Test run rack for aviation hybrid power turbine power generation system

Abstract

The invention discloses an aviation hybrid power turbine power generation system test run rack which comprises a test run platform, a first mounting rack arranged on the test run platform and used for supporting an engine and a second mounting rack arranged on the test run platform and used for supporting a generator. A linear guide rail parallel to the axial direction of the engine, a bottom plate arranged on the linear guide rail in a sliding mode and a driving mechanism used for driving the bottom plate to slide relative to the linear guide rail are arranged on the test run platform, and the first mounting frame is arranged on the bottom plate; the driving mechanism drives the first mounting frame to move through the bottom plate so as to adjust the distance between the first mounting frame and the second mounting frame; the test bench for the aviation hybrid power turbine power generation system can be suitable for combined tests of different engines and generators, can be compatible with complete machine test tests of an aviation hybrid power split type eddy current system or an integrated type eddy current system, and is wide in application range.

Description

Technical Field

[0001] The invention relates to the technical field of aviation engines, and in particular to a test bench for a hybrid power turbine power generation system for aviation. Background Art

[0002] The hybrid turbine power generation system for aviation uses the engine as the prime mover. Its output shaft drives the generator, which generates electrical energy after electromagnetic conversion. The electrical energy is directly used as a source of energy to supply batteries or other power devices. In order to improve the working efficiency and power-to-weight ratio of the turbo-electric system, a turboshaft engine is usually selected as the prime mover of the aircraft engine.

[0003] According to the different power output modes, turbine-generated aviation hybrid power can be divided into two configurations: series hybrid and parallel hybrid. Among them, the main body of the series aviation hybrid turbine power generation system (referred to as turbo-electric system) is composed of an aircraft engine and a generator. According to the connection form between the engine and the generator, it can be divided into a split turbo-electric system and an integrated turbo-electric system.

[0004] The characteristic of the split turbo-electric system is that it needs to be assembled on a test bench. Its engine and generator are connected by a connecting shaft after self-alignment and centering, so the test bench is required to have self-alignment and centering functions. For the integrated turbo-electric system, it is an advancement of the split turbo-electric system. Its characteristic is the integrated design of the engine and generator. The weight of the two is close to 1:1, and the axial characteristic length of the system is nearly doubled compared with that of the traditional engine. Existing aircraft engines are generally connected to the engine with load-consuming equipment. The volume and weight of the load-consuming equipment are much larger than the generator, and there is no need to consider expansion and other issues. Fixed installation is directly adopted without considering the generator situation. Its installation form is difficult to meet the test requirements of the two structural forms of turbo-electric systems. Summary of the invention

[0005] The invention provides a hybrid power turbine power generation system test bench for aviation, so as to solve the technical problem that the existing aviation engine test bench is difficult to meet the test requirements of vortex electric systems with two structural forms.

[0006] According to one aspect of the present invention, there is provided a test bench for a hybrid power turbine power generation system for aviation, comprising a test platform, a first mounting frame arranged on the test platform for supporting an engine, and a second mounting frame arranged on the test platform for supporting a generator, wherein the test platform is provided with a linear guide rail parallel to the axial direction of the engine, a base plate slidably arranged on the linear guide rail, and a driving mechanism for driving the base plate to slide relative to the linear guide rail, the first mounting frame is arranged on the base plate, and the driving mechanism drives the first mounting frame to move through the base plate to adjust the distance between the first mounting frame and the second mounting frame.

[0007] Furthermore, the driving mechanism includes a first screw rod rotatably arranged on the test platform and a driver for driving the first screw rod to rotate, and the first screw rod is threadedly connected to the base plate.

[0008] Furthermore, the first mounting frame includes a first skeleton arranged on the base plate, a first column arranged on the first skeleton, a first fine-adjustment mechanism arranged on the first column and a rear fulcrum support, the rear fulcrum support includes a support seat, a first pin arranged along the axial direction of the engine and a fork arm slidably hinged on the first pin, two of the first columns are arranged side by side in a direction perpendicular to the axial direction of the engine, two fork arms are arranged on the first pin, and the two fork arms and the two first fine-adjustment mechanisms are connected to the engine to support the engine.

[0009] Further, the first fine-tuning mechanism includes a support plate arranged on the first column, an adjustment block arranged on the support plate and movable in a vertical direction relative to the support plate, and a first mounting section arranged on the adjustment block for connecting the engine, the axis of the first mounting section is perpendicular to the axis of the engine and arranged in a horizontal direction, the first mounting section can move along its axis relative to the adjustment block, and the first fine-tuning mechanism also includes a locking nut for limiting the relative position of the first mounting section and the adjustment block.

[0010] Furthermore, the second mounting frame includes a second frame arranged on the test platform and an auxiliary support arranged on the second frame, the auxiliary support includes a support rod, a joint bearing, a second pin shaft and a second mounting section, the support rod can be telescopic along its axial direction and its axial length is fixed after telescopic, two second pin shafts are respectively arranged at both ends of the support rod, the axes of the two second pin shafts are arranged parallel to the axis of the generator, the second pin shaft at the bottom end of the support rod is hinged to the second frame through one of the joint bearings, and the second pin shaft at the top end of the support rod is hinged to the second mounting section through another joint bearing.

[0011] Furthermore, a support frame for supporting the air intake grille is arranged on the bottom plate and / or the first mounting frame.

[0012] Furthermore, the second mounting frame also includes a second column arranged on the second skeleton and a second fine-adjustment mechanism arranged on the second column, the two second columns are arranged side by side along an axial direction perpendicular to the engine, the two auxiliary supports are arranged side by side along an axial direction perpendicular to the engine, the second fine-adjustment mechanism has the same structure as the first fine-adjustment mechanism, and the two second fine-adjustment mechanisms and the two auxiliary supports are connected to the generator to support the generator.

[0013] Furthermore, a limiting mechanism is arranged on the bottom plate, and limiting holes adapted to the limiting mechanism are arranged on the test platform and / or the linear guide rail.

[0014] Furthermore, the test platform is provided with universal wheels and a pull rod for pushing and pulling the test platform.

[0015] Furthermore, the test platform is provided with telescopic support legs for propping up the test platform so that the universal wheels are off the ground.

[0016] The present invention has the following beneficial effects: The aviation hybrid power turbine power generation system test bench of the present invention has a second mounting frame for mounting a generator fixedly mounted on the test platform, a first mounting frame for supporting the engine is mounted on a base plate, a linear guide rail is arranged along the X-axis direction, and the base plate is driven by a driving mechanism to move on the linear guide rail. The spacing between the first mounting frame and the second mounting frame can be adjusted according to assembly requirements, and the test bench can be suitable for combined tests of different engines and generators, and is compatible with whole machine test of aviation hybrid power split turbo-electric systems or integrated turbo-electric systems, and has a wide range of applications.

[0017] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 This is one of the structural schematic diagrams of a test bench for a hybrid power turbine power generation system for aviation according to a preferred embodiment of the present invention; Figure 2 yes Figure 1 A schematic structural diagram of a test platform of the illustrated embodiment; Figure 3 yes Figure 2 a top view of the illustrated embodiment; Figure 4 is a structural schematic diagram of a first mounting frame according to a preferred embodiment of the present invention; Figure 5 is a schematic structural diagram of a rear fulcrum support of a preferred embodiment of the present invention; Figure 6 is one of the structural schematic diagrams of the second mounting frame of the preferred embodiment of the present invention; Figure 7This is the second structural schematic diagram of the test bench for the hybrid power turbine power generation system for aviation according to the preferred embodiment of the present invention; Figure 8 yes Figure 7 A schematic structural diagram of a test platform of the illustrated embodiment; Fig. 9 yes Figure 8 a top view of the illustrated embodiment; Fig.10 This is the second structural schematic diagram of the second mounting frame of the preferred embodiment of the present invention.

[0019] Legend: 1. Test platform; 11. Linear guide rail; 111. Limiting hole; 12. Bottom plate; 13. Driving mechanism; 131. First screw rod; 132. Driver; 14. Limiting mechanism; 141. Limiting block; 142. Positioning handle; 15. Universal wheel; 16. Pull rod; 17. Telescopic support leg; 2. First mounting frame; 21. First frame; 211. Lifting ring; 212. Reinforcement rib; 22. First column; 23. First fine-tuning mechanism; 231. Support plate; 232. Adjustment block; 233. First A mounting section; 234, bearing; 235, second screw rod; 236, positioning bolt; 24, rear fulcrum support; 241, support seat; 242, first pin shaft; 243, fork arm; 25, support frame; 3, second mounting frame; 31, second skeleton; 32, auxiliary support; 321, support rod; 322, joint bearing; 323, second pin shaft; 324, second mounting section; 33, second column; 34, second fine-tuning mechanism; 4, engine; 5, generator; 6, connecting shaft; 7, air intake grille. DETAILED DESCRIPTION

[0020] The embodiments of the present invention are 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.

[0021] like Figure 1 As shown, the aviation hybrid power turbine power generation system test bench of this embodiment includes a test platform 1, a first mounting frame 2 arranged on the test platform 1 for supporting the engine 4, and a second mounting frame 3 arranged on the test platform 1 for supporting the generator 5. The test platform 1 is provided with a linear guide rail 11 parallel to the axial direction of the engine 4, a base plate 12 slidably arranged on the linear guide rail 11, and a driving mechanism 13 for driving the base plate 12 to slide relative to the linear guide rail 11. The first mounting frame 2 is arranged on the base plate 12, and the driving mechanism 13 drives the first mounting frame 2 to move through the base plate 12 to adjust the distance between the first mounting frame 2 and the second mounting frame 3.

[0022] The length direction of the test platform 1 is the X-axis, the width direction of the test platform 1 is the Y-axis, the vertical direction is the Z-axis, the X-axis direction is the front-back direction, the Y-axis direction is the left-right direction, and the Z-axis direction is the up-down direction.

[0023] The aviation hybrid turbine power generation system test bench of the present embodiment has a second mounting frame 3 for mounting the generator 5 fixedly mounted on the test platform 1, and a first mounting frame 2 for supporting the engine 4 is mounted on the base plate 12. The linear guide 11 is arranged along the X-axis direction, and the base plate 12 is driven by the driving mechanism 13 to move on the linear guide 11. The distance between the first mounting frame 2 and the second mounting frame 3 can be adjusted according to assembly requirements. It can be suitable for combined tests of different engines 4 and generators 5, and is compatible with the whole machine test of aviation hybrid split turbo-electric systems or integrated turbo-electric systems, and has a wide range of applications.

[0024] like Figure 2 and Figure 3 As shown, in this embodiment, the driving mechanism 13 includes a first screw 131 rotatably arranged on the test platform 1 and a driver 132 for driving the first screw 131 to rotate. The first screw 131 is screwed to the base plate 12 through the driving mechanism 13 to drive the first screw 131 to rotate, thereby driving the base plate 12 to move along the linear guide 11, which can be applicable to different types of vortex electric systems; it is understandable that the first screw 131 can be replaced by a gear rack or a ball screw. Optionally, the driver 132 is a hand crank handle. The vortex electric system can be subsequently tested with a distributed propulsion system in the form of a propeller, and the number of propellers is usually greater than 1. The hand crank handle does not need to be equipped with an additional power source, and can be tested in combination with other systems in different occasions. Optionally, the driver 132 is an electric motor or a hydraulic motor, which has a high degree of automation and can reduce labor intensity.

[0025] In this embodiment, the driving mechanism 13 is a gas cylinder or an oil cylinder, which has a high degree of automation and is easy to assemble and disassemble, but needs to be equipped with a corresponding gas source or a hydraulic oil station.

[0026] like Figure 4 and Figure 5As shown, in this embodiment, the first mounting frame 2 includes a first frame 21 arranged on the base plate 12, a first column 22 arranged on the first frame 21, a first fine-tuning mechanism 23 arranged on the first column 22, and a rear fulcrum support 24, the rear fulcrum support 24 includes a support seat 241, a first pin shaft 242 arranged along the axial direction of the engine 4, and a fork arm 243 slidably hinged on the first pin shaft 242, the two first columns 22 are arranged side by side along the axial direction perpendicular to the engine 4, two fork arms 243 are arranged on the first pin shaft 242, the two fork arms 243 and the two first fine-tuning mechanisms 23 are all connected to the engine 4 to support the engine 4; the first frame 21 is welded and formed by steel sections, steel plates, etc., and is fixed to the bottom plate 12 by bolts. The first column 22 is arranged along the Z-axis direction. The two first fine-tuning mechanisms 23 are respectively installed on the two first columns 22, and fix the engine 4 in the left and right directions. The first fine-tuning mechanism 23 can make fine adjustments to the installation position of the engine 4 in four directions, namely, up, down, left, and right, so as to facilitate the alignment of the engine 4 and the generator 5 during assembly. The two fork arms 243 of the rear fulcrum support 24 can rotate around the first pin shaft 242 as the axis, and can slide axially relative to the first pin shaft 242, which can compensate for the radial and axial thermal expansion of the vortex electric system and avoid test safety accidents. Optionally, a lifting ring 211 is arranged on the first skeleton 21 to facilitate the lifting of the first mounting frame 2. Optionally, a reinforcing rib 212 for connecting the first column 22 is arranged on the first skeleton 21 to increase the strength of the first mounting frame 2.

[0027] like Figure 4As shown, in this embodiment, the first fine-tuning mechanism 23 includes a support plate 231 arranged on the first column 22, an adjustment block 232 arranged on the support plate 231 and movable relative to the support plate 231 in a vertical direction, and a first mounting section 233 arranged on the adjustment block 232 for connecting the engine 4. The axis of the first mounting section 233 is perpendicular to the axis of the engine 4 and arranged in a horizontal direction. The first mounting section 233 can move relative to the adjustment block 232 along its axis. The first fine-tuning mechanism 23 also includes a locking nut for limiting the relative position of the first mounting section 233 and the adjustment block 232; the adjustment The block 232 can move in the up and down directions to adjust the vertical height of the first mounting joint 233, and the first mounting joint 233 can move in the left and right directions to adjust the left and right positions of the first mounting joint 233, so as to facilitate the alignment of the engine 4 and the generator 5 during assembly; when conducting the test, the first mounting joint 233 on the left side of a first fine-tuning mechanism 23 is locked by a locking nut (the locking nut is pressed against the support plate 231), and the first mounting joint 233 on the right side of another first fine-tuning mechanism 23 can slide left and right (there is a gap between the locking nut and the support plate 231), which can compensate for the radial thermal expansion of the engine 4. Optionally, the support plate 231 is an L-shaped plate, which has a simple structure and a processing scheme. Optionally, a bearing 234 is arranged on the adjustment block 232, and the first mounting joint 233 is arranged in the bearing 234, which can avoid friction between the first mounting joint 233 and the adjustment block 232 and improve the service life of the support plate 231. Optionally, a second screw 235 is disposed on the support plate 231, and a wedge block for contacting the adjustment block 232 is disposed on the second screw 235. The wedge block is driven to move by rotating the second screw 235, thereby adjusting the vertical position of the adjustment block 232. Optionally, the support plate 231 of the first fine-tuning mechanism 23 on the left is fixed to the first column 22 by four fastening bolts, and the support plate 231 of the first fine-tuning mechanism 23 on the right is fixed to the first column 22 by two fastening bolts and two positioning bolts 236. A preset tolerance is reserved between the positioning bolts 236 and the mounting holes on the support plate 231 and the first column 22 for repeated positioning. When the vortex electric system is put on the stage for the first time and the centering is completed, the left and right support plates 231 are in a fixed state. When the test is completed and the system is removed from the stage, the left support plate 231 is fixed and the vortex electric system is removed from the stage by removing the right support plate 231 from the first column 22. When the installation size of the vortex electric system remains unchanged, the installation position of the vortex electric system can be located by using the positioning bolts 236 between the right support plate 231 and the first column 22 when the system is put on the stage next time, without having to repeat the centering, which can reduce the difficulty of assembly and greatly improve the assembly efficiency.

[0028] like Figure 1 , Figure 2 and Figure 6As shown, in this embodiment, the second mounting frame 3 includes a second frame 31 arranged on the test platform 1 and an auxiliary support 32 arranged on the second frame 31, the auxiliary support 32 includes a support rod 321, a joint bearing 322, a second pin shaft 323 and a second mounting section 324, the second mounting section 324 is used to connect the generator 5, the support rod 321 can be telescopic along its axial direction and its axial length is fixed after telescoping, the two second pin shafts 323 are respectively arranged at both ends of the support rod 321, the axes of the two second pin shafts 323 are arranged parallel to the axis of the generator 5, and the second pin shaft 323 at the bottom of the support rod 321 is connected to the generator 5 by a joint The bearing 322 is hinged to the second skeleton 31, and the second pin shaft 323 at the top of the support rod 321 is hinged to the second mounting joint 324 through another joint bearing 322; the second skeleton 31 is formed by welding of steel sections, steel plates, etc., and is fixed to the test platform 1 by bolts; the second pin shaft 323 is arranged along the X-axis direction, and the two ends of the support rod 321 are respectively hinged to the generator 5 and the second skeleton 31, so that the generator 5 has a certain degree of freedom in its radial direction, which can compensate for the radial thermal expansion of the generator 5, and utilizes the rotation angle of the joint bearing 322 itself, so that the generator 5 has a certain degree of freedom in its axial direction, which can compensate for the axial thermal expansion of the generator 5. Optionally, the support rod 321 includes a rod body and an adapter, and two adapters are arranged at both ends of the rod body. A screw is arranged on the adapter, and the screw is threadedly connected to the rod body of the support rod 321. A locking nut is arranged on the screw. The length of the support rod 321 can be adjusted by loosening the locking nut and rotating the adapter. After the support rod 321 is adjusted to a specified length, the length of the support rod 321 can be fixed by tightening the locking nut. The adapters at both ends of the support rod 321 can be adjusted, with a large adjustment range, a simple structure, and convenient adjustment operation, thereby ensuring the support strength.

[0029] like Figure 1 and Figure 2 As shown, in this embodiment, for a certain type of integrated turbo-electric system, the air intake of the engine 4 is located between the engine 4 and the generator 5, and a support frame 25 for supporting the air intake grille 7 is arranged on the base plate 12 and / or the first mounting frame 2. The air intake grille 7 of the engine 4 is supported by the support frame 25 to ensure that the air intake of the engine 4 is clean.

[0030] like Figures 7 to 10As shown, in this embodiment, the second mounting frame 3 also includes a second column 33 arranged on the second frame 31 and a second fine-tuning mechanism 34 arranged on the second column 33. The two second columns 33 are arranged side by side in an axial direction perpendicular to the engine 4, and the two auxiliary supports 32 are arranged side by side in an axial direction perpendicular to the engine 4. The second fine-tuning mechanism 34 has the same structure as the first fine-tuning mechanism 23. The two second fine-tuning mechanisms 34 and the two auxiliary supports 32 are connected to the generator 5 to support the generator 5. The two second fine-tuning mechanisms 34 are respectively installed on the two second columns 33, and fix the generator 5 in the left and right directions, and the second fine-tuning mechanism 34 can adjust the installation position of the generator 5 up, down, and Fine adjustments can be made in the four directions of left and right to facilitate the alignment of the engine 4 and the generator 5 during assembly; the two auxiliary supports 32 can compensate for the radial and axial thermal expansion of the generator 5. During the test, the first installation node 233 on a second fine-tuning mechanism 34 is locked by a locking nut (the locking nut is pressed against the support plate 231), and the first installation node 233 on the other second fine-tuning mechanism 34 can slide left and right (a gap is left between the locking nut and the support plate 231). The first fine-tuning mechanism 23 with a movable first installation node 233 and the second fine-tuning mechanism 34 with a movable first installation node 233 are arranged on the same side of the vortex electric system, which can compensate for the radial and axial thermal expansion of the vortex electric system and avoid test safety accidents. Optionally, a lifting ring 211 is arranged on the second skeleton 31 to facilitate the lifting of the second mounting frame 3. Optionally, a reinforcing rib 212 for connecting the second column 33 is arranged on the second skeleton 31 to increase the strength of the second mounting frame 3.

[0031] like Figure 2 and Figure 3 As shown, in this embodiment, a limiting mechanism 14 is arranged on the bottom plate 12, and limiting holes 111 adapted to the limiting mechanism 14 are arranged on the test platform 1 and the linear guide rail 11. The limiting mechanism 14 includes a limiting block 141 and a positioning handle 142. The limiting block 141 is adapted to the limiting hole 111 on the linear guide rail 11. When the bottom plate 12 moves, the pin on the limiting block 141 is retracted. When the bottom plate 12 needs to be positioned, the pin on the limiting block 141 extends out and is inserted into the limiting hole 111 on the linear guide rail 11, thereby limiting the bottom plate 12 and the linear guide rail 11. Relative position; the positioning handle 142 is adapted to the limit hole 111 on the test platform 1. When the base plate 12 moves, the pin on the positioning handle 142 is retracted. When the base plate 12 needs to be positioned, the pin on the positioning handle 142 is extended and inserted into the limit hole 111 on the test platform 1, thereby limiting the relative position of the base plate 12 and the linear guide rail 11; the engine 4 is positioned by the cooperation of the limit block 141 and the positioning handle 142. On the one hand, it is convenient for the centering operation of the engine 4 and the generator 5, and on the other hand, it can ensure the stability of the vortex electric system test.

[0032] like Figure 2 and Figure 3 As shown, in this embodiment, universal wheels 15 and pull rods 16 for pushing and pulling the test platform 1 are arranged on the test platform 1; when the turbine power generation system, the battery, and the propeller form a complete hybrid power system for testing, the pull rod 16 and the universal wheel 15 are used to move the entire test bench, and the vortex electric system is transported. The vortex electric system can be moved to a dedicated indoor propeller test bench or an outdoor test bench for testing, avoiding frequent disassembly and assembly, especially on-site assembly of a split vortex electric system, without the need for repeated multiple alignment work, which can greatly improve the test efficiency. The entire test bench has ductility and versatility due to its movable characteristics.

[0033] like Figure 2 and Figure 3 As shown, in this embodiment, the test platform 1 is provided with telescopic support legs 17 for propping up the test platform 1 so that the universal wheel 15 is off the ground; the telescopic support legs 17 can be telescoped along the Z-axis direction. When the vortex electric system is tested, the telescopic support legs 17 are extended to contact the ground and the universal wheel 15 is off the ground, providing stable experimental conditions for the test; when the vortex electric system needs to be tested in the field, or tested in combination with a propeller, the telescopic support legs 17 are retracted from the ground, the universal wheel 15 is in contact with the ground, and the vortex electric system can be transported.

[0034] Embodiment 1 like Figures 1 to 6 As shown, this embodiment is suitable for an integrated turbo-electric system. The first mounting frame 2 of this embodiment adopts a four-point support for the engine 4, and the first fine-tuning mechanism 23 on the two first columns 22 is the main support, wherein, Figure 4 As shown, the first installation joint 233 on the first fine-tuning mechanism 23 on the right side is locked, and the first installation joint 233 on the first fine-tuning mechanism 23 on the left side can move left and right, which can compensate for the radial thermal expansion of the engine 4; the two fork arms 243 on the support seat 241 can rotate around the first pin shaft 242 and can slide on the first pin shaft 242 along the X-axis direction, which can compensate for the radial and axial thermal expansion of the engine 4; considering that the generator 5 also has a thermal expansion problem, such as Figure 6 As shown, the second mounting frame 3 is supported by a single fulcrum of a retractable support rod 321, and the two ends of the support rod 321 are respectively hinged to the second skeleton 31 and the generator 5, so that the generator 5 has a certain degree of freedom in its radial direction and can compensate for the radial thermal expansion of the generator 5. By utilizing the rotation angle of the joint bearing 322 itself, the generator 5 has a certain degree of freedom in its axial direction and can compensate for the axial thermal expansion of the generator 5.

[0035] For example, the prime mover of a certain type of turboelectric system is a gas turbine, the gas turbine rotor speed exceeds 40,000 rpm, the power shaft speed exceeds 20,000 rpm, and the applicable power can reach 5,000 kW. When the turboelectric system is in operation, the high temperature effects of the gas turbine and generator windings will cause radial and axial thermal expansion of the engine casing and generator casing. In order to be suitable for aviation power, the turboelectric system develops in the direction of high power density, and its volume is getting smaller and smaller, and the thermal expansion is magnified. If a simple fixed mounting frame is used, the stress of the turboelectric system will increase, and in serious cases, test safety accidents may occur.

[0036] In this embodiment, the rear fulcrum support 24 of the engine 4, the first fine-tuning mechanism 23 on the right side and the auxiliary support 32 of the generator 5 are all movable fulcrums, which can compensate for the radial and axial thermal expansion of the entire vortex-electric system, avoid over-constraint problems during installation and testing of the entire vortex-electric system, and ensure smooth testing of the vortex-electric system.

[0037] Embodiment 2 like Figure 4 , Figure 5 , Figures 7 to 9 As shown, this embodiment is applicable to a split turbo-electric system, which is a transitional form of an integrated turbo-electric system. The engine 4 and the generator 5 are connected in series by a connecting shaft 6. The alignment of the engine 4 and the generator 5 cannot be guaranteed by a dimension chain. Sometimes, it is necessary to reserve installation space for the intake system, and it can only be completed on site. The difficulty of centering is much greater than that of a low-speed generator set.

[0038] During assembly, the engine 4 is installed on the first mounting frame 2, and the generator 5 is installed on the second mounting frame 3. A centering tool (laser centering instrument) is installed at the engine end and the generator end. The engine 4 is driven to move up, down, left, and right through the first fine-tuning mechanism 23, and the generator 5 is driven to move up, down, left, and right through the second fine-tuning mechanism 34 to finally complete the centering. After the centering is completed, the base plate 12 is driven by the driving mechanism 13 to adjust the position of the engine 4, and the connecting shaft 6 is installed to connect the engine 4 to the generator 5. After the connecting shaft 6 is installed, the limit mechanism 14 is inserted into the corresponding limit hole 111 to ensure that the position of the vortex electric system remains unchanged.

[0039] The engine 4 of this embodiment is supported by the first mounting frame 2 in a four-point manner, and the first fine-tuning mechanisms 23 on the two first columns 22 are mainly supported. Figure 4As shown, during the test, the first installation joint 233 on the first fine-tuning mechanism 23 on the right is locked, and the first installation joint 233 on the first fine-tuning mechanism 23 on the left can move left and right, which can compensate for the radial thermal expansion of the engine 4; the two fork arms 243 on the support seat 241 can rotate around the first pin shaft 242, and can slide on the first pin shaft 242 along the X-axis direction, which can compensate for the radial and axial thermal expansion of the engine 4; the generator 5 is supported by the second mounting frame 3 in a four-point manner, and the second fine-tuning mechanisms 34 on the two second columns 33 are mainly supported, as shown in FIG. Fig.10 As shown, the first mounting joint 233 on the second fine-tuning mechanism 34 on the right is locked, and the first mounting joint 233 on the second fine-tuning mechanism 34 on the left can move left and right, which can compensate for the radial thermal expansion of the generator 5; two auxiliary supports 32 are connected to the rear fulcrum of the generator 5, and the second pin shaft 323 is arranged along the X-axis direction. The two ends of the support rod 321 are respectively hinged to the generator 5 and the second skeleton 31, so that the generator 5 has a certain degree of freedom in its radial direction, which can compensate for the radial thermal expansion of the generator 5, and the rotation angle of the joint bearing 322 itself is used to make the generator 5 have a certain degree of freedom in its axial direction, which can compensate for the axial thermal expansion of the generator 5.

[0040] In this embodiment, the rear fulcrum support 24 of the engine 4, the first fine-tuning mechanism 23 on the right, the auxiliary support 32 of the generator 5, and the second fine-tuning mechanism 34 on the right are all movable fulcrums, which can compensate for the radial and axial thermal expansion of the entire vortex-electric system, avoid over-constraint problems during installation and testing of the entire vortex-electric system, and ensure smooth testing of the vortex-electric system.

[0041] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A hybrid power turbine power generation system test bench for aviation, characterized in that: The invention comprises a test platform (1), a first mounting frame (2) arranged on the test platform (1) for supporting an engine (4), and a second mounting frame (3) arranged on the test platform (1) for supporting a generator (5); the test platform (1) is provided with a linear guide rail (11) parallel to the axial direction of the engine (4), a bottom plate (12) slidably arranged on the linear guide rail (11), and a driving mechanism (13) for driving the bottom plate (12) to slide relative to the linear guide rail (11); the first mounting frame (2) is arranged on the bottom plate (12), and the driving mechanism (13) drives the first mounting frame (2) to move via the bottom plate (12) so as to adjust the distance between the first mounting frame (2) and the second mounting frame (3).

2. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: The driving mechanism (13) comprises a first screw rod (131) rotatably arranged on the test platform (1) and a driver (132) for driving the first screw rod (131) to rotate, and the first screw rod (131) is threadedly connected to the bottom plate (12).

3. The aviation hybrid power turbine power generation system test bench according to claim 1 or 2, characterized in that: The first mounting frame (2) comprises a first frame (21) arranged on the base plate (12), a first column (22) arranged on the first frame (21), a first fine-tuning mechanism (23) arranged on the first column (22), and a rear fulcrum support (24); the rear fulcrum support (24) comprises a support seat (241), a first pin shaft (242) arranged along the axial direction of the engine (4), and a fork arm (243) slidably hinged to the first pin shaft (242); two first columns (22) are arranged side by side in a direction perpendicular to the axial direction of the engine (4); two fork arms (243) are arranged on the first pin shaft (242); the two fork arms (243) and the two first fine-tuning mechanisms (23) are connected to the engine (4) to support the engine (4).

4. The aviation hybrid power turbine power generation system test bench according to claim 3, characterized in that: The first fine-adjustment mechanism (23) comprises a support plate (231) arranged on the first column (22), an adjustment block (232) arranged on the support plate (231) and movable in a vertical direction relative to the support plate (231), and a first mounting section (233) arranged on the adjustment block (232) for connecting to the engine (4), wherein the axis of the first mounting section (233) is perpendicular to the axis of the engine (4) and arranged in a horizontal direction, and the first mounting section (233) is movable along its axis relative to the adjustment block (232), and the first fine-adjustment mechanism (23) further comprises a locking nut for limiting the relative position of the first mounting section (233) and the adjustment block (232).

5. The aviation hybrid power turbine power generation system test bench according to claim 4, characterized in that: The second mounting frame (3) comprises a second frame (31) arranged on the test platform (1) and an auxiliary support (32) arranged on the second frame (31); the auxiliary support (32) comprises a support rod (321), a joint bearing (322), a second pin shaft (323) and a second mounting joint (324); the support rod (321) can be extended and retracted along its axial direction and its axial length is fixed after extension and retraction; two second pin shafts (323) are respectively arranged at two ends of the support rod (321); the axes of the two second pin shafts (323) are arranged parallel to the axis of the generator (5); the second pin shaft (323) at the bottom end of the support rod (321) is hinged to the second frame (31) via one joint bearing (322); and the second pin shaft (323) at the top end of the support rod (321) is hinged to the second mounting joint (324) via another joint bearing (322).

6. The aviation hybrid power turbine power generation system test bench according to claim 5, characterized in that: A support frame (25) for supporting the air intake grille (7) is arranged on the bottom plate (12) and / or the first mounting frame (2).

7. The aviation hybrid power turbine power generation system test bench according to claim 5, characterized in that: The second mounting frame (3) further comprises a second column (33) arranged on the second frame (31) and a second fine-tuning mechanism (34) arranged on the second column (33); the two second columns (33) are arranged side by side along an axial direction perpendicular to the engine (4); the two auxiliary supports (32) are arranged side by side along an axial direction perpendicular to the engine (4); the second fine-tuning mechanism (34) has the same structure as the first fine-tuning mechanism (23); the two second fine-tuning mechanisms (34) and the two auxiliary supports (32) are connected to the generator (5) to support the generator (5).

8. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: A limiting mechanism (14) is arranged on the bottom plate (12), and a limiting hole (111) adapted to the limiting mechanism (14) is arranged on the test platform (1) and / or the linear guide rail (11).

9. The aviation hybrid power turbine power generation system test bench according to claim 1, characterized in that: The test platform (1) is provided with universal wheels (15) and a pull rod (16) for pushing and pulling the test platform (1).

10. The aviation hybrid power turbine power generation system test bench according to claim 9, characterized in that: The test platform (1) is provided with telescopic support legs (17) for propping up the test platform (1) so that the universal wheels (15) are off the ground.

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