quartz lamp. By setting the annular heating tube 62 to a ring-shaped quartz lamp, it is possible to heat the rotating sample and precisely control the temperature, ensuring uniform heat distribution during the heating process. Compared with traditional heating methods, the ring heating device can improve temperature control accuracy, ensure temperature stability during the test, and thus improve the reliability and accuracy of the test results.

[0060] See Figure 8 In this embodiment of the disclosure, a method for testing the impact rubbing of a turbine blade 1 is also provided, the method comprising: S1: Provide turbine blade 1 sample and casing 2 sample.

[0061] S2: Turbine blade 1 specimen is fixed on rotating disk 3.

[0062] S3: The sample of the casing 2 is fixed on the feeding mechanism 4.

[0063] S4: The heating mechanism 6 provides heat to the rotating disk 3. Specifically, the heating mechanism 6 provides a high temperature of 500~2000℃ to the rotating disk 3 to simulate the temperature changes in actual operation.

[0064] S5: The feed mechanism 4 drives the sample in the casing 2 to move, and the sample in the casing 2 comes into contact with the blade crown of the turbine blade 1.

[0065] S6: Rotating mechanism 5 drives rotating disk 3 to move.

[0066] In this experiment, a force gauge 46 was used to monitor the load changes of the turbine blade 1 and casing 2 in real time during the impact-wear process, providing data support for wear and damage analysis. Meanwhile, to prevent overheating from affecting the test results, a cooler 47 was used to regulate the temperature of the sample and equipment, ensuring they operate within a suitable temperature range.

[0067] It should be noted that the order of steps S2 and S3 in this test method can be adjusted, and there is no specific restriction on the order of fixing turbine blade 1 and casing 2.

[0068] After the experiment, several key data points can be recorded for further analysis. These include, for example, rotational speed, blade tip linear velocity, blade tip-casing 2 contact load, feed data, and temperature. Furthermore, deformation, morphology, and composition analyses of the blades before and after the experiment were performed. Analysis of this data allows for in-depth research into wear, damage, and the interaction between the blades and casing 2 during the impact-grip process, providing crucial information for the design, performance optimization, and material selection of turbine blade 1.

[0069] In summary, this application achieves high-precision reproduction of the contact friction behavior of turbine blade 1 and casing 2 under extreme conditions of high temperature, high pressure, and high speed. Through an integrated closed-loop temperature-controlled annular radiant heating system, the isotropic characteristics of the heat load distribution are effectively guaranteed. Regarding the dynamic interference process between turbine blade 1 and casing 2, the collision-grip process between the turbine blade 1's blade tip and casing 2 under high-speed rotation conditions was simulated. This helps in studying the mechanical response and failure mode of the turbine blade 1's blade tip under collision-grip conditions.

[0070] Other embodiments of this disclosure will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of this disclosure are indicated by the appended claims.

Claims

1. A turbine blade abrasion test apparatus for conducting abrasion tests between the turbine blade and the casing; characterized in that, The test apparatus includes a rotating disk, a feeding mechanism, a rotating mechanism, and a heating mechanism; The rotating disk is mounted on the rotating mechanism, and the rotating mechanism is used to drive the rotating disk to rotate. The rotating disk has a clamping assembly for clamping the turbine blades; The feeding mechanism is located on one side of the rotating mechanism, and the housing is connected to the feeding mechanism. The feeding mechanism is used to drive the housing to move so that the housing contacts the blade crown of the turbine blade. The heating mechanism is located on one side of the rotating disk and is used to heat the rotating disk.

2. The turbine blade rubbing test apparatus according to claim 1, characterized in that, The clamping assembly includes a first mounting block, a second mounting block, and a fixing member; The rotating disk has a first mounting groove distributed along its circumference on its peripheral side, and the first mounting block is slidably connected in the first mounting groove. The sliding direction of the first mounting block is perpendicular to the rotation direction of the rotating disk. The first mounting block has a second mounting groove on the side away from the rotating disk, and the second mounting block is slidably connected in the second mounting groove. The sliding direction of the second mounting block is the same as the sliding direction of the first mounting block. The second mounting block has a third mounting groove on the side away from the first mounting block, and the turbine blade is fixed in the third mounting groove by the fastener.

3. The turbine blade rubbing test apparatus according to claim 2, characterized in that, The first mounting groove has a first opening, a first bottom wall, a first side wall, and a second side wall; Along one side of the first bottom wall to one side of the first opening, the distance between the first sidewall and the second sidewall gradually decreases.

4. The turbine blade rubbing test apparatus according to claim 3, characterized in that, The first mounting block has a first recess near at least one of the first sidewall and the second sidewall, wherein the first recess is configured to cooperate with the corresponding sidewall.

5. The turbine blade rubbing test apparatus according to claim 2, characterized in that, The second mounting groove has a second opening, a second bottom wall, a third side wall, and a fourth side wall; Along the second bottom wall side to the second opening side, the distance between the third side wall and the fourth side wall gradually decreases.

6. The turbine blade rubbing test apparatus according to claim 5, characterized in that, The third sidewall and the fourth sidewall have a protrusion on the side that are close to each other; The second mounting block has a second recess on its side wall near the second mounting groove; The second recessed portion is configured to cooperate with the protruding portion.

7. The turbine blade rubbing test apparatus according to claim 1, characterized in that, The feeding mechanism includes a test platform, a feeding motor, a feeding screw, a feeding platform, and a clamping assembly; The feed screw is rotatably connected to the test platform, and the axial direction of the feed screw is perpendicular to the rotation axis of the rotating disk; The feed platform is threadedly connected to the feed screw and slidably connected to the test platform; The feed motor is used to drive the feed screw to rotate; The clamping assembly is located on the feed platform and is used to fix the housing.

8. The turbine blade rubbing test apparatus according to claim 7, characterized in that, The feeding mechanism also includes a force gauge and a cooler; The force gauge is mounted on the feed platform and is used to detect the load on the turbine blades and the casing. The cooler is configured to control the test temperature of the turbine blades and the casing.

9. The turbine blade rubbing test apparatus according to claim 1, characterized in that, The heating mechanism includes an annular heating tube and a heating bracket; The heating bracket is located on one side of the rotating disk; The annular heating tube is mounted on the heating bracket and is used to heat the rotating disk.

10. A method for testing the impact and rubbing of turbine blades, characterized in that, The test method includes: Turbine blade samples and casing samples are provided; The turbine blade sample was fixed on the rotating disk; The casing sample is fixed on the feeding mechanism; The heating mechanism provides heat to the rotating disk; The feeding mechanism pushes the casing sample to move, and the casing sample contacts the blade crown of the turbine blade; The rotating mechanism drives the rotating disk to move.

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