CN110346145A - A kind of boat form aeroengine thrust dynamometry rack - Google Patents
A kind of boat form aeroengine thrust dynamometry rack Download PDFInfo
- Publication number
- CN110346145A CN110346145A CN201910642778.5A CN201910642778A CN110346145A CN 110346145 A CN110346145 A CN 110346145A CN 201910642778 A CN201910642778 A CN 201910642778A CN 110346145 A CN110346145 A CN 110346145A
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- frame
- slot
- auxiliary support
- dynamometry
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- 238000009434 installation Methods 0.000 claims description 7
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 238000005259 measurement Methods 0.000 abstract description 4
- 230000005484 gravity Effects 0.000 abstract description 2
- 125000002015 acyclic group Chemical group 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 239000000725 suspension Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
Classifications
-
- 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
-
- 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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The present invention provides a kind of boat form aeroengine thrust dynamometry racks, belong to propulsion test device technical field, including moving frame, quiet frame, load cell, calibrated force loader；Through slot is offered inside quiet frame, moving frame is rotatablely connected by one group of opposite side of shaft and through slot, fixes one group of symmetrical vertical plate in moving frame, vertical plate upper end is provided with one group of engine mounting base；The limit plate that one group of cross section is " L " type is symmetrically arranged on the corresponding quiet pallet face of another group of opposite side of through slot, the level board of limit plate is respectively positioned on above through slot, the level board bottom of side limit plate is provided with calibrated force loader, and the level board bottom of other side limit plate is provided with load cell；Fine tuning auxiliary support frame is additionally provided on quiet frame, fine tuning auxiliary support frame is slidably connected with quiet frame, finely tunes and is provided with position centering micro actuator on auxiliary support frame.Moving frame is limited in through slot by the dynamometry rack, and whole center of gravity is low, highly-safe, can preferably overcome thrust eccentric phenomenon, and measurement accuracy is high.
Description
Technical field
The invention belongs to propulsion test device technical fields, and in particular to a kind of boat form aeroengine thrust ergograph
Frame.
Background technique
Thrust is one of main performance index of engine, accurately determine motor power to the development of engine and
Assessment of performance is all significant.According to the difference of mounting means, currently used thrust rack has suspension type and brace type two
Class, using common flex part (spring leaf), either universal flexible element (hook switch) by moving frame suspension or is supported.Using flexibility
The advantages of part is the flexible deformation offer freedom of motion by material itself, but due to before engine intake and after jet pipe
Face can not all install load cell, and current almost all of rack is all off-axis formula support stand or off-axis formula suspension platform
Frame will unavoidably generate thrust eccentric phenomenon, i.e., there are angle offset between the axis of engine axis and load cell,
The thrust the accurate transmission of engine not can guarantee to thrust pickup, in turn result in certain measurement error.
With the development of high-performance bearing technology, the height of high revolving speed, high bearing capacity and low vibration noise, low friction moment
End bearing is widely used in fields such as high-speed rail, precision machine tools, and therefore, this external friction connection of bearing is used in aero-engine
Influence in this precise force-measuring equipment of rack to measurement accuracy will greatly reduce.
Therefore, the application proposes a kind of boat form aeroengine thrust dynamometry rack.
Summary of the invention
In order to overcome the shortcomings of the prior art described above, the present invention provides a kind of boat form aeroengine thrust dynamometry
Rack, including moving frame, quiet frame, load cell, calibrated force loader；
Through slot is offered inside the quiet frame, the moving frame is placed in the through slot, and the moving frame passes through shaft and institute
One group of opposite side rotation connection of through slot is stated, fixes one group of symmetrical vertical plate in the moving frame, the vertical plate upper end is provided with one group of hair
Motivation mounting base；
The limit that one group of cross section is " L " type is symmetrically arranged on the corresponding quiet pallet face of another group of opposite side of the through slot
Plate, the level board of the limit plate are respectively positioned on above the through slot, and the level board bottom of limit plate described in side is provided with described
The level board bottom of calibrated force loader, limit plate described in the other side is provided with the load cell；
Fine tuning auxiliary support frame is additionally provided on the quiet frame, the fine tuning auxiliary support frame is located at the load cell one
Side, the fine tuning auxiliary support frame are slidably connected with quiet frame, are provided with position centering micro actuator on the fine tuning auxiliary support frame,
Axial central axes by adjusting the micromatic setting on the position centering micro actuator, the symmetry axis and moving frame of realizing engine exist
It is parallel to each other in perpendicular.
Preferably, the load cell is connected in series by universal flexible element, load cell, universal flexible element.
Preferably, mounting blocks are provided on one group of opposite side of the through slot, bearing is installed in the mounting blocks, described turn
Axis passes through the moving frame and is fixedly connected with the moving frame, and the both ends of the shaft is connect with two bearing inner races respectively.
Preferably, guide rail is provided on the quiet frame, the fine tuning auxiliary support frame bottom is provided with matches with the guide rail
The pulley of conjunction, fine tuning auxiliary support frame guide rail described in the drive lower edge of the pulley are moved horizontally to adapt to difference and start
Machine mounting structure.
Preferably, the quantity of the position centering micro actuator is two, and two position centering micro actuators are respectively set
In the inside two sides of the fine tuning auxiliary support frame.
It preferably, further include controller, the load cell is electrically connected with the signal input part of the controller, the school
Quasi- power loader is electrically connected with the signal output end of the controller.
When boat form aeroengine thrust dynamometry rack provided by the invention is rotated around the axis using moving frame, 3 vertex are cut
To the equal-sized principle of power, thrust size is directly measured only with a sensor, and a calibrated force is only needed to add
Device is carried, vertical forces is converted by axial thrust and measures and calibrate.The dynamometry horse structure is simple, assembles opposite hold
Easily, strong applicability, moving frame are limited in through slot, and whole center of gravity is lower, highly-safe, and can preferably overcome thrust eccentric existing
As measurement accuracy is high.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the boat form aeroengine thrust dynamometry rack of the embodiment of the present invention 1；
Fig. 2 is that structure diagram is fixedly mounted in engine；
Fig. 3 is load cell structure chart；
Fig. 4 is fine tuning auxiliary support frame schematic diagram.
Description of symbols:
The quiet frame of 1-, 2- calibrated force loader, 3- moving frame, 4- engine fixed installation structure, 5- bearing, 6- load cell,
7- finely tunes auxiliary support frame, the position 8- centering micro actuator, 9- guide rail, 10- zero levelling device, 11- through slot, 12- shaft, 13-
Vertical plate, 14- limit plate, 15- mounting blocks, 16- controller, 17- clamp.
Specific embodiment
With reference to the accompanying drawing, further description of the specific embodiments of the present invention.Following embodiment is only used for more
Technical solution of the present invention is clearly demonstrated, and not intended to limit the protection scope of the present invention.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside", " axis
To ", " radial direction ", the orientation or positional relationship of the instructions such as " circumferential direction " be to be based on the orientation or positional relationship shown in the drawings, be only for
Convenient for description technical solution of the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have
Specific orientation is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.
In addition, term " first ", " second " etc. are used for description purposes only, it is not understood to indicate or imply relatively important
Property.In the description of the present invention, it should be noted that unless otherwise specific regulation or limit, term " connected ", " connection " are answered
It broadly understood, for example, it may be being fixedly connected, may be a detachable connection or integral type connects；It can be mechanical connect
It connects, is also possible to be electrically connected；It can be directly connected, be also possible to indirectly connected through an intermediary.For the general of this field
For logical technical staff, the specific meanings of the above terms in the present invention can be understood according to specific conditions.It is retouched in of the invention
In stating, unless otherwise indicated, the meaning of " plurality " is two or more, and this will not be detailed here.
Embodiment 1
It is specific as shown in Figures 1 to 4 including dynamic the present invention provides a kind of boat form aeroengine thrust dynamometry rack
Frame 3, quiet frame 1, load cell 6, calibrated force loader 2；
Through slot 11 is offered inside quiet frame 1, moving frame 3 is placed in through slot 11, and moving frame 3 passes through shaft 12 and the one of through slot 11
Group opposite side is rotatablely connected, and fixes one group of symmetrical vertical plate 13 in moving frame 3,13 upper end of vertical plate is provided with one group of engine mounting base 4；
The limit plate that one group of cross section is " L " type is symmetrically arranged on corresponding quiet 1 table top of frame of 11 another groups of opposite side of through slot
14, the level board of limit plate 14 is respectively positioned on 11 top of through slot, and the level board bottom of side limit plate 14 is provided with calibrated force load
Device 2, the level board bottom of other side limit plate 14 are provided with load cell 6, and in the present embodiment, load cell 6 is by universal flexible
Part, load cell, universal flexible element are connected in series.The load cell 6 that the present embodiment is used is commonly used on current aircraft industry
, the universal flexible element at both ends can play the role of decoupling power, guarantee there was only axial force, this model power in intermediate sensor
The tangential force of each point is equal on circumference, so to guarantee that measuring is tangential force.
Fine tuning auxiliary support frame 7 is additionally provided on quiet frame 1, engine is long, and there are two to three installations sections, engine
Mounting base 4 can with main installation save flange assembly, behind fine tuning auxiliary support frame 7 play the role of Auxiliary support, in order to guarantee
Power in engine mounting base 4 is horizontal shear force, and fine tuning auxiliary support frame 7 is required to fine tuning and guarantees axis horizontal, and and dynamic
The axis of frame 3 is parallel in vertical plane.Fine tuning auxiliary support frame 7 is located at 6 side of load cell, finely tune auxiliary support frame 7 and
Quiet frame 1 is slidably connected, specifically, being provided with guide rail 9 on quiet frame 1 in the present embodiment, fine tuning 7 bottom of auxiliary support frame is provided with
The pulley cooperated with guide rail 9, fine tuning auxiliary support frame 7 are moved horizontally along guide rail 9 under the drive of pulley to adapt to difference and start
Machine mounting structure.Position centering micro actuator 8, the position centering micro actuator 8 in the present embodiment are provided on fine tuning auxiliary support frame 7
Quantity be two, two position centering micro actuators 8 be separately positioned on fine tuning auxiliary support frame 7 inside two sides, by adjusting
Micromatic setting on position centering micro actuator 8, the axial central axes of the symmetry axis and moving frame 3 of realizing engine are in perpendicular
It is parallel to each other.
Specifically, being provided with mounting blocks 15 in the present embodiment on 11 1 groups of opposite side of through slot, being equipped with axis in mounting blocks 15
5 are held, shaft 12 passes through moving frame 3 and is fixedly connected with moving frame 3, and 12 both ends of shaft are connect with two 5 inner rings of bearing respectively.
In order to realize that position adjusts, in the present embodiment, further include be arranged in quiet 1 side of frame to acyclic homologically trioial leveling device 10, it is right
Acyclic homologically trioial leveling device 10 is connect with bearing 5, and control moving frame 3 is whole to keep horizontal.In the present embodiment is existing to acyclic homologically trioial leveling device 10
There is component, be substantially exactly to apply a kind of torque, application auxiliary torque that can be adaptive overcomes moving frame bottom plank not water
Flat problem.
It further include controller 16, the signal of load cell 6 and controller 16 in the present embodiment to realize accurate control
Input terminal electrical connection, calibrated force loader 2 are electrically connected with the signal output end of controller 16.
Fig. 2 is from longitudinal, namely vertical 4 schematic diagram of engine mounting base in terms of the face with engine axis, engine
Clamp 17 are provided in mounting base 4, similar to the disc brake of automobile, for fixing main installation section flange, the axis of right end can stretch
To adapt to different engine radius.
Implement measuring phases and implementation calibration phase when it is implemented, being divided into.
Measuring phases:
1, initial quiet frame installation locking is fixed, by making the horizontal zero deflection of 3 holding of moving frame to acyclic homologically trioial leveling device 10；
2, engine is installed on engine and structure 4 is fixedly mounted, engine tail portion is then passed through into two position centerings
Micro actuator 8 is adjusted, and holding position centering micro actuator 8 and the installation of engine pair save basic frictionless contact after adjustment；
3, comprehensive adjustment zero levelling device 10 and position centering micro actuator 8 keep engine axis and 3 axis of moving frame flat
Row and the horizontal zero deflection of moving frame 3, clamp 17 are locked engine；
4, load cell is zeroed, then starts engine and is tested.
After engine generates thrust, moving frame and engine are simultaneously around bearing rotary, so that moving frame produces load cell
Raw effect, measures motor power size, and be transmitted to computer by controller.
Calibration phase:
1, engine is removed, moving frame 3 playbacks, and keeps horizontal zero deflection, sensor zero；
2, computer and controller send loading command according to calibrated force load table and give calibrated force loader, load cell
A series of values are obtained, to assess rack dynamometry performance；
3, if you need to more Due Diligence test stand performance, then it can be calibrated for error, started using calibrated in situ method
Machine symmetry axis and moving frame perpendicular bisector point of intersection apply horizontal direction, the power of the thrust of energy simulated engine, to be calibrated.
The boat form aeroengine thrust rack that the application proposes, moving frame are big using each tangential direction power on uniform disc
Small equal principle cleverly converts horizontal direction thrust of the engine to main fulcrum to the pressure or drawing of vertical direction
Then power measures the size of the thrust with the load cell of stern vertical display, when being calibrated, also only need on the bow
The power for applying vertical direction is calibrated.
Embodiment described above is merely preferred embodiments of the present invention, and the scope of protection of the present invention is not limited to this,
Anyone skilled in the art within the technical scope of the present disclosure, the technical solution that can be become apparent to
Simple change or equivalence replacement, all belong to the scope of protection of the present invention.
Claims (6)
1. a kind of boat form aeroengine thrust dynamometry rack, which is characterized in that including moving frame (3), quiet frame (1), load cell
(6), calibrated force loader (2)；
It is offered through slot (11) inside the quiet frame (1), the moving frame (3) is placed in the through slot (11), the moving frame (3)
It is rotatablely connected by one group of opposite side of shaft (12) and the through slot (11), fixes one group of symmetrical vertical plate on the moving frame (3)
(13), vertical plate (13) upper end is provided with one group of engine mounting base (4)；
The limit that one group of cross section is " L " type is symmetrically arranged on corresponding quiet frame (1) table top of described another group of opposite side of through slot (11)
Position plate (14), the level board of the limit plate (14) are respectively positioned on above the through slot (11), the water of limit plate (14) described in side
Flat plate bottom is provided with the calibrated force loader (2), and the level board bottom of limit plate (14) described in the other side is provided with described
Load cell (6)；
Fine tuning auxiliary support frame (7) is additionally provided on the quiet frame (1), the fine tuning auxiliary support frame (7) is located at the dynamometry
Unit (6) side, the fine tuning auxiliary support frame (7) are slidably connected with the quiet frame (1), the fine tuning auxiliary support frame (7)
On be provided with position centering micro actuator (8), by adjusting the micromatic setting on the position centering micro actuator (8), realization is started
The axial central axes of the symmetry axis of machine and the moving frame (3) are parallel to each other in perpendicular.
2. boat form aeroengine thrust dynamometry rack according to claim 1, which is characterized in that the load cell
(6) it is sequentially connected in series by universal flexible element, load cell, universal flexible element.
3. boat form aeroengine thrust dynamometry rack according to claim 1, which is characterized in that the through slot (11) one
It is provided with mounting blocks (15) on group opposite side, is equipped with bearing (5) in the mounting blocks (15), the shaft (12) passes through described
Moving frame (3) is simultaneously fixedly connected with the moving frame (3), and shaft (12) both ends are connect with two bearing (5) inner rings respectively.
4. boat form aeroengine thrust dynamometry rack according to claim 1, which is characterized in that on the quiet frame (1)
It is provided with guide rail (9), described fine tuning auxiliary support frame (7) bottom is provided with the pulley with the guide rail (9) cooperation, the fine tuning
Auxiliary support frame (7) guide rail described in the drive lower edge of the pulley (9) is moved horizontally to adapt to different engine installation structures.
5. boat form aeroengine thrust dynamometry rack according to claim 1, which is characterized in that the position centering is micro-
The quantity for adjusting device (8) is two, and two position centering micro actuators (8) are separately positioned on the fine tuning auxiliary support frame (7)
Inside two sides.
6. boat form aeroengine thrust dynamometry rack according to claim 1, which is characterized in that further include controller
(16), the load cell (6) is electrically connected with the signal input part of the controller (16), the calibrated force loader (2) with
The signal output end of the controller (16) is electrically connected.
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 |
Applications Claiming Priority (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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| Publication Number | Publication Date |
|---|---|
| CN110346145A true CN110346145A (en) | 2019-10-18 |
| CN110346145B CN110346145B (en) | 2021-03-19 |
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| Application Number | Title | Priority Date | Filing Date |
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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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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114112155A (en) * | 2020-08-26 | 2022-03-01 | 中国科学院沈阳自动化研究所 | Horizontal two-degree-of-freedom force measuring rack with large bearing capacity |
| CN114199456A (en) * | 2021-11-18 | 2022-03-18 | 湖南崇德科技股份有限公司 | Large-scale thrust sliding bearing static self-balancing capability test bench |
| CN114216688A (en) * | 2021-11-12 | 2022-03-22 | 南京航空航天大学 | Thrust measuring device of miniature turbine engine |
| 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 |
| CN114923617A (en) * | 2022-07-21 | 2022-08-19 | 中国航发四川燃气涡轮研究院 | Engine lift force measuring device |
| CN115307924A (en) * | 2022-10-12 | 2022-11-08 | 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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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114112155A (en) * | 2020-08-26 | 2022-03-01 | 中国科学院沈阳自动化研究所 | Horizontal two-degree-of-freedom force measuring rack with large bearing capacity |
| CN114112155B (en) * | 2020-08-26 | 2022-10-14 | 中国科学院沈阳自动化研究所 | Horizontal two-degree-of-freedom force measuring rack with large bearing capacity |
| CN114216688A (en) * | 2021-11-12 | 2022-03-22 | 南京航空航天大学 | Thrust measuring device of miniature turbine engine |
| 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 |
| CN114199456A (en) * | 2021-11-18 | 2022-03-18 | 湖南崇德科技股份有限公司 | Large-scale thrust sliding bearing static self-balancing capability test bench |
| 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 |
| CN114923617A (en) * | 2022-07-21 | 2022-08-19 | 中国航发四川燃气涡轮研究院 | Engine lift force measuring device |
| CN115307924A (en) * | 2022-10-12 | 2022-11-08 | 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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| CN110346145B (en) | 2021-03-19 |
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Granted publication date: 20210319 |