A multi-axis loading test device for a gas generator rotor end tooth connection structure

Abstract

This invention discloses a multiaxial loading test device for a gas generator rotor end-tooth connection structure, including a test base, a gas generator rotor test piece, a front support, a middle support, a rear support, an axial load loading device, a lateral load loading device, and a displacement sensor. The front support supports the axial load loading device, while the middle and rear supports support the gas generator rotor test piece. The axial load loading device is installed at the front end of the gas generator rotor test piece and can apply axial tensile loads; the lateral load loading device is installed between the compressor and turbine of the gas generator rotor test piece and can apply lateral force loads. This invention can apply axial tensile loads and lateral force loads to the end-tooth connection structure rotor test piece and simulate the stress state of the end-tooth connection structure under rotor bending deformation, enabling experimental measurement of the rotor stiffness characteristics under the combined influence of multi-directional loads.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, specifically relating to a multi-axis loading test device for a gas generator rotor end tooth connection structure. Background Technology

[0002] Aero engines are typical high-speed rotating complex machines. Their rotors are often composed of multiple components with different geometries and materials, connected by various forms of structures. During rotor operation, the connecting structures need to withstand and transmit multiaxial loads such as axial loads, lateral loads, torque loads, and bending loads. Due to the discontinuous nature of the connection interface, under the action of complex multiaxial loads, the connection interface will inevitably experience changes in contact characteristic parameters or even local separation. This leads to mechanical property degradation phenomena such as constraint failure and bending stiffness loss in the connection structure, causing the rotor dynamic characteristics to deviate from the design values.

[0003] For small-sized, high-speed gas generator rotors, the radial diameter of the rotor drum is around 100mm, and the rotor speed is typically above 30,000 rpm. Due to the small radial dimension, bolted connections are generally difficult to use. The rotor components are often connected using end-tooth connections, with a central tie rod used to axially compress the entire rotor. However, under high-speed, high-temperature, and high-pressure environments, the Poisson's ratio effect of the material, the thermal expansion effect of the central tie rod leading to a reduction in the preload of the central tie rod, and the aerodynamic axial load on the rotor structure all cause a decrease in the axial compressive force of the end-tooth connections. This makes slippage and partial separation more likely at the connection interfaces, affecting the mechanical properties of the connection structure. When the rotor undergoes bending deformation at high speeds, due to the discontinuity of the end-tooth connection structure, usually only the end-tooth interface on the compression side is compressed and bears the load, while the end-tooth interface on the tension side slips or even separates partially, resulting in a loss of bending stiffness in the end-tooth connection structure and affecting the rotor's dynamic response characteristics. Therefore, it is necessary to establish an easy-to-use test device for multiaxial load loading and stiffness characteristic testing of end-tooth connection structures to assist in rotor and connection structure design.

[0004] Currently, numerous scholars have conducted research on the mechanical properties of end-tooth connection structures in aero-engines. However, the vast majority of these studies primarily rely on finite element simulation methods to calculate the mechanical properties of these structures, with limited attention paid to specific experimental setups and methods. Furthermore, publicly available rotor testing devices for end-tooth connection structures, such as the utility model patent CN214251512U published by Central South University and the invention patent application CN114166516A published by Beijing University of Chemical Technology, cannot simultaneously apply axial and lateral multi-axis loads to rotor testers with multiple end-tooth connection structures, making it difficult to accurately measure the stiffness characteristics of such rotors. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention discloses a multi-axis loading test device for the end-tooth connection structure of a gas generator rotor. This device can simultaneously apply axial tensile load and lateral force load to the rotor test piece with the end-tooth connection structure, simulating the stress state of the end-tooth connection structure under rotor bending deformation, and can experimentally measure the rotor stiffness characteristics under the combined influence of multi-directional loads.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] A multiaxial loading test device for a gas generator rotor end tooth connection structure includes a test base, an axial load loading device, a front support, a middle support, a gas generator rotor test piece, a lateral load application device, a rear support, and a bolted connection structure for installation and connection. The front end of the gas generator rotor test piece is supported by the middle support and the rear end is supported by the rear support. It is fixed on the test base by the middle support and the rear support. The front support, middle support, and rear support are all fixedly installed on the test base.

[0008] The axial load loading device is located at the front end of the gas generator rotor test piece and is fixed on the test base by the front support seat to apply axial tensile load to the gas generator rotor test piece;

[0009] The lateral load application device is located between the centrifugal compressor disk and the turbine disk of the gas generator rotor test piece. It is mounted and fixed to the test base via a first lateral load application device mounting fixture and a second lateral load application device mounting fixture, applying a lateral force load to the gas generator rotor test piece to simulate the stress state of the end-tooth connection structure under rotor bending deformation. Furthermore, the front end of the gas generator rotor test piece is supported by a middle support seat, and the rear end is supported by a rear support seat, both of which are used to mount and fix it to the test base.

[0010] Furthermore, the lateral load loading device is located in the middle of the gas generator rotor test piece. It is installed and fixed on the test base by the first lateral load loading device mounting fixture and the second lateral load loading device mounting fixture, which can apply lateral force load to the gas generator rotor test piece to simulate the stress state of the end tooth connection structure under the bending deformation state of the rotor.

[0011] Furthermore, the gas generator rotor test piece has a four-end tooth connection structure and is axially clamped by a central tie rod. The gas generator rotor test piece adopts a 1-0-1 two-point support scheme, with the front bearing located in front of the first-stage compressor disk and the rear bearing located behind the turbine disk. Both the front and rear bearings are fixed to the middle and rear support seats respectively through their respective bearing seats, thereby supporting the gas generator rotor test piece.

[0012] Furthermore, a total of 2 axial displacement measuring points and 6 lateral displacement measuring points are arranged on the gas generator rotor test piece. Displacement sensors are used to measure the axial and lateral displacements of the gas generator rotor test piece at each displacement measuring point, thereby realizing the measurement and analysis of its stiffness characteristics.

[0013] Furthermore, the axial load loading device includes an axial load loading screw, an axial load loading screw mounting fixture, an axial load loading screw adapter shaft, an axial load adapter fixture, and adapter bolts. The axial load loading screw is a device for loading and controlling the axial load. It is bolted to the axial load loading screw mounting fixture, which is then bolted to the front support seat, thus achieving the installation and fixation of the axial load loading screw.

[0014] Furthermore, the axial load transfer fixture is designed as a split structure, with a specially shaped channel inside to enclose the bolt head and part of the threaded rod of the transfer bolt, and to enclose the active bevel gear on the gas generator rotor test piece, replacing the original fixture. The axial load loading screw transfer shaft has its right end connected to the transfer bolt via the transfer shaft bolt hole, and its left end connected to the axial load loading screw via the transfer shaft mounting edge. When the axial load loading screw applies an axial tensile load, the axial load will sequentially pass through the axial load loading screw transfer shaft, the transfer bolt, the axial load transfer fixture, and the active bevel gear (replacing the original fixture), finally being applied to the gas generator rotor test piece, thus achieving the application of the axial load.

[0015] Furthermore, the multi-axis loading test device for a gas generator rotor end tooth connection structure includes a transverse load loading screw, a transverse load loading screw mounting fixture, a transverse load applying pressure head, a first transverse load loading device mounting fixture, and a second transverse load loading device mounting fixture. The transverse load loading screw is fixed to the transverse load loading screw mounting fixture by bolts. The transverse load loading screw mounting fixture is mounted above the first and second transverse load loading device mounting fixtures via its lower mounting edge. The first and second transverse load loading device mounting fixtures are then fixed to the test base by bolts, thus achieving the installation and fixation of the transverse load loading device.

[0016] Furthermore, the upper part of the lateral load applying head is a disc-shaped mounting edge, which is connected to the lateral load loading screw. The lower part is a V-shaped contact head, which contacts the lateral load loading position on the gas generator rotor test piece. When the lateral load loading screw applies the lateral force load, the lateral force load will be applied to the gas generator rotor test piece through the lateral load applying head, thereby realizing the application of the lateral force load.

[0017] The present invention has the following beneficial effects:

[0018] (1) This invention can change the initial preload of the central tie rod by adjusting the tightening torque of the clamping nut on the central tie rod, and conduct tests under various preload conditions. It can also measure the stiffness characteristics of the rotor with end tooth connection structure under working conditions by actively applying axial tensile load to the gas generator rotor test piece to simulate the situation where the axial clamping force of the end tooth connection structure decreases during operation.

[0019] (2) The present invention arranges multiple transverse displacement measuring points along the axial direction of the rotor tester, which can accurately measure the position of the elastic line of the rotor under deformation, thereby accurately calculating the transverse stiffness characteristics of the end-tooth connected rotor. By arranging axial displacement measuring points symmetrical along the rotation axis, the angular deformation of the rotor at the measuring points can be calculated, thereby calculating the angular stiffness characteristics of the rotor, and assisting in the design of the structural and mechanical properties of the rotor and connecting structure. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of a multi-axis loading test device for a gas generator rotor end tooth connection structure according to an embodiment of the present invention;

[0021] Figure 2 This is a cross-sectional view of the gas generator rotor test piece in this invention;

[0022] Figure 3 This is a schematic diagram of the displacement measuring points and load loading positions on the gas generator rotor test piece in this invention;

[0023] Figure 4 This is a schematic diagram of the structural composition of the axial load loading device in this invention;

[0024] Figure 5 This is an exploded view of the connection between the axial load loading device and the gas generator rotor test piece in this invention;

[0025] Figure 6 This is a schematic diagram of the structural composition of the transverse load loading device in this invention.

[0026] In the picture:

[0027] 1-Test base, 2-Axial load loading device, 3-Front support, 4-Middle support, 5-Gas generator rotor test piece, 6-Transverse load application device, 7-Rear support;

[0028] 101-Front bearing clamping nut, 102-Drive bevel gear replacement tooling, 103-Front bearing, 104-First stage compressor bladed disk, 105-Second stage compressor bladed disk, 106-Third stage compressor bladed disk, 107-Centrifugal compressor bladed disk, 108-Connecting rod bushing, 109-Connecting rod clamping nut, 110-Turbine bladed disk, 111-Turbine rear bushing, 112-Rear bearing, 113-Rear bearing clamping nut, 114-Connecting rod rear clamping nut, 115-Central connecting rod;

[0029] 201 - Axial load loading screw, 202 - Axial load loading screw mounting fixture, 203 - Axial load loading screw adapter shaft, 204 - Axial load adapter fixture, 205 - Adapter bolt, 202a - First mounting side of axial load loading screw mounting fixture, 202b - Second mounting side of axial load loading screw mounting fixture, 203a - Adapter shaft bolt hole, 203b - Adapter shaft mounting side, 204a - Upper half of axial load adapter fixture, 204b - Lower half of axial load adapter fixture;

[0030] 301- Lateral load loading screw, 302- Lateral load loading screw mounting fixture, 303- Lateral load applying pressure head, 304- First lateral load loading device mounting fixture, 305- Second lateral load loading device mounting fixture;

[0031] A1 - First axial displacement measuring point, A2 - Second axial displacement measuring point, D1 - First lateral displacement measuring point, D2 - Second lateral displacement measuring point, D3 - Third lateral displacement measuring point, D4 - Fourth lateral displacement measuring point, D5 - Fifth lateral displacement measuring point, D6 - Sixth lateral displacement measuring point, F1 - Axial load loading position, F2 - Lateral load loading position. Detailed Implementation

[0032] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Unless otherwise specified, the technical means used in the embodiments are conventional means well known to those skilled in the art.

[0033] like Figure 1As shown, this embodiment of the invention relates to a multi-axial loading test device for a gas generator rotor end tooth connection structure, including a test base 1, an axial load loading device 2, a front support 3, a middle support 4, a gas generator rotor test piece 5, a lateral load application device 6, a rear support 7, and a bolted connection structure for installation. The axial load loading device 2 is located at the front end of the gas generator rotor test piece 5, and the lateral load loading device 6 is located in the middle of the gas generator rotor test piece 5. The front support 3, the middle support 4, and the rear support 7 are all fixedly installed on the test base 1, wherein the front support 3 is used to support the axial load loading device 2, and the middle support 4 and the rear support 7 are used to support the gas generator rotor test piece 5.

[0034] like Figure 2 As shown, the gas generator rotor test piece 5 in this embodiment of the invention includes a front bearing clamping nut 101, a drive bevel gear replacement tooling 102, a front bearing 103, a first-stage compressor impeller 104, a second-stage compressor impeller 105, a third-stage compressor impeller 106, a centrifugal compressor impeller 107, a tie rod bushing 108, a tie rod clamping nut 109, a turbine impeller 110, a turbine rear bushing 111, a rear bearing 112, a rear bearing clamping nut 113, a tie rod rear clamping nut 114, and a central tie rod 115.

[0035] like Figure 2 As shown, the gas generator rotor test piece 5 has four end tooth connection structures. The first end tooth connection structure is used to connect the first stage compressor blade disk 104 and the second stage compressor blade disk 105. The second end tooth connection structure is used to connect the second stage compressor blade disk 105 and the third stage compressor blade disk 106. The third end tooth connection structure is used to connect the third stage compressor blade disk 106 and the centrifugal compressor blade disk 107. The fourth end tooth connection structure is used to connect the centrifugal compressor blade disk 107 and the turbine blade disk 110. All end tooth connection structures are axially pressed together by a central tie rod 115.

[0036] like Figure 2 As shown, the gas generator rotor test piece 5 adopts a 1-0-1 two-point support scheme. The front bearing 103 is located in front of the first-stage compressor blade disk 104. The inner ring of the front bearing 103 is installed and fixed on the rotor by a drive bevel gear replacing tooling 102 and the front bearing clamping nut 101, while the outer ring is installed and fixed on the intermediate support 4 by a bearing housing. The rear bearing 112 is located behind the turbine blade disk 110. The inner ring of the rear bearing 112 is installed and fixed on the rotor by the turbine rear bushing 111 and the rear bearing clamping nut 113, while the outer ring is installed and fixed on the rear support 7 by a bearing housing, thereby achieving support for the gas generator rotor test piece 5.

[0037] like Figure 2As shown, the gas generator rotor test piece 5 is axially clamped using a central tie rod 115. The front end of the central tie rod 115 is threadedly installed inside the first-stage compressor impeller 104. A thread is also designed in the middle of the central tie rod 115. It is clamped behind the centrifugal compressor impeller 107 using a tie rod bushing 108 and a tie rod clamping nut 109. The front half of the central tie rod 115 axially clamps the first, second, and third end-tooth connection structures. The rear of the central tie rod 115 is fixed to the turbine impeller 110 using a tie rod rear clamping nut 114. The rear half of the central tie rod 115 axially clamps the fourth end-tooth connection structure.

[0038] like Figure 3 As shown, the gas generator rotor test piece 5 in this embodiment of the invention has one axial load loading position F1, one lateral load loading position F2, six lateral displacement measuring points, and two axial displacement measuring points. The six lateral displacement measuring points are: first lateral displacement measuring point D1, second lateral displacement measuring point D2, third lateral displacement measuring point D3, fourth lateral displacement measuring point D4, fifth lateral displacement measuring point D5, and sixth lateral displacement measuring point D6. The two axial displacement measuring points are: first axial displacement measuring point A1 and second axial displacement measuring point A2. The axial load loading position F1 is located on the active bevel gear replacement tooling 102, and the lateral load loading position F2 is located between the centrifugal compressor bladed disk 107 and the turbine bladed disk 110. The first lateral displacement measuring point D1 is located between the first-stage compressor bladed disk 104 and the second-stage compressor bladed disk 105; the second lateral displacement measuring point D2 is located between the second-stage compressor bladed disk 105 and the third-stage compressor bladed disk 106; the third lateral displacement measuring point D3 is located between the third-stage compressor bladed disk 106 and the centrifugal compressor bladed disk 107; the fourth lateral displacement measuring point D4 is located at the top of the centrifugal compressor bladed disk 107; the fifth lateral displacement measuring point D5 is located between the centrifugal compressor bladed disk 107 and the turbine bladed disk 110; and the sixth lateral displacement measuring point D6 is located at the top of the turbine bladed disk 110. The first axial displacement measuring point A1 is located at the top of the centrifugal compressor bladed disk 107; and the second axial displacement measuring point A2 is located at the bottom of the centrifugal compressor bladed disk 107. Six lateral displacement measuring points are simultaneously arranged along the axial direction of the gas generator rotor test piece 5. The purpose is to accurately measure the position of the rotor's elastic line under deformation, thereby accurately calculating the lateral stiffness characteristics of the end-tooth connected rotor. Two axial displacement measuring points are arranged on the centrifugal compressor disk 107. The purpose is to measure and calculate the angular deformation of the centrifugal compressor disk 107 under bending deformation, thereby calculating the angular stiffness of the centrifugal compressor disk 107.

[0039] like Figure 4As shown, the axial load loading device 2 in this embodiment of the invention includes an axial load loading screw 201, an axial load loading screw mounting fixture 202, an axial load loading screw adapter shaft 203, an axial load adapter 204, and an adapter bolt 205. The axial load loading screw 201 is a device for loading and controlling axial loads. It is bolted to the axial load loading screw mounting fixture 202. Subsequently, the first mounting edge 202a and the second mounting edge 202b of the axial load loading screw mounting fixture are bolted to the front support seat 3, thereby achieving the installation and fixation of the axial load loading screw 201.

[0040] like Figure 4 and Figure 5 As shown, the axial load transfer fixture 204 is designed as a split structure, including an upper half 204a and a lower half 204b. The upper and lower halves are fitted together by mounting edges and connected by bolts to form a complete axial load transfer fixture 204. The interior of the axial load transfer fixture 204 is designed with a specially shaped channel that encloses the bolt head and part of the threaded rod of the adapter bolt 205, and also encloses the driving bevel gear on the gas generator rotor test piece 5, replacing the fixture 102. The right end of the axial load loading screw adapter shaft 203 is connected to the adapter bolt 205 through the adapter shaft bolt hole 203a, and its left end is connected to the axial load loading screw 201 through the adapter shaft mounting edge 203b. When the axial load loading screw 201 applies an axial tensile load, the axial load will be applied sequentially through the axial load loading screw adapter shaft 203, adapter bolt 205, axial load adapter tooling 204, and active bevel gear replacing tooling 102, and finally applied to the gas generator rotor test piece 5, thus realizing the application of the axial load.

[0041] like Figure 6 As shown, the lateral load loading device 6 in this embodiment of the invention includes a lateral load loading screw 301, a lateral load loading screw mounting fixture 302, a lateral load applying pressure head 303, a first lateral load loading device mounting fixture 304, and a second lateral load loading device mounting fixture 305. The lateral load loading screw 301 is fixed to the lateral load loading screw mounting fixture 302 by bolts. The lateral load loading screw mounting fixture 302 is mounted above the first lateral load loading device mounting fixture 304 and the second lateral load loading device mounting fixture 305 via its lower mounting edge. The first lateral load loading device mounting fixture 304 and the second lateral load loading device mounting fixture 305 are then fixed to the test base 1 by bolts, thereby realizing the installation and fixation of the lateral load loading device 6.

[0042] like Figure 6As shown, the upper part of the transverse load applying head 303 is a disc-shaped mounting edge, which is connected to the transverse load loading screw 301. The lower part of the transverse load applying head 303 is a V-shaped contact head, which contacts the transverse load loading position F2 on the gas generator rotor test piece 5. When the transverse load loading screw 301 applies a transverse force load, the transverse force load will be applied to the gas generator rotor test piece 5 through the transverse load applying head 303, thereby realizing the application of the transverse force load.

[0043] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Any modifications, alterations, substitutions, or variations made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A multi-axial loading test device for a gas generator rotor end toothing connection structure, characterized in that: It includes a test base (1), an axial load loading device (2), a front support (3), a middle support (4), a gas generator rotor test piece (5), a transverse load loading device (6), a rear support (7), and a bolt connection structure for installation and connection; the front end of the gas generator rotor test piece (5) is supported by the middle support (4), and the rear end is supported by the rear support (7). It is installed and fixed on the test base (1) through the middle support (4) and the rear support (7). The front support (3), the middle support (4), and the rear support (7) are all fixedly installed on the test base (1); The axial load loading device (2) is located at the front end of the gas generator rotor test piece (5) and is fixed on the test base (1) by the front support seat (3) to apply axial tensile load to the gas generator rotor test piece (5); The lateral load loading device (6) is located between the centrifugal compressor blade disk (107) and the turbine blade disk (110) of the gas generator rotor test piece (5). It is installed and fixed on the test base (1) through the first lateral load loading device mounting fixture (304) and the second lateral load loading device mounting fixture (305) to apply lateral force load to the gas generator rotor test piece (5) and simulate the stress state of the end tooth connection structure under the bending deformation state of the rotor. The gas generator rotor test piece (5) is composed of a first-stage compressor blade disk (104), a second-stage compressor blade disk (105), a third-stage compressor blade disk (106), a centrifugal compressor blade disk (107), and a turbine blade disk (110). The first-stage compressor blade disk (104), the second-stage compressor blade disk (105), the third-stage compressor blade disk (106), the centrifugal compressor blade disk (107), and the turbine blade disk (110) are all connected by an end-tooth connection structure. The gas generator rotor test piece (5) has a total of 4 end-tooth connection structures and is axially pressed by a central tie rod (115). The gas generator rotor test piece (5) adopts a two-point support method. The front bearing (103) is located in front of the first stage compressor blade disk (104), and the rear bearing (112) is located behind the turbine blade disk (110). The front bearing (103) and the rear bearing (112) are respectively fixed on the middle support (4) and the rear support (7) through their respective bearing seats to support the gas generator rotor test piece (5). The gas generator rotor test piece (5) has an active bevel gear (102) installed in front of the front bearing (103) to replace the tooling (102). The active bevel gear (102) is connected to the axial load loading device (2) to apply the axial load. Two axial displacement measuring points and six lateral displacement measuring points are arranged on the gas generator rotor test piece (5). Displacement sensors are used to measure the axial and lateral displacements of the gas generator rotor test piece (5) at each axial displacement measuring point and lateral displacement measuring point, thereby realizing the measurement and analysis of its stiffness characteristics.

2. The multi-axial loading test device for a rotor end toothing connection structure of a gas generator according to claim 1, characterized in that: The axial load loading device (2) includes an axial load loading screw (201), an axial load loading screw mounting fixture (202), an axial load loading screw adapter shaft (203), an axial load adapter fixture (204), and an adapter bolt (205). The axial load loading screw (201) is an axial load loading and control device. It is connected to the axial load loading screw mounting fixture (202) by bolts. Then, the first mounting edge (202a) and the second mounting edge (202b) of the axial load loading screw mounting fixture are mounted on the front support seat (3) by bolts to realize the installation and fixation of the axial load loading screw (201). The axial load transfer fixture (204) is designed as a split structure, including an upper half (204a) and a lower half (204b). The upper half (204a) and the lower half (204b) are fitted together by mounting edges and connected by bolts to form a complete axial load transfer fixture (204). The interior of the axial load transfer fixture (204) is designed as a channel, which wraps around the bolt head and part of the bolt of the transfer bolt (205) and wraps around the active bevel gear on the gas generator rotor test piece (5) to replace the fixture (102). The right end of the axial load loading screw adapter shaft (203) is connected to the adapter bolt (205) through the adapter shaft bolt hole (203a), and its left end is connected to the axial load loading screw (201) through the adapter shaft mounting edge (203b). When the axial load loading screw (201) applies an axial tensile load, the axial load will be applied to the gas generator rotor test piece (5) in sequence through the axial load loading screw adapter shaft (203), the adapter bolt (205), the axial load adapter tooling (204), and the active bevel gear replacing the tooling (102), thus realizing the application of the axial load.

3. The multi-axial loading test device for a rotor end toothing connection structure of a gas generator according to claim 1, characterized in that: The transverse load loading device (6) includes a transverse load loading screw (301), a transverse load loading screw mounting fixture (302), a transverse load applying pressure head (303), a first transverse load loading device mounting fixture (304), and a second transverse load loading device mounting fixture (305). The transverse load loading screw (301) is fixed to the transverse load loading screw mounting fixture (302) by bolts. The transverse load loading screw mounting fixture (302) is mounted above the first transverse load loading device mounting fixture (304) and the second transverse load loading device mounting fixture (305) by its lower mounting edge. The first transverse load loading device mounting fixture (304) and the second transverse load loading device mounting fixture (305) are fixed to the test base (1) by bolts, thereby realizing the installation and fixation of the transverse load loading device (6). The transverse load applying head (303) has a disc-shaped mounting edge on top, which is connected to the transverse load loading screw (301). The bottom part is a "V"-shaped contact head, which contacts the transverse load loading position (F2) on the gas generator rotor test piece (5). When the transverse load loading screw (301) applies a transverse force load, the transverse force load will be applied to the gas generator rotor test piece (5) through the transverse load applying head (303), thereby realizing the application of the transverse force load.

Images