Split turbine blade cascade experimental device

Abstract

The present invention discloses a split turbine blade array experimental device, comprising a base, a plurality of blade arrays and a plurality of correction blocks. A positioning hole for movably inserting the blade array is provided on the base, the inner wall shape of the positioning hole is adapted to the outer wall shape of the blade array, the positioning hole and the blade array are arranged in a one-to-one correspondence, the outer contour of the correction block is adapted to the inner wall contour of a preset airflow channel in a casing, the plurality of correction blocks are arranged on the base at intervals, two adjacent correction blocks are enclosed to form a correction channel for inserting the blade array into the positioning hole and then being sleeved outside the blade array to correct the placement angle and position of the blade array, the blade array is inserted into the positioning hole and corrected by the correction block and then detachably connected to the base, the blade array comprises a detachably connected blade body and a blade tip.

Description

Technical Field

[0001] The present invention relates to the technical field of blade cascade experimental devices, in particular to a split turbine blade cascade experimental device. Background Art

[0002] After the design of an aircraft engine turbine blade is completed, the aerodynamic performance of the designed turbine blade needs to be evaluated. The current method is to conduct a turbine plane blade cascade test with the casing in a static state. The blade cascade test is used to verify the performance level of the turbine blade in advance. That is, the loss characteristics, pressure distribution, flow field in the blade tip clearance, and flow function of the turbine blade cascade are experimentally measured. The experimental data obtained can provide data support for subsequent optimization design, whole machine matching, and tool verification to a certain extent. Generally, multiple turbine blade schemes are designed and verified by multiple rounds of turbine blade cascade tests to find the optimal design.

[0003] However, when blade cascade tests with different blade shapes, different blade tip geometries or different blade tip clearances are required, multiple sets of blade cascade test pieces of the same type need to be reprocessed. In the entire turbine blade cascade test cycle, the processing and assembly of the blade cascade test pieces takes the longest time. The design, processing and assembly of the blade cascade test pieces consumes a lot of manpower, financial resources and time, resulting in a long design cycle and poor economy of the aircraft engine. Summary of the Invention

[0004] The present invention provides a split turbine blade cascade test device to solve the technical problem that the existing turbine blade cascade test consumes a lot of manpower, material resources and materials, resulting in a long design cycle of aircraft engines and poor economy.

[0005] According to one aspect of the present invention, a split turbine blade experimental device is provided, comprising a base, a plurality of blades and a plurality of correction blocks, wherein a positioning hole for movably inserting the blade is opened on the base, the inner wall shape of the positioning hole is adapted to the outer wall shape of the blade, the positioning hole and the blade are arranged in a one-to-one correspondence, the outer contour of the correction block is adapted to the inner wall contour of a preset airflow channel in the casing, the plurality of correction blocks are arranged on the base at intervals, and two adjacent correction blocks are enclosed to form a correction channel for inserting the blade into the positioning hole and then being sleeved on the outside of the blade to correct the placement angle and position of the blade, the blade is inserted into the positioning hole and corrected by the correction block and then detachably connected to the base, and the blade includes a detachably connected blade body and a blade tip.

[0006] As a further improvement of the above technical solution:

[0007] Furthermore, the split turbine blade experimental device also includes a moving end wall simulation system for simulating the relative movement between the casing and the blade. The moving end wall simulation system includes a mounting bracket, an angle of attack matching adjustment mechanism arranged on the mounting bracket, and a moving end wall simulation component arranged in the angle of attack matching adjustment mechanism for driving the casing to move relative to the blade. The base is arranged in the moving end wall simulation component, and the angle of attack matching adjustment mechanism is used to drive the moving end wall simulation component to rotate so that the blade inlet angle of attack matches the preset inlet angle of attack.

[0008] Furthermore, the moving end wall simulation component includes a mounting shell, a belt rotating member arranged in the mounting shell, and a driving mechanism arranged in the mounting shell for driving the belt rotating member to rotate, and the base is arranged in the belt rotating member.

[0009] Furthermore, a cascade leading edge line passing through the leading edges of the plurality of cascades is arranged on the base, and the cascade leading edge line passes through the rotation center of the attack angle matching adjustment mechanism.

[0010] Furthermore, the base is provided with a bottom plate front edge which is arranged close to the frontal line of the cascade front edge and is parallel to the frontal line of the cascade front edge.

[0011] Furthermore, the distance between the front line of the leading edge of the cascade and the leading edge of the base plate is 20 mm to 25 mm.

[0012] Furthermore, a plug-in gap for assembly is provided between the positioning hole and the blade grid, and the plug-in gap has a value of 0.05 mm to 0.10 mm.

[0013] Furthermore, the machining accuracy of the outer contour of the correction block is 0.02 mm to 0.03 mm.

[0014] Furthermore, a display scale for displaying the insertion depth is provided on the blade body.

[0015] Furthermore, a clamping groove is concavely provided at the end of the blade body facing the blade tip, and a clamping protrusion is convexly provided at the end of the blade tip facing the blade body and is clamped and connected with the clamping groove.

[0016] The present invention has the following beneficial effects:

[0017] The split turbine blade test device of the present invention can carry out multiple blade tests simultaneously by plugging multiple blades into the corresponding positioning holes of the base one by one when conducting turbine plane blade tests, thereby greatly improving the test efficiency and ensuring the accuracy of the test results. Moreover, by adjusting the depth of the blades plugged into the positioning holes, the test of blades with different blade tip clearances can be realized. Moreover, since the plug-in experiments are all carried out through the base plate, there are no other factors interfering, and the stability of the test results is guaranteed to the greatest extent. After the blades are plugged into the positioning holes, the outer contour of the correction block is adapted to the inner wall contour of the preset airflow channel in the casing. The correction channel is sleeved outside the blade to correct the placement angle and position of the blade, so as to simulate the state of the blade in the preset airflow channel in the casing, thereby improving the reliability of the experimental results. Reliability, and then the base and the blade cascade are connected to carry out subsequent blade cascade experiments. After the blade cascade experiment is completed, the blade cascade experiment with different blade shapes can be realized by replacing different blade shapes and detachably connecting with the base. The blade cascade adopts a split structure, which is composed of a blade body and a blade tip. By replacing blade tips of different shapes and detachably connecting with the blade body, the blade cascade experiment with blade tips of different shapes can be realized. This solution cooperates with each other through the base, the blade cascade and the correction block. When conducting blade cascade experiments with different tip clearances, different blade shapes and different blade tip geometries, it can be completed through a set of split turbine blade cascade experimental equipment. It has strong versatility, greatly reduces the experimental cost, shortens the design cycle of aircraft engines, has good economy, and the experimental results are reliable and practical, suitable for wide promotion and application.

[0018] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0020] Figure 1 2 is a schematic structural diagram of a split turbine blade cascade experimental device according to a preferred embodiment of the present invention;

[0021] Figure 2 1. It is an exploded schematic diagram of a split turbine blade cascade experimental device according to a preferred embodiment of the present invention;

[0022] Figure 3 1. It is a structural schematic diagram of the base in the split turbine blade cascade experimental device of the preferred embodiment of the present invention;

[0023] Figure 4 1. It is an exploded schematic diagram of a cascade in a split turbine cascade experimental device according to a preferred embodiment of the present invention;

[0024] Figure 5 This is a schematic diagram of the structure of the moving end wall simulation system in the split turbine blade cascade experimental device of the preferred embodiment of the present invention.

[0025] 100. Base; 110. Positioning hole; 120. Blade leading edge line; 130. Base plate leading edge; 200. Blade; 210. Blade body; 220. Blade tip; 300. Correction block; 400. Motion end wall simulation system; 410. Mounting bracket; 420. Attack angle matching adjustment mechanism; 430. Motion end wall simulation assembly. DETAILED DESCRIPTION

[0026] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0027] Figure 1 2 is a schematic structural diagram of a split turbine blade cascade experimental device according to a preferred embodiment of the present invention; Figure 2 1. It is an exploded schematic diagram of a split turbine blade cascade experimental device according to a preferred embodiment of the present invention; Figure 3 1. It is a structural schematic diagram of the base in the split turbine blade cascade experimental device of the preferred embodiment of the present invention; Figure 4 1. It is an exploded schematic diagram of a cascade in a split turbine cascade experimental device according to a preferred embodiment of the present invention; Figure 5 It is a structural schematic diagram of a moving end wall simulation system in a split turbine blade cascade experimental device according to a preferred embodiment of the present invention.

[0028] like Figures 1-4As shown, the split turbine blade experimental device of this embodiment includes a base 100, multiple blades 200 and multiple correction blocks 300. The base 100 is provided with a positioning hole 110 for the blade 200 to be movably inserted. The inner wall shape of the positioning hole 110 is adapted to the outer wall shape of the blade 200. The positioning hole 110 and the blade 200 are arranged in a one-to-one correspondence. The outer contour of the correction block 300 is used to adapt to the inner wall contour of the preset airflow channel in the casing. Multiple correction blocks 300 are arranged at intervals on the base 100. Two adjacent correction blocks 300 are enclosed to form a correction channel for the blade 200 to be inserted into the positioning hole 110 and then sleeved on the outside of the blade 200 to correct the placement angle and position of the blade 200. The blade 200 is inserted into the positioning hole 110 and corrected by the correction block 300 and then detachably connected to the base 100. The blade 200 includes a detachably connected blade body 210 and a blade tip 220. Specifically, the split turbine blade experimental device of the present invention, when conducting a turbine plane blade cascade 200 experiment, can simultaneously conduct multiple blade cascade 200 experiments by plugging multiple blade cascades 200 one by one into the corresponding positioning holes 110 of the base 100, thereby greatly improving the experimental efficiency and ensuring the accuracy of the experimental results. By adjusting the depth of the blade cascade 200 inserted into the positioning hole 110, the experiment of the blade cascade 200 with different blade tip 220 gaps can be realized. Since the plug-in experiments are all performed through the base plate, there is no interference from other factors, and the stability of the experimental results is guaranteed to the greatest extent. After the blade cascade 200 is inserted into the positioning hole 110, the outer contour of the correction block 300 is adapted to the inner wall contour of the preset airflow channel in the casing, and the two adjacent correction blocks 300 are enclosed to form a correction channel. The correction channel is sleeved outside the blade cascade 200 to correct the placement angle and position of the blade cascade 200 to simulate the state of the blade 200 when it is in the preset airflow channel in the casing, thereby improving the experimental results. The reliability of the test results is then ensured, and the base 100 and the cascade 200 are connected to carry out subsequent cascade 200 tests. After the cascade 200 test is completed, by replacing different blade shapes and detachably connecting with the base 100, the cascade 200 test of different blade shapes can be realized. The cascade 200 adopts a split structure, which is composed of a blade body 210 and a blade tip 220 connected. By replacing the blade tip 220 of different shapes and detachably connecting with the blade body 210, the cascade 200 test of blade tips 220 of different shapes can be realized. In this solution, the base 100, the cascade 200 and the correction block 300 cooperate with each other. When conducting cascade 200 tests with different blade tip 220 gaps, different blade shapes and different blade tip 220 geometric shapes, a set of split turbine cascade test devices can be used to complete the test. The solution has strong versatility, greatly reduces the experimental cost, shortens the design cycle of the aircraft engine, has good economy, and the experimental results are reliable and practical, which is suitable for wide promotion and application. It should be understood that the preset airflow path refers to the airflow path where the cascade 200 is located when it is inside the aircraft engine.It should be understood that the clearance of the blade tip 220 of the cascade 200 refers to the clearance between the blade tip 220 and the airflow channel when the cascade 200 is in the casing.

[0029] like Figure 5 As shown, in this embodiment, the split turbine blade cascade test apparatus also includes a moving endwall simulation system 400 for simulating the relative motion between the casing and the blade cascade 200. The moving endwall simulation system 400 includes a mounting bracket 410, an angle of attack matching adjustment mechanism 420 disposed on the mounting bracket 410, and a moving endwall simulation assembly 430 disposed within the angle of attack matching adjustment mechanism 420 for driving the casing to move relative to the blade cascade 200. The base 100 is disposed within the moving endwall simulation assembly 430. The angle of attack matching adjustment mechanism 420 is used to drive the moving endwall simulation assembly 430 to rotate so that the inlet angle of attack of the blade cascade 200 matches a preset inlet angle of attack. It should be understood that turbine blade cascade experiments are generally conducted with the casing stationary. The turbine rotor blade characteristics obtained from the experiments have certain defects and do not take into account the relative motion of the actual casing. Therefore, the flow field within the rotor gap differs from that of an actual turbine and cannot reflect the aerodynamic performance of the blade cascade under actual operating conditions. Specifically, after the cascade blades 200 are plugged into the base 100 and the base 100 is placed within the moving end wall simulation assembly 430, the moving end wall simulation assembly 430 drives the casing to move relative to the cascade blades 200, realistically simulating the relative motion between the casing and the cascade blades 200. Furthermore, the angle of attack matching adjustment mechanism 420 drives the moving end wall simulation assembly 430 to rotate, indirectly driving the base 100 to rotate, so that the inlet angle of attack of the cascade blades 200 on the base 100 matches the preset inlet angle of attack, thereby simulating the actual operating state of the cascade blades 200 within the casing and improving the reliability of the experimental results of the cascade blades 200. It should be understood that the preset inlet angle of attack refers to the inlet angle of attack of the cascade blades 200 when they are within the casing. It should be understood that the intake angle of attack of the cascade vanes 200 varies at different positions within the casing. Specifically, the intake angle of attack of the cascade vanes 200 is adjusted by the intake angle of attack matching adjustment assembly to match the intake angle of attack at different positions within the casing, thereby avoiding multiple cascade vane 200 experiments and improving experimental efficiency. Optionally, the angle of attack matching adjustment mechanism 420 includes a drive motor disposed on the mounting bracket 410, with an output shaft connected to the moving endwall simulation assembly 430, for driving the moving endwall simulation assembly 430 to rotate. Optionally, the mounting bracket 410 is movably disposed.

[0030] like Figure 5As shown, in this embodiment, the motion end wall simulation assembly 430 includes a mounting housing, a belt rotating member disposed within the mounting housing, and a driving mechanism disposed within the mounting housing for driving the belt rotating member to rotate. The base 100 is disposed within the belt rotating member. Specifically, the driving mechanism drives the belt rotating member to rotate. The base 100 is disposed within the belt rotating member and remains stationary relative to the belt rotating member, thereby simulating the relative motion between the casing and the blade cascade 200. Optionally, the driving mechanism is a motor connected to the belt rotating member via gear engagement or a pulley. Optionally, the belt rotating member includes two rollers disposed relative to each other and a motion simulation belt that rotates around the two rollers, one of which is connected to the driving mechanism. Optionally, an amplitude suppression plate is disposed within the belt rotating member to suppress vibrations of the motion simulation belt. Optionally, the belt rotating member also includes a tensioning member for pressing against the motion simulation belt to maintain tension.

[0031] like Figure 3 As shown, in this embodiment, a cascade leading edge line 120 is disposed on the base 100 and passes through the leading edges of the plurality of cascade blades 200. The cascade leading edge line 120 passes through the rotation center of the angle of attack matching adjustment mechanism 420. Specifically, the cascade leading edge line 120 passes through the rotation center of the angle of attack matching adjustment mechanism 420 to facilitate calculation and adjustment of the inlet angle of attack of the cascade blades 200.

[0032] like Figure 3 As shown, in this embodiment, the base 100 is provided with a bottom plate leading edge 130 disposed near and parallel to the cascade leading edge line 120. Specifically, by keeping the bottom plate leading edge 130 parallel to the cascade leading edge line 120, after the current cascade 200 test is completed, when the next set of cascades 200 is tested, the setting deviation of the zero position of the inlet angle of attack of the cascade 200 can be controlled.

[0033] In this embodiment, the distance between the cascade leading edge line 120 and the base plate leading edge 130 is 20 mm to 25 mm. It should be understood that during the cascade test, a suction boundary layer structure exists in front of the base plate leading edge 130 of the base 100. When the distance between the cascade leading edge line 120 and the base plate leading edge 130 is between 20 mm and 25 mm, the airflow after the suction boundary layer cannot form a new boundary layer within a short distance. Therefore, the cascade leading edge line 120 can be indirectly measured by measuring the base plate leading edge 130, reducing the measurement and conversion of cascade surface parameters. When the distance between the cascade leading edge line 120 and the base plate leading edge 130 is greater than 25 mm, a new boundary layer may form, increasing the measurement of cascade surface parameters. When the distance between the cascade leading edge line 120 and the base plate leading edge 130 is less than 20 mm, the width of the base 100 is reduced, and reliability is reduced.

[0034] In this embodiment, a gap for assembly is provided between the positioning hole 110 and the blade cascade 200. The gap is set between 0.05 mm and 0.10 mm. Specifically, when the gap is between 0.05 mm and 0.10 mm, the blade cascade 200 is easy to assemble and has high positioning accuracy. When the gap is less than 0.05 mm, the blade cascade 200 is difficult to assemble, which increases assembly time and reduces experimental efficiency. When the gap is greater than 0.10 mm, the positioning accuracy of the blade cascade 200 deviates significantly, and the reliability of the experimental results is low.

[0035] In this embodiment, the machining accuracy of the outer contour of the calibration block 300 is 0.02mm-0.03mm. Specifically, when the machining accuracy of the outer contour of the calibration block 300 is between 0.02mm and 0.03mm, the consistency and uniformity of the blade 200 within the calibration channel are ensured to be good, and the reliability of the experimental results is high. When the machining accuracy of the outer contour of the calibration block 300 is less than 0.02mm, the manufacturing difficulty of the calibration block 300 is too great, and the economic efficiency is low. When the machining accuracy of the outer contour of the calibration block 300 is greater than 0.03mm, the consistency and uniformity of the blade 200 within the calibration channel are poor, and the reliability of the experimental results is low.

[0036] In this embodiment, a display scale for displaying the insertion depth is arranged on the blade body 210. Specifically, the display scale displays the insertion depth of the blade cascade 200 into the positioning hole 110, which facilitates the adjustment of the blade tip 220 clearance of the blade cascade 200.

[0037] In this embodiment, a snap-fit ​​groove is recessed at the end of the blade body 210 facing the blade tip 220, and a snap-fit ​​protrusion is protruded from the end of the blade tip 220 facing the blade body 210 to engage with the snap-fit ​​groove. Specifically, the snap-fit ​​groove and snap-fit ​​protrusion provide a snap-fit ​​connection, facilitating the connection and separation of the blade body 210 and the blade tip 220.

[0038] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A split turbine blade experimental device, characterized in that: The invention comprises a base (100), a plurality of blade cascades (200) and a plurality of correction blocks (300). The base (100) is provided with a positioning hole (110) for movably inserting the blade cascade (200). The inner wall shape of the positioning hole (110) is adapted to the outer wall shape of the blade cascade (200). The positioning hole (110) and the blade cascade (200) are arranged in a one-to-one correspondence. The outer contour of the correction block (300) is adapted to the inner wall contour of a preset air flow channel in the casing. The plurality of correction blocks (300) are spaced apart. Arranged on the base (100), two adjacent correction blocks (300) enclose to form a correction channel. The correction channel is used for the blade (200) to be inserted into the positioning hole (110) and then sleeved outside the blade (200) to correct the placement angle and position of the blade (200). After the blade (200) is inserted into the positioning hole (110) and corrected by the correction block (300), it is detachably connected to the base (100). The blade (200) includes a detachably connected blade body (210) and a blade tip (220).

2. The split turbine blade experimental device according to claim 1, characterized in that: The split turbine blade cascade experimental device also includes a moving end wall simulation system (400) for simulating relative motion between a casing and a blade cascade (200). The moving end wall simulation system (400) includes a mounting bracket (410), an angle of attack matching adjustment mechanism (420) arranged on the mounting bracket (410), and a moving end wall simulation component (430) arranged in the angle of attack matching adjustment mechanism (420) for driving the casing to move relative to the blade cascade (200). The base (100) is arranged in the moving end wall simulation component (430). The angle of attack matching adjustment mechanism (420) is used to drive the moving end wall simulation component (430) to rotate so that the inlet angle of attack of the blade cascade (200) matches a preset inlet angle of attack.

3. The split turbine blade experimental device according to claim 2, characterized in that: The moving end wall simulation component (430) comprises a mounting shell, a belt rotating member arranged in the mounting shell, and a driving mechanism arranged in the mounting shell for driving the belt rotating member to rotate. The base (100) is arranged in the belt rotating member.

4. The split turbine blade cascade experimental device according to claim 2, characterized in that: A cascade leading edge line (120) passing through the leading edges of the plurality of cascades (200) is arranged on the base (100), and the cascade leading edge line (120) passes through the rotation center of the attack angle matching adjustment mechanism (420).

5. The split turbine blade cascade experimental device according to claim 4, characterized in that: The base (100) is provided with a bottom plate front edge (130) arranged close to the cascade front edge line (120) and parallel to the cascade front edge line (120).

6. The split turbine blade cascade experimental device according to claim 5, characterized in that: The distance between the leading edge line (120) of the cascade and the leading edge (130) of the base plate is 20 mm to 25 mm.

7. The split turbine blade cascade experimental device according to any one of claims 1 to 6, characterized in that: A plug-in gap for assembly is provided between the positioning hole (110) and the blade grid (200), and the value of the plug-in gap is 0.05 mm to 0.10 mm.

8. The split turbine blade cascade experimental device according to any one of claims 1 to 6, characterized in that The machining accuracy of the outer contour of the correction block (300) is 0.02 mm to 0.03 mm.

9. The split turbine blade cascade experimental device according to any one of claims 1 to 6, characterized in that: A display scale for displaying the insertion depth is arranged on the blade body (210).

10. The split turbine blade cascade experimental device according to any one of claims 1 to 6, characterized in that: The end of the blade body (210) facing the blade tip (220) is concavely provided with a clamping groove, and the end of the blade tip (220) facing the blade body (210) is convexly provided with a clamping protrusion clamped and connected with the clamping groove.

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