Gas turbine gas path parameter response test method under random excitation and experimental device

Abstract

The invention relates to the technical field of gas turbine gas path parameter testing, particularly discloses a gas turbine gas path parameter response testing method under random excitation and an experimental device, and aims to solve the problem that gas path parameter response testing is difficult under the random excitation effect in the prior art. Comprising a first test tube body and a second test part, a mounting part for fixing a gas turbine blade is arranged between the first test tube body and the second test part, two fixing bases are symmetrically arranged at the lower end of the second test part, the fixing bases are connected with the second test part through supporting legs, and the supporting legs are connected with the first test tube body and the second test tube body. According to the present invention, the corresponding airflow is modulated according to the existing requirements, the test requirements of the gas path parameter response when the random airflow excitation with different intensities acts on the blade are met, and the test application range is improved; meanwhile, multiple sets of gas turbine blades can be fixed, in addition, the included angle between the blades and airflow can be adjusted according to needs, more test data can be obtained, and the machining efficiency is effectively improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine gas path parameter testing, in particular to a gas turbine gas path parameter response testing method and an experimental device under random excitation. Background Art

[0002] Because gas turbines operate at high speeds, the blade tips are subject to complex forces in contact with the working gas, potentially causing wear or damage due to aerodynamic loads, centrifugal forces, or friction or impact between the blade tips and the casing. Tip drop typically affects the aerodynamic performance of the blades, reducing gas turbine efficiency. In the latter stages of the compressor, the airflow velocity may approach or exceed the speed of sound due to compression effects and high-pressure conditions, leading to the formation of shock waves. The appearance of shock waves can cause drastic changes in local airflow pressure, temperature, and velocity, generating very complex aerodynamic loads.

[0003] Under transonic conditions, the airflow decelerates from subsonic to supersonic or from supersonic to subsonic, usually accompanied by the generation of shock waves. A shock wave is an area of sudden pressure, temperature, and density changes in the airflow, and is the result of airflow acceleration and deceleration. Impact on the blades: The shock wave action will produce violent aerodynamic shocks in certain areas of the blades, especially in the blade tips. Due to the concentration of aerodynamic stress, this shock will accelerate fatigue damage to the blade material. In addition, after degassing, part of the gas is extracted, and the total downstream airflow rate is reduced. This may cause the overall airflow speed of the blade to decrease, especially in the blade tip area, where the Mach number is reduced, which may reduce the probability of transonic or supersonic airflow (such as shock waves), thereby reducing tip stress. Shock waves may cause the blade tip to be subjected to high stress loads for a short period of time, and the tip stress decreases after degassing. Such repeated unstable flow leads to fatigue cracks at the blade tip, and then corner loss occurs.

[0004] In order to detect the impact of random airflow excitation on blades, the existing patent publication number CN116539267A discloses a simulation test device for gas turbine foreign object damage. The device can simulate the foreign object damage process and damage characteristics of the gas turbine in a rotating state. However, if the test object is replaced with a gas turbine, the device cannot rectify the airflow, the test is too simple, and it is inconvenient to fix the gas turbine blades.

[0005] Based on this, a gas turbine gas path parameter response test method and experimental device under random excitation are now provided, which can eliminate the disadvantages of existing devices. Summary of the Invention

[0006] The purpose of the present invention is to provide a method and an experimental device for testing the gas path parameter response of a gas turbine under random excitation, which solves the problem of poor testing effect in the prior art.

[0007] To achieve the above object, the present invention provides the following technical solutions:

[0008] An experimental device for testing the gas turbine gas path parameter response under random excitation includes a first test tube body and a second test component. A mounting component for fixing the blades is provided between the first test tube body and the second test component. Two fixed bases are symmetrically provided at the lower end of the second test component. The fixed bases are connected to the second test component through legs. The first test tube body is connected to a first separation component for driving it away from the mounting component. After the first separation component drives the first test tube body to separate from the mounting component, it is convenient to install and fix the blades. The other end of the second test component is connected to an air supply pipe. An adjustment component for adjusting the airflow is provided at the end of the second test component. A gas supply component for providing gas is provided on the gas supply pipe. The gas supply pipe is connected to a second separation component for driving it away from the second test component.

[0009] On the basis of the above technical solutions, the present invention also provides the following optional technical solutions:

[0010] In an optional solution: the second separation component includes a second horizontal push rod fixedly connected to the fixed base, the lower end of the air supply pipe is connected to the second movable base through a positioning leg, the output end of the second horizontal push rod is connected to the second movable base, and walking wheels are symmetrically provided at both ends of the second movable base. Two second horizontal guide rods are slidingly provided on the second movable base, and the ends of the second horizontal guide rods are connected to the fixed base.

[0011] In an optional solution: the air supply assembly includes a compressed air supply box group arranged above the air supply pipe, the air supply end of the compressed air supply box group is connected to the air inlet end of the air supply pipe through an inflation pipe, an air storage chamber is provided inside the air supply pipe, an isolation plate is provided in the air storage chamber, a vent hole is provided at the center position of the isolation plate, a blocking block is provided at the position of the vent hole, the blocking block is connected to the output end of the blocking push rod, and the blocking push rod is installed on the air supply pipe.

[0012] In an optional solution: the adjustment assembly includes a debugging tube fixedly connected to the second test component, the debugging tube is connected to the second test component through a connecting end plate, a debugging installation cavity is opened at the end of the debugging tube, an adjustment inner cylinder is provided in the debugging installation cavity, and a plurality of coaxially arranged stepped holes are provided on the adjustment inner cylinder.

[0013] In an optional solution: the mounting component includes a fixed outer ring connected to the end of the second test component, the end of the fixed outer ring is provided with a docking ring that docks with the first test tube body, a rotating inner ring is provided on the inner side of the fixed outer ring, a locking unit for locking the position of the rotating inner ring is provided on the outer side of the fixed outer ring, and a plurality of clamping units for fixing the blades are distributed in an array on the inner side of the rotating inner ring.

[0014] In an optional solution: the clamping unit includes a second knob of a steering base fixedly connected to the inner wall of the rotating inner ring, a mounting seat is rotatably provided at the upper end of the second knob of the steering base, a clamping member for clamping the blade is provided at the upper end of the mounting seat, and a rotating adjustment member for driving the mounting seat to rotate is provided on the second knob of the steering base.

[0015] In an optional solution: the rotary adjustment member includes a rotating chamber arranged inside the second knob of the steering base, a steering shaft is rotated in the rotating chamber, the upper end of the steering shaft is connected and fixed to the bottom of the mounting seat, a steering worm gear is provided on the steering shaft, a steering worm rotates horizontally in the rotating chamber, the steering worm and the steering worm gear are engaged with each other, and one end of the steering worm passes through the second knob of the steering base and is connected to the first knob and the second knob.

[0016] In an optional solution: the clamping member includes two clamping plates slidably arranged on the upper end of the mounting seat, a clamping groove is provided on the surface of the mounting seat, the clamping groove is connected to the transmission cavity inside the mounting seat, a clamping screw is rotatably provided in the transmission cavity, two threaded blocks are slidably provided in the clamping screw, the threaded blocks are threadedly connected to the clamping screw, two threaded areas with opposite rotation directions are provided on the clamping screw, the upper end of the threaded block is connected to the clamping plate, and one end of the clamping screw passes through the mounting seat and is connected to the second knob.

[0017] In an optional solution: the locking unit includes a positioning base arranged on the outside of the fixed outer ring, a positioning push rod is installed on the positioning base, a through hole is provided inside the positioning base, a receiving groove connected to the through hole is provided inside the fixed outer ring, a positioning pressure block is provided in the receiving groove, and the output end of the positioning push rod is connected to the positioning pressure block.

[0018] In an optional solution: the first separation component includes a first movable base arranged under the first test tube body, first walking wheels are symmetrically provided at both ends of the first movable base, the upper end of the first movable base is connected and fixed to the first test tube body through a first movable support leg, a first horizontal guide rod is slidably provided on the first movable base, the end of the first horizontal guide rod is connected to the fixed base, a first horizontal push rod is fixed on the fixed base, and the output end of the first horizontal push rod is connected to the first movable base.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] In response to existing needs, the present invention can shape the corresponding airflow to meet the test needs of the effects of random airflow excitation of different intensities on blades, thereby improving the adaptability of the test; at the same time, multiple groups of gas turbine blades can be fixed, and the angle between the blades and the airflow can be adjusted as needed, thereby obtaining more test data and effectively improving processing efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of the present invention.

[0022] Figure 2 It is a schematic diagram of the lower structure of the present invention.

[0023] Figure 3 It is a schematic diagram of the internal structure of the present invention.

[0024] Figure 4 It is a schematic diagram of the installation component structure of the present invention.

[0025] Figure 5 It is a schematic diagram of the internal structure of the installation component of the present invention.

[0026] Figure 6 It is a schematic diagram of the structure of the regulating inner cylinder of the present invention.

[0027] Figure 7 It is a schematic diagram of the structure of the installation components of the present invention.

[0028] Figure 8 This is a schematic diagram of the structure of the turbine clamping of the present invention

[0029] Reference numerals: first test tube 100 , first movable leg 101 , first movable base 102 , first traveling wheel 103 , first horizontal guide rod 104 ;

[0030] Mounting component 200, fixed outer ring 201, docking ring 202, clamping unit 203, rotating inner ring 204, positioning base 205, positioning push rod 206, through hole 207, receiving groove 208, positioning pressing block 209;

[0031] Mounting base 210, clamping slot 211, clamping plate 212, threaded block 213, transmission chamber 214, clamping screw 215, steering shaft 216, steering worm gear 217, steering worm 218, rotating chamber 219, first knob 220, steering base 221, second knob 222;

[0032] A second testing component 300, a first horizontal push rod 301, and a fixed base 302;

[0033] Debugging tube 400, debugging installation cavity 401, adjusting inner cylinder 402, connecting end plate 403, stepped hole 404;

[0034] Air supply pipe 500 , inflation connecting pipe 501 , positioning legs 502 , compressed air supply box assembly 503 , blocking push rod 504 , second movable base 505 , second horizontal guide rod 506 , second horizontal push rod 507 , air storage chamber 508 , isolation plate 509 , and blocking block 510 . DETAILED DESCRIPTION

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without creative work are within the scope of protection of the present invention.

[0036] like Figures 1-8 As shown, an embodiment of the present invention provides an experimental device for testing gas turbine gas path parameter responses under random excitation, comprising a first test tube 100 and a second test component 300. A mounting component 200 for fixing blades is provided between the first test tube 100 and the second test component 300. Two fixing bases 302 are symmetrically provided at the lower end of the second test component 300. The fixing bases 302 are connected to the second test component 300 via legs. The first test tube 100 is connected to a first separation assembly for driving it away from the mounting component 200. After the first separation assembly drives the first test tube 100 to separate from the mounting component 200, the blades can be easily installed and fixed. The other end of the second test component 300 is connected to an air supply pipe 500. An adjustment assembly for adjusting airflow is provided at the end of the second test component 300. The air supply pipe 500 is provided with an air supply assembly for providing gas. The air supply pipe 500 is connected to a second separation assembly for driving it away from the second test component 300. The second separation assembly can separate the second test component 300 from the air supply pipe 500, facilitating equipment installation and maintenance.

[0037] The second separation assembly includes a second horizontal push rod 507 fixedly connected to the fixed base 302. The lower end of the air supply pipe 500 is connected to the second movable base 505 through the positioning leg 502. The output end of the second horizontal push rod 507 is connected to the second movable base 505. The second movable base 505 is symmetrically provided with walking wheels at both ends. Two second horizontal guide rods 506 are slidably provided on the second movable base 505. The ends of the second horizontal guide rods 506 are connected to the fixed base 302. Driven by the second horizontal push rod 507, the second movable base 505 can move along the second horizontal guide rods 506, thereby driving the air supply pipe 500 away from the debugging tube 400 to facilitate the replacement of the adjustment inner cylinder 402.

[0038] The air supply assembly includes a compressed air supply box group 503 arranged above the air supply pipe 500, and the air supply end of the compressed air supply box group 503 is connected to the air inlet end of the air supply pipe 500 through the inflation connecting pipe 501. An air storage chamber 508 is provided inside the air supply pipe 500, and an isolation plate 509 is provided in the air storage chamber 508. A vent hole is provided at the center of the isolation plate 509, and a blocking block 510 is provided at the position of the vent hole. The blocking block 510 is connected to the output end of the blocking push rod 504, and the blocking push rod 504 is installed on the air supply pipe 500. Under the drive of the air supply pipe 500, the blocking block 510 can move along the axis of the air supply pipe 500, so that the air storage chamber 508 can be connected with the second test component 300 to realize the release of gas;

[0039] The air storage chamber 508 is provided with a pressure gauge for detecting air pressure, and the second test component 300 is provided with a tachometer for detecting air flow velocity;

[0040] The adjustment assembly includes a debugging tube 400 fixedly connected to the second test component 300. The debugging tube 400 is connected to the second test component 300 via a connecting end plate 403. A debugging installation cavity 401 is defined at the end of the debugging tube 400. An adjustment inner cylinder 402 is provided in the debugging installation cavity 401. The adjustment inner cylinder 402 is provided with a plurality of coaxial stepped holes 404. The stepped holes are used to modify the airflow to meet different testing requirements. The adjustment inner cylinder 402 and the debugging installation cavity 401 are detachable to facilitate subsequent replacement, thereby meeting the requirements of obtaining different test airflows.

[0041] The mounting component 200 includes a fixed outer ring 201 connected to the end of the second test component 300. The fixed outer ring 201 is provided with a docking ring 202 at the end thereof for docking with the first test tube 100. A rotating inner ring 204 is rotatably mounted inside the fixed outer ring 201. A locking unit is provided on the outer side of the fixed outer ring 201 to lock the position of the rotating inner ring 204. A plurality of blade-fixing clamping units 203 are arranged in an array inside the rotating inner ring 204. The clamping units 203 can be used to secure individual blades, and the angle of the corresponding blade can be adjusted as needed to meet different testing requirements.

[0042] The clamping unit 203 includes a second steering base knob 2221 fixedly connected to the inner wall of the rotating inner ring 204. A mounting seat 210 is rotatably provided on the upper end of the second steering base knob 2221. A clamping member for clamping the blade is provided on the upper end of the mounting seat 210. A rotating adjustment member is provided on the second steering base knob 2221 to drive the mounting seat 210 to rotate. By rotating the adjustment member, the mounting seat 210 can be driven to rotate, thereby adjusting the angle between the blade on the mounting seat 210 and the airflow.

[0043] The rotary adjustment member includes a rotating chamber 219 provided inside the second knob 2221 of the steering base, a steering shaft 216 is rotatably provided in the rotating chamber 219, the upper end of the steering shaft 216 is connected and fixed to the bottom of the mounting seat 210, a steering worm gear 217 is provided on the steering shaft 216, a steering worm 218 is horizontally rotated in the rotating chamber 219, the steering worm 218 and the steering worm gear 217 are meshed with each other, one end of the steering worm 218 passes through the second knob 2221 of the steering base and is connected to the first knob and the second knob 2220, the first knob and the second knob 2220 are driven to rotate by a tool, the first knob and the second knob 2220 drive the steering worm 218 and the steering worm gear 217 to rotate relative to each other, thereby driving the steering shaft 216 to rotate, and the steering shaft 216 drives the mounting seat 210 to rotate, thereby providing power for steering adjustment;

[0044] The clamping member includes two clamping plates 212 slidably arranged on the upper end of the mounting seat 210, and a clamping slot 211 is provided on the surface of the mounting seat 210, and the clamping slot 211 is communicated with the transmission cavity 214 inside the mounting seat 210, and a clamping screw 215 is rotatably provided in the transmission cavity 214, and two threaded blocks 213 are slidably provided in the clamping screw 215, and the threaded block 213 is threadedly connected with the clamping screw 215, and the clamping screw 215 is provided with two threaded areas with opposite rotation directions. The upper end of the threaded block 213 is connected to the clamping plate 212, and one end of the clamping screw 215 passes through the mounting seat 210 and is connected to the second knob 2222. The second knob 2222 is driven by a tool to rotate, and the second knob 2222 and the threaded block 213 rotate relative to each other. Under the action of the thread, the threaded block 213 will drive the two clamping plates 212 to move closer to or away from each other, thereby completing the clamping and fixing of the blade;

[0045] The locking unit includes a positioning base 205 arranged on the outside of the fixed outer ring 201, a positioning push rod 206 is installed on the positioning base 205, a through hole 207 is provided inside the positioning base 205, a receiving groove 208 is provided inside the fixed outer ring 201 and is communicated with the through hole 207, a positioning pressing block 209 is provided in the receiving groove 208, an output end of the positioning push rod 206 is connected to the positioning pressing block 209, and a pressing surface of the positioning pressing block 209 is provided with an anti-slip layer. The positioning push rod 206 drives the positioning pressing block 209 to move toward the rotating inner ring 204, thereby locking the rotation position of the rotating inner ring 204;

[0046] The first separation assembly includes a first movable base 102 disposed below the first test tube body 100. First running wheels 103 are symmetrically provided at both ends of the first movable base 102. The upper end of the first movable base 102 is fixedly connected to the first test tube body 100 via first movable legs 101. A first horizontal guide rod 104 is slidably provided on the first movable base 102. The end of the first horizontal guide rod 104 is connected to the fixed base 302. A first horizontal push rod 301 is fixedly provided on the fixed base 302. The output end of the first horizontal push rod 301 is connected to the first movable base 102. Driven by the first horizontal push rod 301, the first movable base 102 slides horizontally along the first horizontal guide rod 104, thereby driving the first test tube body 100 to separate from the mounting component 200.

[0047] Working principle: In actual use, multiple gas turbines are obtained, and then corresponding sensor components are installed on the blades to obtain test data. The blades are then installed on the inner side of the fixed outer ring 201, and the bottom of the blades are fixed by clamping parts. Then, the angle between the blades and the airflow is adjusted by controlling the rotating adjustment parts as needed. Then, gas is input into the air supply pipe 500 through the compressed air supply box group 503. When the air pressure reaches the set value, the blocking block 510 can move along the axis of the air supply pipe 500 under the drive of the air supply pipe 500, so that the air storage chamber 508 can be connected with the second test component 300 to realize the release of gas. The airflow will be shaped when passing through the stepped hole 404 on the regulating inner cylinder 402. The shaped airflow flows along the second test component 300 and then acts on the blades on the mounting component 200, thereby obtaining corresponding data.

[0048] When it is necessary to change the influence of different airflows on the blades, it is only necessary to separate the air supply pipe 500 from the debugging pipe 400 through the second separation component, and then replace the regulating inner cylinder 402;

[0049] When replacing the blades, it is only necessary to separate the first test tube body 100 from the mounting component 200 using the first separation assembly.

[0050] When the incoming flow is subsonic (0.95), it accelerates on the blade suction surface, forming a localized supersonic region. This supersonic region is eventually terminated by a weak normal shock wave, and the airflow becomes subsonic and continues to accelerate, reaching sonic velocity again at the cascade throat, forming a sonic line. At this point, the cascade has maximum mass flow. Simultaneously, a lip wave forms on the pressure side of the cascade leading edge. Finally, the supersonic flow passes through a channel shock wave downstream, becoming subsonic.

[0051] When the incoming flow is supersonic (1.1, 1.2), a detached shock wave is formed at the leading edge of the blade. Part of this shock wave enters the blade channel and appears as a channel oblique shock wave and forms a reflected wave on the suction surface of the blade. Part of it propagates to the upstream of the blade and appears as a detached extended shock wave; as well as a corresponding expansion wave.

[0052] In supersonic inflow (1.2), lip waves are generated on both the suction and pressure sides of the blade leading edge. Simultaneously, the channel normal shock wave causes the boundary layers on the suction and pressure sides of the blade to separate, forming a lambda shock wave. Due to the severe separation of the boundary layer on the suction side, a secondary shock wave is formed after the channel normal shock wave.

[0053] Measuring equipment

[0054] It has electrical measurement, optical measurement and pressure-sensitive paint measurement methods, such as pressure sensor, dynamic pressure sensor, PIV, high-speed Schlieren camera, and surface spraying pressure-sensitive paint.

[0055] PIV: Flow Field Velocity

[0056] PIV generally refers to particle image velocimetry, a method that uses multiple camera recordings to record the positions of particles in a flow field and analyzes the captured images to measure flow velocity.

[0057] High-speed Schlieren imaging: flow field density

[0058] Schlieren is a commonly used optical observation method in mechanical experiments. Its basic principle is to measure the refractive index gradient of light in the measured flow field, which is proportional to the airflow density. It is widely used to observe boundary layers, combustion, shock waves, and convection within gases.

[0059] Surface spraying pressure sensitive paint: blade static pressure

[0060] Pressure-sensitive paint measurement technology utilizes the photoluminescence properties of organic polymers and the oxygen quenching effect to measure surface pressure. This technology can non-invasively obtain high-resolution, continuous pressure maps of an object's surface, addressing the shortcomings of traditional pressure measurement methods.

[0061] Considering the special nature of the shock tube device, contact measurement is not considered at present (conventional pressure and dynamic pressure sensors affect the flow), and only three non-contact measurements are considered: PIV, high-speed schlieren imaging, and surface spraying of pressure-sensitive paint.

[0062] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A gas turbine gas path parameter response test device under random excitation, comprising a first test tube (100) and a second test component (300), wherein a mounting component (200) for fixing a gas turbine blade is provided between the first test tube (100) and the second test component (300), and characterized in that: Two fixed bases (302) are symmetrically provided at the lower end of the second test component (300), and the fixed bases (302) are connected to the second test component (300) through legs. The first test tube body (100) is connected to a first separation component used to drive it away from the mounting component (200). The other end of the second test component (300) is connected to an air supply pipe (500). An adjustment component for adjusting the air flow is provided at the end of the second test component (300). An air supply component for providing random air flow excitation is provided on the air supply pipe (500). The air supply pipe (500) is connected to a second separation component used to drive it away from the second test component (300).

2. The gas turbine gas path parameter response test device under random excitation according to claim 1 is characterized in that: The second separation component includes a second horizontal push rod (507) fixedly connected to the fixed base (302), the lower end of the air supply pipe (500) is connected to the second movable base (505) through the positioning leg (502), the output end of the second horizontal push rod (507) is connected to the second movable base (505), and the second movable base (505) is symmetrically provided with walking wheels at both ends. Two second horizontal guide rods (506) are slidably provided on the second movable base (505), and the ends of the second horizontal guide rods (506) are connected to the fixed base (302).

3. The gas turbine gas path parameter response test device under random excitation according to claim 1 is characterized in that: The air supply assembly for generating random airflow excitation comprises a compressed air supply box group (503) arranged above the air supply pipe (500), the air supply end of the compressed air supply box group (503) is connected to the air inlet end of the air supply pipe (500) through an air charging pipe (501), an air storage chamber (508) is provided inside the air supply pipe (500), an isolation plate (509) is provided in the air storage chamber (508), an air vent is provided at the center of the isolation plate (509), a blocking block (510) is provided at the position of the air vent, the blocking block (510) is connected to the output end of the blocking push rod (504), and the blocking push rod (504) is installed on the air supply pipe (500).

4. The gas turbine gas path parameter response test device under random excitation according to claim 1 is characterized in that: The adjustment assembly comprises a debugging tube (400) fixedly connected to the second test component (300), the debugging tube (400) being connected to the second test component (300) via a connecting end plate (403), a debugging installation cavity (401) being provided at the end of the debugging tube (400), an adjustment inner cylinder (402) being provided in the debugging installation cavity (401), and a plurality of coaxially arranged stepped holes (404) being provided on the adjustment inner cylinder (402).

5. The gas turbine gas path parameter response test device under random excitation according to claim 1 is characterized in that: The mounting component (200) comprises a fixed outer ring (201) connected to the end of the second test component (300); a docking ring (202) docking with the first test tube body (100) is provided at the end of the fixed outer ring (201); a rotating inner ring (204) is provided inside the fixed outer ring (201); a locking unit for locking the position of the rotating inner ring (204) is provided outside the fixed outer ring (201); and a plurality of clamping units (203) for fixing blades are distributed in an array inside the rotating inner ring (204).

6. The gas turbine gas path parameter response test device under random excitation according to claim 5 is characterized in that: The clamping unit (203) comprises a second steering base knob (2221) fixedly connected to the inner wall of the rotating inner ring (204); a mounting seat (210) is rotatably provided on the upper end of the second steering base knob (2221); a clamping member for clamping the blade is provided on the upper end of the mounting seat (210); and a rotation adjustment member for driving the mounting seat (210) to rotate is provided on the second steering base knob (2221).

7. The gas turbine gas path parameter response test device under random excitation according to claim 6 is characterized in that: The rotary adjustment member comprises a rotation chamber (219) arranged inside the second knob (2221) of the steering base, a steering shaft (216) is rotatably provided in the rotation chamber (219), the upper end of the steering shaft (216) is fixedly connected to the bottom of the mounting seat (210), a steering worm wheel (217) is provided on the steering shaft (216), a steering worm (218) is horizontally rotated in the rotation chamber (219), the steering worm (218) and the steering worm wheel (217) are meshed with each other, and one end of the steering worm (218) passes through the second knob (2221) of the steering base and is connected to the first knob and the second knob (2220).

8. The gas turbine gas path parameter response test device under random excitation according to claim 6 is characterized in that: The clamping member includes two clamping plates (212) slidably arranged on the upper end of the mounting seat (210), a clamping groove (211) is provided on the surface of the mounting seat (210), the clamping groove (211) is communicated with a transmission cavity (214) inside the mounting seat (210), a clamping screw (215) is rotatably provided in the transmission cavity (214), two threaded blocks (213) are slidably provided in the clamping screw (215), the threaded blocks (213) are threadedly connected to the clamping screw (215), and the clamping screw (215) is provided with two threaded areas with opposite rotation directions, the upper end of the threaded block (213) is connected to the clamping plate (212), and one end of the clamping screw (215) passes through the mounting seat (210) and is connected to the second knob (2222).

9. The gas turbine gas path parameter response test device under random excitation according to claim 6 is characterized in that: The locking unit comprises a positioning base (205) arranged outside the fixed outer ring (201), a positioning push rod (206) is installed on the positioning base (205), a through hole (207) is provided inside the positioning base (205), a receiving groove (208) connected to the through hole (207) is provided inside the fixed outer ring (201), a positioning pressing block (209) is provided in the receiving groove (208), and the output end of the positioning push rod (206) is connected to the positioning pressing block (209).

10. A method for using the experimental device for testing gas turbine gas path parameter response under random excitation according to any one of claims 1 to 9, characterized in that: The following steps are involved: Step 1: Obtain multiple gas turbines and install corresponding sensor assemblies on the blades to obtain test data; Step 2: Install the blade inside the fixed outer ring 201, fix the bottom of the blade with a clamp, and then control the rotary adjustment member to adjust the angle between the blade and the airflow as needed, and then input gas into the air supply pipe 500 through the compressed air supply box assembly 503; Step 3: When the air pressure reaches the set value, driven by the air supply pipe 500, the blocking block 510 can move along the axis of the air supply pipe 500, so that the air storage chamber 508 can be connected with the second test component 300 to realize the release of gas. The airflow will be shaped when passing through the stepped hole 404 on the regulating inner cylinder 402. The shaped airflow flows along the second test component 300 and then acts on the blades on the mounting component 200 to obtain corresponding data.

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