CN210375704U - Aeroengine test bench - Google Patents
Aeroengine test bench Download PDFInfo
- Publication number
- CN210375704U CN210375704U CN201921588963.2U CN201921588963U CN210375704U CN 210375704 U CN210375704 U CN 210375704U CN 201921588963 U CN201921588963 U CN 201921588963U CN 210375704 U CN210375704 U CN 210375704U
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- thrust
- strain gauge
- adjusting mechanism
- test
- torque transmission
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Abstract
The utility model relates to the field of aircraft engine test equipment, in particular to an aircraft engine test bench, which comprises an installation bench, a test platform, a bracket, a pitching adjusting mechanism and a tilting adjusting mechanism, wherein the bracket and the pitching adjusting mechanism are arranged on the installation bench, and the pitching adjusting mechanism is used for driving the bracket to swing on the installation bench; the inclination adjusting mechanism is arranged on the bracket, the test platform is arranged on the inclination adjusting mechanism, and the inclination adjusting mechanism is used for controlling the inclination state of the test platform. The test bench is characterized in that a pitching adjusting mechanism is installed to drive a bracket on the test bench to rotate, an inclination adjusting mechanism is arranged on the bracket, and a test platform for installing the aero-engine to be tested is fixed on the inclination adjusting mechanism, so that pitching angle adjustment and inclination angle adjustment can be respectively realized when the aero-engine is tested by the test bench, and pitching and inclination angle adjustment can be simultaneously carried out on the aero-engine.
Description
Technical Field
The utility model relates to an aeroengine test equipment field, concretely relates to aeroengine test rack.
Background
Aircraft engines are the core components of an aircraft, and the performance of the aircraft engine directly determines the overall performance of the aircraft. In order to ensure the excellent performance of the aircraft engine and ensure the smooth implementation of various procedures such as the design, development and maintenance of the aircraft engine, the ground test of the aircraft engine becomes an important task. Due to the rapid development of aeronautical science and technology in recent years, the requirements and standards for test benches for aircraft engine testing are constantly increasing. The method mainly shows that the test content is more and more complex, the test requirement of the aircraft engine is more and more, the types of test items and parameters are more and more, and in most of laboratory or research institute environments, the test angle of the aircraft engine is often required to be adjusted under the condition of no parking so as to simulate the states and parameters of the aircraft during horizontal rising, diving and turning. Therefore, the test bench must be capable of simulating engine pitch, engine tilt, and simultaneous multi-angle rotation of engine pitch and tilt to meet the test requirements of different flight conditions for the aircraft engine. Therefore, there is a need for a test bench that can adjust pitch, tilt, and pitch and tilt angles without stopping the aircraft engine during testing.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model aims at overcoming the defect among the prior art, provide an aeroengine test bench.
In order to solve the technical problem, the utility model discloses a following technical scheme:
an aircraft engine test bench comprises an installation bench, a test platform, a bracket, a pitching adjusting mechanism and a tilting adjusting mechanism, wherein the bracket and the pitching adjusting mechanism are arranged on the installation bench, and the pitching adjusting mechanism is used for driving the bracket to swing on the installation bench; the inclination adjusting mechanism is arranged on the bracket, the test platform is arranged on the inclination adjusting mechanism, and the inclination adjusting mechanism is used for controlling the inclination state of the test platform.
Further, the pitch adjusting mechanism comprises a first slewing bearing and a first driving motor, and an output shaft of the first driving motor is connected with a worm shaft of the first slewing bearing; one end of the bracket is connected with the first rotary support, and the first driving motor drives the first rotary support to drive the bracket to swing on the mounting rack.
Further, the tilt adjusting mechanism comprises a second rotary support and a second driving motor, and an output shaft of the second driving motor is connected with a worm shaft of the second rotary support.
The rotating shaft is fixed in a rotating inner ring of the second slewing bearing; the test platform comprises a test system mounting bottom plate, the test system mounting bottom plate is mounted on the rotating shaft, and the test system mounting bottom plate rotates along the central axis of the second slewing bearing along with the rotating shaft.
Further, the central axis of the rotating shaft is coincident with the central axis of the second slewing bearing.
Further, a thrust transmission sliding plate is arranged on the testing system installation bottom plate in a sliding mode, and the sliding direction of the thrust transmission sliding plate is parallel to the central axis of the second slewing bearing.
Further, a torque testing device is arranged on the thrust transmission sliding plate and comprises a torque transmission shaft, a torque transmission shaft support, a torque transmission plate, a torque strain gauge and a torque strain gauge fixing seat; the two torque transmission shaft supports are arranged on the thrust transmission sliding plate at intervals, the torque transmission shafts are rotatably connected with the two torque transmission shaft supports, and an engine mounting plate is arranged at the front ends of the torque transmission shafts;
the torque transmission plate is arranged on the torque transmission shaft, the torque strain gauge fixing seat is arranged on the thrust transmission sliding plate, and two ends of the torque strain gauge are respectively connected to the torque transmission plate and the torque strain gauge fixing seat.
Further, the central axes of the two torque transmission shaft supports are overlapped and are positioned on the same vertical plane with the central axis of the rotating shaft, and the central axes of the torque transmission shaft supports are parallel to the central axis of the rotating shaft.
Furthermore, a thrust testing device is arranged on the testing system mounting base plate and comprises a thrust strain gauge top block, a thrust strain gauge and a thrust strain gauge fixing base, the thrust strain gauge top block is arranged on the thrust transmission sliding plate, the thrust strain gauge fixing base is arranged on the testing system mounting base plate, and two ends of the thrust strain gauge are respectively connected to the thrust strain gauge top block and the thrust strain gauge fixing base.
The utility model has the advantages that: the utility model discloses an aeroengine test rack, it drives the bracket rotation on the test rack through installation every single move adjustment mechanism to set up the slope adjustment mechanism on the bracket, and a test platform for installing the examination aeroengine that awaits measuring fixes on the slope adjustment mechanism, consequently, aeroengine can realize the angle modulation of every single move and the angle modulation of slope (turn) respectively when this test rack tests, and the engine carries out the angle modulation of every single move and slope simultaneously. Furthermore, the pitching adjusting mechanism and the tilting adjusting mechanism are respectively composed of a slewing bearing, a worm shaft and a driving motor, the worm shaft can drive the slewing bearing to rotate and can respectively simulate the test angle adjustment of the aircraft engine in the pitching and turning states, the driving motor drives the worm shaft to rotate and can drive the slewing bearing to rotate according to the corresponding angle, so that the real-time angle adjustment of the engine in the non-stop state in the test process is realized, and the performance parameters such as thrust, torque and the like are rapidly and accurately measured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a schematic structural view of an aircraft engine test bench according to the present invention;
FIG. 2 is a schematic structural view of a pitch adjustment mechanism and a tilt adjustment mechanism;
FIG. 3 is a top view of the test platform;
fig. 4 is a side view of a test platform.
Reference numerals:
1-an installation bench, 11-a base, 12-a left stand, 13-a right stand, 14-a diagonal brace, 2-a test platform, 21-a test system installation bottom plate, 22-a rotating shaft, 23-a thrust transmission sliding plate, 24-an engine installation plate, 25-a guide rail, 26-a limiting block, 3-a bracket, 31-a cross beam, 32-a left side plate, 33-a right side plate, 4-a pitching adjusting mechanism, 41-a first slewing bearing, 42-a first driving motor, 5-a tilting adjusting mechanism, 51-a second slewing bearing, 52-a second driving motor, 6-a bearing support, 7-a torque test device, 71-a torque transmission shaft, 72-a torque transmission shaft support, 73-a torque transmission plate, 74-a torque strain gauge, 75-torque strain gauge fixing seat, 8-thrust testing device, 81-thrust strain gauge top block, 82-thrust strain gauge and 83-thrust strain gauge fixing seat.
Detailed Description
The present invention will be described in further detail with reference to examples.
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1, the utility model provides an aeroengine test bench, specifically, this test bench includes mounting rack 1, test platform 2, bracket 3, every single move adjustment mechanism 4 and slope adjustment mechanism 5, and bracket 1 and every single move adjustment mechanism 4 set up on mounting rack 1, and every single move adjustment mechanism 4 is used for driving bracket 3 to swing on mounting rack 1; the inclination adjusting mechanism 5 is arranged on the bracket 3, the test platform 2 is arranged on the inclination adjusting mechanism 5, and the inclination adjusting mechanism 5 is used for controlling the inclination state of the test platform 2.
The utility model discloses a test bench comprises five parts of installing rack 1, test platform 2, bracket 3, every single move adjustment mechanism 4 and slope adjustment mechanism 5. Wherein, the bracket 3 and the pitching adjusting mechanism 4 are both arranged on the mounting rack 1, and the tilting adjusting mechanism 5 provided with the test platform 2 is arranged on the bracket 3. Further, a carriage 3 is swingably provided on the mounting stand 1, and a pitch adjustment mechanism 4 is connected to the carriage 3 for providing a driving force for the swing of the carriage 3. The bracket 3 on the mounting rack 1 is driven to swing by the mounting pitch adjusting mechanism 4, so that the ascending or diving state of the engine is simulated; and a tilt adjusting mechanism 5 is provided on the bracket 3, and a test platform 2 for mounting an aircraft engine to be tested is provided on the tilt adjusting mechanism 5, thereby simulating a turning state of the engine. When the test bench is used for testing, the aero-engine can independently realize the angle adjustment in the pitching state and the angle adjustment in the tilting (turning) state respectively, and simultaneously carry out the angle adjustment in the pitching state and the tilting state, so that the real-time angle adjustment of the engine in the non-stop state in the test process is realized.
The "pitch" in the pitch adjustment mechanism 4 means that when the first slewing bearing 41 swings the cradle 3 on the mounting stand 1, the angle between the center axis of the torque transmission shaft 71 on the test platform 2 and the horizontal line is changed to simulate the ascending or descending state of the engine, thereby measuring the thrust performance parameter of the engine in the ascending or descending state. (Components are further described below)
The term "tilt" in the tilt adjusting mechanism 5 refers to that when the second rotary support 51 rotates the testing platform 2, the central axis of the torque transmission shaft 71 is rotated along the central axis of the second rotary support 51, so as to simulate the rotating tilt (i.e. turn) when the engine is in a horizontal state, thereby measuring the torque performance parameter of the engine in a tilted state. (Components are further described below)
In the present embodiment, the installation stand 1 includes a base 11, a left stand 12, and a right stand 13, and the left stand 12 and the right stand 13 are oppositely disposed on the base 11. The left vertical frame 12, the right vertical frame 13 and the base 11 are connected with inclined struts 14. The base 11 is arranged horizontally, and the left vertical frame 12 and the right vertical frame 13 are respectively arranged on the base 11 and used for providing stable support for the bracket 3, the pitch adjusting mechanism 4, the tilt adjusting mechanism 5 and the like. The mounting rack 1 further comprises an inclined strut 14, the upper end of the inclined strut 14 is connected with the upper ends of the left vertical frame 12 and the right vertical frame 13 respectively, and the lower end of the inclined strut 14 is fixed on the base 11. Strengthen firmly through a bracing 14 between left grudging post 12 and the base 11, also strengthen firmly through a bracing 14 between right grudging post 13 and the base 11 to improve this test bench's intensity and stability.
In the present embodiment, the pitch adjustment mechanism 4 is provided on the right vertical frame 13, the bearing support 6 is provided on the left vertical frame 12, the bracket 3 is arranged in an inverted "shape, and the bracket 3 is composed of a cross beam 31, and a left side plate 32 and a right side plate 33 provided at both ends of the cross beam 31, respectively. Wherein, the top of left side board 32 and the top of right side board 33 are provided with the journal stirrup that extends to outside respectively to make this bracket 3 be "nearly" font structure, this structure can make the focus of test platform 2 on the bracket 3 lower, thereby make the test more stable. Further, the two lugs are rotatably connected to the bearing support 6 of the left stand 12 and the pitch adjustment mechanism 4 of the right stand 13, respectively, so that the bracket 3 can swing between the left stand 12 and the right stand 13.
The pitch adjusting mechanism 4 comprises a first slewing bearing 41 and a first driving motor 42, wherein an output shaft of the first driving motor 42 is connected with a worm shaft of the first slewing bearing 41; one end of the bracket 3 is connected with the first rotary support 41, and the first driving motor 42 drives the first rotary support 41 to drive the bracket 3 to swing on the mounting rack 1.
In the present embodiment, the first drive motor 42 is a servo motor with a brake function. The first driving motor 42 drives the first worm shaft of the first pivoting support 41 to rotate, the structure is simple and compact, and the first pivoting support 41 can be conveniently controlled to rotate according to the designed angle, so that the bracket 3 can rotate according to the designed angle, and the real-time angle adjustment of the pitching state of the engine under the non-stop state in the test process is realized. The first slewing bearing 41 is prior art and will not be described in detail herein.
Further, the tilt adjusting mechanism 5 includes a second slewing bearing 51 and a second drive motor 52, and an output shaft of the second drive motor 52 is connected to a worm shaft of the second slewing bearing 51. The rotary shaft 22 is further included, and the rotary shaft 22 is fixed in a rotary inner ring of the second rotary support 51; the test platform 2 comprises a test system mounting base plate 21, the test system mounting base plate 21 is mounted on the rotating shaft 22, and the test system mounting base plate 21 rotates along the central axis of the second pivoting support 51 along with the rotating shaft 22.
The structure and connection relationship of the tilt adjusting mechanism 5 are the same as those of the pitch adjusting mechanism 4, and are not described herein again, and in this embodiment, the second driving motor 52 also employs a servo motor with a braking function. The second driving motor 52 drives the worm shaft of the second slewing bearing 51 to rotate, and is used for controlling the second slewing bearing 51 to rotate according to a designed angle, so that the testing platform 2 can rotate along the central axis of the second slewing bearing 51 along with the rotating shaft 22, and real-time testing angle adjustment of the engine in a non-stop inclined state in a testing process is realized.
Further, in order to improve the accuracy of the test result, the central axis of the rotating shaft 22 coincides with the central axis of the second slewing bearing 51.
In the present embodiment, the test system mounting base plate 21 is slidably provided with a thrust transmission sliding plate 23, and the sliding direction of the thrust transmission sliding plate 23 is parallel to the central axis of the second slewing bearing 51. Further, a torque testing device 7 is arranged on the thrust transmission sliding plate 23, and the torque testing device 7 comprises a torque transmission shaft 71, a torque transmission shaft support 72, a torque transmission plate 73, a torque strain gauge 74 and a torque strain gauge fixing seat 75; two torque transmission shaft supports 72 are arranged on the thrust transmission sliding plate 23 at intervals, a torque transmission shaft 71 is rotatably connected with the two torque transmission shaft supports 72, and the front end of the torque transmission shaft 71 is provided with an engine mounting plate 24; the torque transmission plate is arranged on the torque transmission shaft, the torque strain gauge fixing seat is arranged on the thrust transmission sliding plate, and two ends of the torque strain gauge 74 are respectively connected to the torque transmission plate 73 and the torque strain gauge fixing seat 75.
When the test bench is in an initial state, the test system installation bottom plate 21 is horizontally arranged, taking the direction shown in fig. 4 as an example, a guide rail 25 is transversely arranged at the top of the test system installation bottom plate 21, a sliding seat is arranged at the bottom of the thrust transmission sliding plate 23 corresponding to the guide rail 25, the sliding seat is in fit with the guide rail 25, so that the thrust transmission sliding plate 23 is slidably installed on the test system installation bottom plate 21, and in order to prevent the thrust transmission sliding plate 23 from sliding out of the guide rail 25, a limit block 26 is arranged at the front end of the guide rail 25 (i.e. the end of the guide rail 25 close to.
In the present embodiment, two torque transmission shaft supports 72 are provided on the thrust transmission slide plate 23, and the two torque transmission shaft supports 72 together provide a supporting function for the torque transmission shaft 71. The torque transmission shaft 71 is a cylinder, the front end of the torque transmission shaft 71 is provided with an engine mounting plate 24 for mounting an engine to be tested, the central axis of the torque transmission shaft 71 is parallel to the length direction of the mounting rack 1, and the torque transmission shaft 71 is mounted in a torque transmission shaft support 72 through a bearing, so that the torque transmission shaft 71 can rotate around the central axis of the torque transmission shaft support 72. Further, a groove is formed on the torque transmission shaft 71, the torque transmission plate 73 is installed in the groove, and the torque transmission shaft 71 can drive the torque transmission plate 73 to synchronously rotate when rotating. The torque gauge fixing seat 75 is fixed to the thrust force transmission sliding plate 23 by bolts, and both ends of the torque gauge 74 are connected to the torque transmission plate 73 and the torque gauge fixing seat 75, respectively, so that the torque transmission plate 73 can press the torque gauge 74 after the torque transmission shaft 71 drives the torque transmission plate 73 to rotate.
In the present embodiment, the central axes of the two torque transmission shaft supports 72 coincide and are located on the same vertical plane as the central axis of the rotating shaft 22, and the central axes of the torque transmission shaft supports 72 are parallel to the central axis of the rotating shaft 22.
Furthermore, the test system mounting base plate 21 is provided with a thrust test device 8, the thrust test device 8 includes a thrust strain gauge top block 81, a thrust strain gauge 82 and a thrust strain gauge fixing base 83, the thrust strain gauge top block 81 is provided on the thrust transmission sliding plate 23, the thrust strain gauge fixing base 83 is provided on the test system mounting base plate 21, and both ends of the thrust strain gauge 82 are respectively connected to the thrust strain gauge top block 81 and the thrust strain gauge fixing base 83.
In order to meet the thrust test requirements of the aircraft engine, the test system further comprises a thrust test device 8. Specifically, the thrust strain gauge top block 81 is fixed at a middle position of a rear end of the thrust transmission sliding plate 23 (the rear end refers to an end of the thrust transmission sliding plate 23 away from the engine mounting plate 24) by bolts, the thrust strain gauge fixing seat 83 is fixed at a rear position on the test system mounting base plate 21 by bolts, and both ends of the thrust strain gauge 82 are respectively connected to the thrust strain gauge top block 81 and the thrust strain gauge fixing seat 83, so that the thrust strain gauge top block 81 can squeeze the thrust strain gauge 82 after the thrust transmission sliding plate 23 drives the thrust strain gauge top block 81 to slide.
Finally, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.
Claims (9)
1. The utility model provides an aeroengine test bench which characterized in that: the test bench comprises an installation bench, a test platform, a bracket, a pitching adjusting mechanism and a tilting adjusting mechanism, wherein the bracket and the pitching adjusting mechanism are arranged on the installation bench, and the pitching adjusting mechanism is used for driving the bracket to swing on the installation bench; the inclination adjusting mechanism is arranged on the bracket, the test platform is arranged on the inclination adjusting mechanism, and the inclination adjusting mechanism is used for controlling the inclination state of the test platform.
2. The aircraft engine test rig of claim 1, wherein: the pitching adjusting mechanism comprises a first slewing bearing and a first driving motor, and an output shaft of the first driving motor is connected with a worm shaft of the first slewing bearing; one end of the bracket is connected with the first rotary support, and the first driving motor drives the first rotary support to drive the bracket to swing on the mounting rack.
3. The aircraft engine test rig of claim 1, wherein: the inclination adjusting mechanism comprises a second rotary support and a second driving motor, and an output shaft of the second driving motor is connected with a worm shaft of the second rotary support.
4. The aircraft engine test rig of claim 3, wherein: the rotating shaft is fixed in a rotating inner ring of the second slewing bearing; the test platform comprises a test system mounting bottom plate, the test system mounting bottom plate is mounted on the rotating shaft, and the test system mounting bottom plate rotates along the central axis of the second slewing bearing along with the rotating shaft.
5. The aircraft engine test rig of claim 4, wherein: the central axis of the rotating shaft is coincided with the central axis of the second slewing bearing.
6. An aircraft engine test rig according to claim 4 or 5, wherein: and a thrust transfer sliding plate is arranged on the mounting bottom plate of the test system in a sliding manner, and the sliding direction of the thrust transfer sliding plate is parallel to the central axis of the second slewing bearing.
7. The aircraft engine test rig of claim 6, wherein: a torque testing device is arranged on the thrust transmission sliding plate and comprises a torque transmission shaft, a torque transmission shaft support, a torque transmission plate, a torque strain gauge and a torque strain gauge fixing seat; the two torque transmission shaft supports are arranged on the thrust transmission sliding plate at intervals, the torque transmission shafts are rotatably connected with the two torque transmission shaft supports, and an engine mounting plate is arranged at the front ends of the torque transmission shafts;
the torque transmission plate is arranged on the torque transmission shaft, the torque strain gauge fixing seat is arranged on the thrust transmission sliding plate, and two ends of the torque strain gauge are respectively connected to the torque transmission plate and the torque strain gauge fixing seat.
8. The aircraft engine test rig of claim 7, wherein: the central axes of the two torque transmission shaft supports are overlapped and are positioned on the same vertical plane with the central axis of the rotating shaft, and the central axes of the torque transmission shaft supports are parallel to the central axis of the rotating shaft.
9. The aircraft engine test rig of claim 6, wherein: the testing system comprises a testing system mounting base plate and is characterized in that a thrust testing device is arranged on the testing system mounting base plate and comprises a thrust strain gauge top block, a thrust strain gauge and a thrust strain gauge fixing seat, the thrust strain gauge top block is arranged on a thrust transmission sliding plate, the thrust strain gauge fixing seat is arranged on the testing system mounting base plate, and two ends of the thrust strain gauge are respectively connected to the thrust strain gauge top block and the thrust strain gauge fixing seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921588963.2U CN210375704U (en) | 2019-09-20 | 2019-09-20 | Aeroengine test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921588963.2U CN210375704U (en) | 2019-09-20 | 2019-09-20 | Aeroengine test bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210375704U true CN210375704U (en) | 2020-04-21 |
Family
ID=70255285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921588963.2U Expired - Fee Related CN210375704U (en) | 2019-09-20 | 2019-09-20 | Aeroengine test bench |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210375704U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112230091A (en) * | 2020-10-27 | 2021-01-15 | 苏州菲利波电磁技术有限公司 | Lifting adjusting device and electric automobile wireless charging radiation emission test rack |
-
2019
- 2019-09-20 CN CN201921588963.2U patent/CN210375704U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112230091A (en) * | 2020-10-27 | 2021-01-15 | 苏州菲利波电磁技术有限公司 | Lifting adjusting device and electric automobile wireless charging radiation emission test rack |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211201 Address after: 400032 9-11, building 2, No. 15, Shidai Tianjie street, Yuzhong District, Chongqing Patentee after: Chongqing Beili Intelligent Technology Co.,Ltd. Address before: 400000 Beihu County, Yuanyang street, Yubei District, Chongqing Patentee before: Wu Liangjun |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200421 |