CN110346145B - Boat type aero-engine thrust force measurement rack - Google Patents
Boat type aero-engine thrust force measurement rack Download PDFInfo
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- CN110346145B CN110346145B CN201910642778.5A CN201910642778A CN110346145B CN 110346145 B CN110346145 B CN 110346145B CN 201910642778 A CN201910642778 A CN 201910642778A CN 110346145 B CN110346145 B CN 110346145B
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- 238000005259 measurement Methods 0.000 title claims abstract description 12
- 230000003068 static effect Effects 0.000 claims abstract description 17
- 238000012360 testing method Methods 0.000 abstract description 3
- 230000005484 gravity Effects 0.000 abstract description 2
- 238000011161 development Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 239000007921 spray Substances 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The invention provides a thrust force measurement rack of a ship type aircraft engine, which belongs to the technical field of thrust test devices and comprises a movable rack, a static rack, a force measurement unit and a calibration force loader, wherein the movable rack is fixedly connected with the static rack; a through groove is formed in the static frame, the movable frame is rotatably connected with a group of opposite sides of the through groove through a rotating shaft, a group of symmetrical vertical plates are fixed on the movable frame, and a group of engine mounting seats are arranged at the upper ends of the vertical plates; a group of limiting plates with L-shaped cross sections are symmetrically arranged on the static frame table top corresponding to the other group of opposite sides of the through groove, the horizontal plates of the limiting plates are all positioned above the through groove, the bottom of the horizontal plate of one limiting plate is provided with a calibration force loader, and the bottom of the horizontal plate of the other limiting plate is provided with a force measuring unit; still be provided with fine setting auxiliary stay frame on the quiet frame, fine setting auxiliary stay frame and quiet frame sliding connection are provided with the position centering micromatic setting on the fine setting auxiliary stay frame. The force measuring rack limits the movable rack in the through groove, has low integral gravity center and high safety, can better overcome the thrust eccentricity phenomenon, and has high measuring precision.
Description
Technical Field
The invention belongs to the technical field of thrust testing devices, and particularly relates to a thrust force measuring rack of a boat-type aircraft engine.
Background
The thrust is one of the main performance indexes of the engine, and the accurate measurement of the engine thrust has important significance for the development and performance evaluation of the engine. According to different installation modes, the conventional thrust stand comprises a suspension type thrust stand and a support type thrust stand, and a common flexible part (a spring leaf) or a universal flexible part (a fork spring) is adopted to suspend or support the movable stand. The flexible part has the advantages that the degree of freedom of movement is provided by the elastic deformation of the material, however, as the force sensors cannot be arranged in front of an air inlet of the engine and behind the spray pipe, almost all the existing platforms are off-axis supporting platforms or off-axis suspension platforms, the phenomenon of thrust eccentricity cannot be avoided, namely, the thrust of the engine cannot be accurately transmitted to the thrust sensor due to the fact that the angle between the axis of the engine and the axis of the force sensors deviates, and further certain measurement errors are caused.
With the development of high-performance bearing technology, high-end bearings with high rotating speed, high bearing capacity, low vibration noise and low friction torque are widely used in the fields of high-speed rails, precision machine tools and the like, so that the influence of the external friction connection of the bearings on the precision force measuring equipment such as an aircraft engine rack on the measuring precision is greatly reduced.
Therefore, the application provides a ship type aeroengine thrust dynamometry rack.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a thrust force measuring rack of a boat type aircraft engine, which comprises a movable rack, a stationary rack, a force measuring unit and a calibration force loader, wherein the movable rack is fixedly connected with the stationary rack;
a through groove is formed in the static frame, the movable frame is placed in the through groove, the movable frame is rotatably connected with a group of opposite sides of the through groove through a rotating shaft, a group of symmetrical vertical plates are fixed on the movable frame, and a group of engine mounting seats are arranged at the upper ends of the vertical plates;
a group of limiting plates with L-shaped cross sections are symmetrically arranged on the static frame table top corresponding to the other group of opposite sides of the through groove, horizontal plates of the limiting plates are all positioned above the through groove, the bottom of the horizontal plate of the limiting plate on one side is provided with the calibration force loader, and the bottom of the horizontal plate of the limiting plate on the other side is provided with the force measuring unit;
the fine adjustment auxiliary support frame is arranged on the static frame and located on one side of the force measurement unit, the fine adjustment auxiliary support frame is connected with the static frame in a sliding mode, a position centering fine adjuster is arranged on the fine adjustment auxiliary support frame, and the symmetry axis of the engine and the axial central axis of the movable frame are parallel to each other in a vertical plane through adjusting a fine adjustment device on the position centering fine adjuster.
Preferably, the force measuring unit is formed by connecting a universal flexible piece, a force measuring sensor and a universal flexible piece in series.
Preferably, a pair of edges of the through groove is provided with a mounting block, a bearing is mounted in the mounting block, the rotating shaft penetrates through the movable frame and is fixedly connected with the movable frame, and two ends of the rotating shaft are connected with the inner rings of the bearings respectively.
Preferably, the stationary frame is provided with a guide rail, the bottom of the fine adjustment auxiliary support frame is provided with a pulley matched with the guide rail, and the fine adjustment auxiliary support frame is driven by the pulley to move horizontally along the guide rail so as to adapt to different engine mounting structures.
Preferably, the number of the position centering micro-regulators is two, and the two position centering micro-regulators are respectively arranged on two sides of the interior of the fine-adjustment auxiliary supporting frame.
Preferably, the force measuring device further comprises a controller, the force measuring unit is electrically connected with a signal input end of the controller, and the calibration force loader is electrically connected with a signal output end of the controller.
The thrust force measuring rack of the ship type aircraft engine provided by the invention utilizes the principle that when the rotating frame rotates around the rotating shaft, the 3 vertex tangential forces are equal in magnitude, only one sensor is adopted to directly measure the magnitude of the thrust force, and only one calibration force loader is needed to convert the axial thrust force into the vertical force for measurement and calibration. The force measuring rack is simple in structure, relatively easy to assemble, high in applicability, capable of limiting the movable rack in the through groove, low in overall gravity center, high in safety, capable of overcoming the thrust eccentricity phenomenon well and high in measuring accuracy.
Drawings
Fig. 1 is a schematic structural view of a thrust force measuring rack of a boat-type aircraft engine in embodiment 1 of the present invention;
FIG. 2 is a schematic view of a fixed mounting structure of the engine;
FIG. 3 is a diagram of a force cell configuration;
FIG. 4 is a schematic view of a fine tuning auxiliary support frame.
Description of reference numerals:
1-a static frame, 2-a calibration force loader, 3-a movable frame, 4-an engine fixed mounting structure, 5-a bearing, 6-a force measuring unit, 7-a fine adjustment auxiliary support frame, 8-a position centering fine adjuster, 9-a guide rail, 10-a zero-return leveling device, 11-a through groove, 12-a rotating shaft, 13-a vertical plate, 14-a limiting plate, 15-a mounting block, 16-a controller and 17-a caliper.
Detailed Description
The following further describes embodiments of the present invention with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing technical solutions of the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. In the description of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "connected" and "connected" are to be interpreted broadly, e.g., as a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations. In the description of the present invention, unless otherwise specified, "a plurality" means two or more, and will not be described in detail herein.
Example 1
The invention provides a thrust force measuring rack of a ship type aircraft engine, which is particularly shown in figures 1 to 4 and comprises a movable rack 3, a static rack 1, a force measuring unit 6 and a calibration force loader 2;
a through groove 11 is formed in the static frame 1, the movable frame 3 is placed in the through groove 11, the movable frame 3 is rotatably connected with a group of opposite sides of the through groove 11 through a rotating shaft 12, a group of symmetrical vertical plates 13 are fixed on the movable frame 3, and a group of engine mounting seats 4 are arranged at the upper ends of the vertical plates 13;
a group of limiting plates 14 with L-shaped cross sections are symmetrically arranged on the table top of the static frame 1 corresponding to the other pair of the opposite sides of the through groove 11, the horizontal plates of the limiting plates 14 are all positioned above the through groove 11, the calibration force loader 2 is arranged at the bottom of the horizontal plate of the limiting plate 14 on one side, and the force measuring unit 6 is arranged at the bottom of the horizontal plate of the limiting plate 14 on the other side. The force measuring unit 6 used in the embodiment is commonly used in the aviation industry at present, the universal flexible parts at two ends can play a role in decoupling force, only axial force is ensured to be exerted on the middle sensor, and the tangential force of each point on the circumference of the model force is equal, so that the tangential force is ensured to be measured.
Still be provided with fine setting auxiliary stay frame 7 on the quiet frame 1, the engine is longer, has two to three erection joint, and engine mount pad 4 can with main erection joint flange assembly, and fine setting auxiliary stay frame 7 plays auxiliary stay's effect at the back, and in order to guarantee that the power on the engine mount pad 4 is the level tangential force, fine setting auxiliary stay frame 7 need can finely tune the assurance axis level, and parallel in vertical plane with the axis of moving frame 3. Fine setting auxiliary stay frame 7 is located force cell 6 one side, and fine setting auxiliary stay frame 7 and quiet 1 sliding connection of putting up are concrete, in this embodiment, be provided with guide rail 9 on the quiet frame 1, and fine setting auxiliary stay frame 7 bottom is provided with guide rail 9 complex pulley, and fine setting auxiliary stay frame 7 is along 9 horizontal migration of guide rail in order to adapt to different engine mounting structure under the drive of pulley. Be provided with position centering micromatic setting 8 on the fine setting auxiliary stay frame 7, the quantity of position centering micromatic setting 8 in this embodiment is two, and two position centering micromatic settings 8 set up respectively in the inside both sides of fine setting auxiliary stay frame 7, through the micromatic setting on the position centering micromatic setting 8 of adjustment, realize that the symmetry axis of engine and the axial axis of movable frame 3 are parallel to each other in vertical plane.
Specifically, in this embodiment, the pair of edges of the through groove 11 are provided with the mounting blocks 15, the bearings 5 are mounted in the mounting blocks 15, the rotating shaft 12 penetrates through the movable frame 3 and is fixedly connected with the movable frame 3, and two ends of the rotating shaft 12 are respectively connected with the inner rings of the two bearings 5.
In order to realize position adjustment, the device further comprises a zero-alignment leveling device 10 arranged on one side of the stationary frame 1, wherein the zero-alignment leveling device 10 is connected with the bearing 5 to control the whole movable frame 3 to be kept horizontal. The zero leveling device 10 in the embodiment is an existing component, which essentially applies a torque, can apply an auxiliary torque in a self-adaptive manner, and overcomes the problem that the bottom plate of the movable frame is not level.
In order to realize accurate control, the force measuring unit 6 further comprises a controller 16 in the embodiment, the force measuring unit is electrically connected with a signal input end of the controller 16, and the calibration force loader 2 is electrically connected with a signal output end of the controller 16.
Fig. 2 is a schematic view of the engine mount 4 viewed in the longitudinal direction, i.e. perpendicular to the plane of the engine axis, the engine mount 4 being provided with a caliper 17, similar to a disc brake of a car, for fixing a main mount flange, the shaft at the right end being telescopic to accommodate different engine radii.
In specific implementation, the method is divided into a measurement implementation stage and a calibration implementation stage.
And (3) a measuring stage:
1. the initial static frame is installed, locked and fixed, and the movable frame 3 is kept to horizontally deflect zero through the zero-alignment leveling device 10;
2. the engine is arranged on the engine fixing and installing structure 4, then the tail part of the engine is adjusted through two position centering micro-adjusters 8, and the position centering micro-adjusters 8 are kept in basically frictionless contact with the engine auxiliary installing section after adjustment;
3. the leveling device 10 for comprehensive adjustment and zero return and the position centering fine adjuster 8 keep the axis of the engine parallel to the axis of the movable frame 3 and the movable frame 3 horizontally deflecting in zero, and the calipers 17 lock and fix the engine;
4. the load cell is zeroed and the engine is started for testing.
When the engine generates thrust, the movable frame and the engine rotate around the bearing simultaneously, so that the movable frame acts on the force measuring sensor to measure the magnitude of the thrust of the engine, and the thrust is transmitted to the computer through the controller.
A calibration stage:
1. taking down the engine, resetting the movable frame 3, keeping horizontal zero deflection, and resetting the sensor to zero;
2. the computer and the controller send a loading command to the calibration force loader according to the calibration force loading table, and the force measuring sensor obtains a series of values so as to evaluate the force measuring performance of the rack;
3. if the performance of the rack needs to be evaluated more strictly, an in-situ calibration method can be adopted for error calibration, and the force of the thrust of the engine can be simulated by applying the horizontal direction at the intersection point of the symmetry axis of the engine and the perpendicular bisector of the movable rack, so that the calibration is carried out.
The application provides a boat form aeroengine thrust rack, its movable support adopt the principle that each tangential direction power size equals on the homogeneity disc, ingenious with the engine to the horizontal direction thrust of main pivot turn into the pressure or the pulling force of vertical direction, then measure the size of this thrust with the dynamometry unit that the stern was vertical put, when carrying out the calibration, also only need exert the power of vertical direction at the prow and calibrate can.
The above-mentioned embodiments are only preferred embodiments of the present invention, and the scope of the present invention is not limited thereto, and any simple modifications or equivalent substitutions of the technical solutions that can be obviously obtained by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Claims (6)
1. A thrust force measurement rack of a ship type aircraft engine is characterized by comprising a movable rack (3), a static rack (1), a force measurement unit (6) and a calibration force loader (2);
a through groove (11) is formed in the static frame (1), the movable frame (3) is placed in the through groove (11), the movable frame (3) is rotatably connected with a group of opposite sides of the through groove (11) through a rotating shaft (12), a group of symmetrical vertical plates (13) are fixed on the movable frame (3), and a group of engine mounting seats (4) are arranged at the upper ends of the vertical plates (13);
a group of limiting plates (14) with L-shaped cross sections are symmetrically arranged on the table top of the static frame (1) corresponding to the other pair of the through grooves (11), horizontal plates of the limiting plates (14) are all positioned above the through grooves (11), the bottom of the horizontal plate of the limiting plate (14) at one side is provided with the calibration force loader (2), and the bottom of the horizontal plate of the limiting plate (14) at the other side is provided with the force measuring unit (6);
still be provided with fine setting auxiliary stay frame (7) on quiet frame (1), fine setting auxiliary stay frame (7) are located dynamometry unit (6) one side, fine setting auxiliary stay frame (7) with quiet frame (1) sliding connection, be provided with position centering micromatic setting (8) on fine setting auxiliary stay frame (7), through the adjustment micromatic setting on position centering micromatic setting (8), realize the symmetry axis of engine with the axial axis of moving frame (3) is parallel to each other in vertical plane.
2. The thrust dynamometric gantry of a boat-type aircraft engine according to claim 1, characterized in that the dynamometric cell (6) is formed by a universal flexure, a dynamometric sensor, and a universal flexure connected in series in this order.
3. The thrust force measuring platform of the ship type aircraft engine as claimed in claim 1, wherein a pair of edges of the through groove (11) are provided with mounting blocks (15), bearings (5) are mounted in the mounting blocks (15), the rotating shaft (12) penetrates through the movable frame (3) and is fixedly connected with the movable frame (3), and two ends of the rotating shaft (12) are respectively connected with inner rings of the two bearings (5).
4. The boat-type aircraft engine thrust force measurement platform of claim 1, wherein a guide rail (9) is arranged on the static frame (1), a pulley matched with the guide rail (9) is arranged at the bottom of the fine adjustment auxiliary support frame (7), and the fine adjustment auxiliary support frame (7) is driven by the pulley to horizontally move along the guide rail (9) so as to adapt to different engine mounting structures.
5. The thrust dynamometer platform of boat aircraft engine according to claim 1, characterized in that the number of said position centering trimmers (8) is two, and two of said position centering trimmers (8) are respectively disposed on both sides of the inside of said fine adjustment auxiliary support frame (7).
6. The naval aircraft engine thrust dynamometric gantry of claim 1, further comprising a controller (16), wherein the dynamometric cell (6) is electrically connected to a signal input of the controller (16), and wherein the calibration force loader (2) is electrically connected to a signal output of the controller (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910642778.5A CN110346145B (en) | 2019-07-16 | 2019-07-16 | Boat type aero-engine thrust force measurement rack |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910642778.5A CN110346145B (en) | 2019-07-16 | 2019-07-16 | Boat type aero-engine thrust force measurement rack |
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| Publication Number | Publication Date |
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| CN110346145A CN110346145A (en) | 2019-10-18 |
| CN110346145B true CN110346145B (en) | 2021-03-19 |
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| CN201910642778.5A Expired - Fee Related CN110346145B (en) | 2019-07-16 | 2019-07-16 | Boat type aero-engine thrust force measurement rack |
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| CN114216688B (en) * | 2021-11-12 | 2023-08-04 | 南京航空航天大学 | Miniature turbine engine thrust measuring device and application method thereof |
| CN114199456B (en) * | 2021-11-18 | 2024-10-18 | 湖南崇德科技股份有限公司 | Large-scale thrust sliding bearing static self-balancing capability test rack |
| CN114235426A (en) * | 2021-12-16 | 2022-03-25 | 南京航空航天大学 | Support miniature turbojet engine test bench of dysmorphism spray tube |
| CN114923617B (en) * | 2022-07-21 | 2022-10-25 | 中国航发四川燃气涡轮研究院 | Engine lift force measuring device |
| CN115307924B (en) * | 2022-10-12 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Dynamic ground effect simulation system for shipborne test run of aircraft engine |
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Granted publication date: 20210319 |