CN206056861U - A kind of thrust measurement calibrating installation of aircraft engine test stand frame - Google Patents
A kind of thrust measurement calibrating installation of aircraft engine test stand frame Download PDFInfo
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- CN206056861U CN206056861U CN201620918054.0U CN201620918054U CN206056861U CN 206056861 U CN206056861 U CN 206056861U CN 201620918054 U CN201620918054 U CN 201620918054U CN 206056861 U CN206056861 U CN 206056861U
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- hanger
- loader
- calibrating installation
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Abstract
The utility model discloses a kind of thrust measurement calibrating installation of aircraft engine test stand frame, aircraft engine test stand frame includes determining frame, moving frame and motor mounts, thrust measurement calibrating installation includes loading system and measuring and controlling equipment, loading system includes hanger and servo-loader, hanger hanging is connected to be determined on frame, servo-loader is arranged on hanger, the working chamber of servo-loader is connected with hydraulic oil source by servo valve, the piston rod of servo-loader is connected with motor mounts by standard force transducer, servo valve and standard force transducer are connected with measuring and controlling equipment respectively.This utility model is by installing thrust measurement calibrating installation additional to aircraft engine test stand frame, static load calibration and dynamic load calibration can be completed, true simulation trial condition of the aero-engine on stand can accurately obtain the parameters such as thrust, improve work efficiency, reduces cost.This utility model is particularly suited in the thrust measurement calibration of large-scale civil engine its Test Rig.
Description
Technical field
This utility model is related to measure calibration field, and in particular to a kind of thrust measurement school of aircraft engine test stand frame
Standard apparatus.
Background technology
Aero-engine will be through bench test repeatedly in the qualification test stage.The thrust of aero-engine is to identify which
Whether qualified important parameter, is the overall merit to electromotor overall work situation.To measure which in each working condition
Thrust, it is necessary to set up a set of accurate aircraft engine test stand frame.
In commissioning process, often because bench alignment is lack of standardization, cause the motor power parameter for obtaining inaccurate, shadow
Normal payment is rung, therefore the thrust measurement calibration of stand seems particularly important.A kind of outstanding test bed thrust measurement calibration side
Method can not only reflect true thrust well, moreover it is possible to reduce substantial amounts of Experimental Comparison work, effective control production cost, to boat
Empty electromotor subsequently installs to use very high reference value.How to make each aircraft engine test stand frame can be truly anti-
Mirror by the true thrust parameter of spreadsheet engine, be the focus of present calibration.
Current conventional aircraft engine test stand frame thrust measurement calibration steps mainly has intercrossed calibration and gauging calibration
Calibration.
Intercrossed calibration is the method that the states such as America and Europe adopted in recent years.Being will be an electromotor enterprising in multiple its Test Rigs
Row test run, verifies the certainty of measurement of each its Test Rig so as to calculate relative deviation.But if not introducing in test benchmark
Test bay data, intercrossed calibration will be unable to obtain accurate engine performance parameter, and be only capable of evaluating, revising the survey of each test bay
Accuracy of measurement.
Gauging calibration calibration is the method that Russia adopts.Core content is to choose a standard aero-engine to be tried
Car, so as to complete the calibration to its Test Rig.Due to reasons such as standard aviation engine stabilizations, the method can not be obtained accurately
Engine performance parameter, the property only with overall merit production degree of stability per year.
Therefore develop a kind of simple, the thrust measurement calibration steps for being capable of achieving aircraft engine test stand frame becomes industry
The difficult problem for solving is thirsted on boundary for a long time.
The content of the invention
To solve above-mentioned technical problem, goal of the invention of the present utility model is to provide a kind of aircraft engine test stand frame
Thrust measurement calibrating installation.It is simple and easy to do, the thrust measurement calibration of aircraft engine test stand frame can be realized, overcomes existing
The deficiency of technology, improve production efficiency.
For achieving the above object, this utility model provides following technical scheme：A kind of aircraft engine test stand
The thrust measurement calibrating installation of frame, the aircraft engine test stand frame include determining frame, moving frame and motor mounts, described
Determine frame to be connected with the roof of test cell, the moving frame is determined frame and is connected with described by spring leaf, the moving frame with it is described determine frame it
Between be additionally provided with displacement transducer, the motor mounts are connected with the moving frame, and the thrust measurement calibrating installation includes
Loading system and measuring and controlling equipment, the loading system include hanger and servo-loader, and it is described fixed that the hanger hanging is connected to
On frame, the servo-loader is arranged on the hanger, and the working chamber of the servo-loader passes through servo valve and hydraulic oil
Source connects, and the piston rod of the servo-loader is connected with the motor mounts by standard force transducer, the servo
Valve and the standard force transducer are connected with the measuring and controlling equipment respectively.
In above-mentioned technical proposal, the hanger is rigid hanger.
In above-mentioned technical proposal, the hanger includes the base plate being horizontally mounted and the connection base plate to the extension for determining frame
Plate, the servo-loader are horizontally arranged on the base plate.
In above-mentioned technical proposal, the hanger determines frame detachable connection with described.
In above-mentioned technical proposal, the hanger determines frame with the multiple relative installations in same level with described.
In above-mentioned technical proposal, the servo-loader and the hanger detachable connection.
In above-mentioned technical proposal, the servo-loader and the hanger are with being mounted opposite in the multiple of same level
Position
In above-mentioned technical proposal, the measuring and controlling equipment and the hydraulic oil source are placed in hoistable platform or the test run of test cell
Between terrace on.
As above-mentioned technical proposal is used, this utility model has following advantages compared with prior art：This utility model
By thrust measurement calibrating installation being installed additional to aircraft engine test stand frame, can complete static load calibration and dynamic load calibration, truly
Simulation trial condition of the aero-engine on stand, can accurately obtain the parameters such as thrust, improve work efficiency, reduces cost.
Present invention is particularly suitable in the thrust measurement calibration of large-scale civil engine its Test Rig.
Description of the drawings
Thrust measurement calibrating installations of the Fig. 1 for aircraft engine test stand frame disclosed in this utility model.
Wherein, 10, measuring and controlling equipment；21st, determine frame；22nd, moving frame；23rd, motor mounts；24th, spring；25th, displacement sensing
Device；26th, hanger；27th, servo-loader；28th, servo valve；29th, hydraulic oil source；30th, the roof of test cell；40th, proof force sensing
Device；50th, the hoistable platform of test cell；60th, the terrace of test cell.
Specific embodiment
With reference to the accompanying drawings and examples, specific embodiment of the present utility model is described in further detail.Below
Embodiment is used to illustrate this utility model, but is not limited to scope of the present utility model.
Referring to Fig. 1, as shown in legend therein, a kind of thrust measurement calibrating installation of aircraft engine test stand frame, boat
Empty engine running bench support includes determining frame 21, moving frame 22 and motor mounts 23, and the roof 30 for determining frame 21 with test cell connects
Connect, moving frame 22 is connected with frame 21 is determined by spring leaf 24, moving frame 22 and determine between frame 21, to be additionally provided with displacement transducer 25, start
Machine installing rack 23 is connected with moving frame 22, and thrust measurement calibrating installation includes measuring and controlling equipment 10 and loading system, above-mentioned loading system
Including hanger 26 and servo-loader 27, the hanging of hanger 26 is connected to be determined on frame 21, and servo-loader 27 is arranged on hanger 26,
The working chamber of servo-loader 27 is connected with hydraulic oil source 29 by servo valve 28, and the piston rod of servo-loader 27 passes through standard
Force transducer 40 is connected with the motor mounts 23, and servo valve 28 and standard force transducer 40 are connected with measuring and controlling equipment 10 respectively
Connect.
In a kind of embodiment, hanger 26 is rigid hanger, and servo-loader 27 is servo-cylinder.
In a kind of embodiment, hanger 26 includes the base plate 261 being horizontally mounted and connecting bottom board 261 to the link plate for determining frame 21
262, servo-loader 27 is horizontally arranged on base plate 261.
In a kind of embodiment, hanger 26 with determine 21 detachable connection of frame.
In a kind of embodiment, hanger 26 is at an angle mounted opposite position with the multiple of same level with frame 21 is determined
Put.
In a kind of embodiment, servo-loader 27 and 26 detachable connection of hanger.
In a kind of embodiment, servo-loader 27 is with hanger 26 with the multiple phases at an angle in same level
To installation site.
In a kind of embodiment, measuring and controlling equipment 10 and hydraulic oil source 29 are placed in the hoistable platform 50 of test cell or test cell
On terrace 60.
When the thrust measurement calibrating installation of aircraft engine test stand frame carries out calibration operation, measuring and controlling equipment 10 is to servo valve
28 send control signal, and control signal is converted to hydraulic pressure signal by servo valve 28, controls the piston rod action of servo-loader 27,
Loaded to motor mounts 23 by standard force transducer 40, be deformed spring leaf 24, cause to determine frame 21 and moving frame 22
Between there is relative displacement, the rigidity of displacement and spring leaf 24 is measured by displacement transducer 25, loading force F can be calculated1；
According to the difference of control signal, to complete, static loading, sinusoidal force loading, random force loading etc. are different to be loaded servo-loader 27
Waveform.Standard force transducer 40 is produced signal by loading force, by feeding back to measuring and controlling equipment 10, can obtain loading force F0；By F0And F1
Contrasted, that is, reached the purpose of the thrust calibration of aircraft engine test stand frame.
Change the direction of motion of 27 piston rod of servo-loader, you can change the action direction of loading force, boat can be simulated
Empty engine work and the operating mode of propulsive thrust work.
It is more than the description to this utility model embodiment, by the foregoing description of the disclosed embodiments, makes ability
Domain professional and technical personnel can realize or use this utility model.Professional skill to various modifications of these embodiments to this area
Will be apparent for art personnel, generic principles defined herein can without departing from it is of the present utility model spirit or
In the case of scope, realize in other embodiments.Therefore, this utility model is not intended to be limited to these realities shown in this article
Example is applied, and is to fit to the most wide scope consistent with principles disclosed herein and features of novelty.
Claims (8)
1. a kind of thrust measurement calibrating installation of aircraft engine test stand frame, the aircraft engine test stand frame include fixed
Frame, moving frame and motor mounts, described to determine frame and be connected with the roof of test cell, the moving frame is fixed with described by spring leaf
Frame connect, the moving frame and it is described determine between frame, to be additionally provided with displacement transducer, the motor mounts are connected with the moving frame
Connect, it is characterised in that the thrust measurement calibrating installation includes loading system and measuring and controlling equipment, the loading system includes hanger
And servo-loader, hanger hanging be connected to it is described determine on frame, the servo-loader is on the hanger, described
The working chamber of servo-loader is connected with hydraulic oil source by servo valve, and the piston rod of the servo-loader is passed by proof force
Sensor is connected with the motor mounts, and the servo valve and the standard force transducer are connected with the measuring and controlling equipment respectively
Connect.
2. thrust measurement calibrating installation according to claim 1, it is characterised in that the hanger is rigid hanger.
3. thrust measurement calibrating installation according to claim 1, it is characterised in that the hanger includes the bottom being horizontally mounted
, to the link plate for determining frame, the servo-loader is horizontally arranged on the base plate for plate and the connection base plate.
4. thrust measurement calibrating installation according to claim 1, it is characterised in that the hanger is with described to determine frame detachable
Formula connects.
5. thrust measurement calibrating installation according to claim 4, it is characterised in that the hanger with it is described determine frame with
Multiple relative installations of same level.
6. thrust measurement calibrating installation according to claim 1, it is characterised in that the servo-loader and the hanger
Detachable connection.
7. thrust measurement calibrating installation according to claim 6, it is characterised in that the servo-loader and the hanger
With the multiple relative installations in same level.
8. thrust measurement calibrating installation according to claim 1, it is characterised in that the measuring and controlling equipment and the hydraulic oil
Source is placed on the hoistable platform of test cell or the terrace of test cell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620918054.0U CN206056861U (en) | 2016-08-23 | 2016-08-23 | A kind of thrust measurement calibrating installation of aircraft engine test stand frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620918054.0U CN206056861U (en) | 2016-08-23 | 2016-08-23 | A kind of thrust measurement calibrating installation of aircraft engine test stand frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206056861U true CN206056861U (en) | 2017-03-29 |
Family
ID=58383712
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620918054.0U Expired - Fee Related CN206056861U (en) | 2016-08-23 | 2016-08-23 | A kind of thrust measurement calibrating installation of aircraft engine test stand frame |
Country Status (1)
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| CN (1) | CN206056861U (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107588955A (en) * | 2017-10-18 | 2018-01-16 | 中国航发成都发动机有限公司 | It is a kind of to push away experimental rig for the counter of engine THR REV life performance detection |
| CN107870053A (en) * | 2017-10-10 | 2018-04-03 | 西安航天动力试验技术研究所 | A kind of attitude control engine thrust-measuring device |
| CN109060239A (en) * | 2018-06-15 | 2018-12-21 | 西北工业大学 | A kind of pulse-knocking engine test bay thrust test dynamic calibrating method and device |
| CN109556868A (en) * | 2018-10-24 | 2019-04-02 | 中航工程集成设备有限公司 | A kind of load transfer device for high-precision test bay dynamometry |
| CN109807779A (en) * | 2019-01-28 | 2019-05-28 | 上海瑞吉机械传动技术有限公司 | The calibration installation instrument and shaft coupling of reed in elastic damping flat spring coupling |
| CN110346145A (en) * | 2019-07-16 | 2019-10-18 | 中国航发四川燃气涡轮研究院 | A kind of boat form aeroengine thrust dynamometry rack |
| CN110411751A (en) * | 2019-07-09 | 2019-11-05 | 中航工程集成设备有限公司 | A kind of thrust calibration system for engine running bench support |
| CN110702292A (en) * | 2019-11-28 | 2020-01-17 | 北京航天三发高科技有限公司 | Engine test bed air inlet thrust measuring device and using method |
| CN110716503A (en) * | 2019-10-10 | 2020-01-21 | 西安航天动力试验技术研究所 | High-precision thrust servo controller |
| CN113218552A (en) * | 2021-03-23 | 2021-08-06 | 中国人民解放军空军工程大学 | Auxiliary equipment and method for evaluating installation thrust of aero-engine |
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
-
2016
- 2016-08-23 CN CN201620918054.0U patent/CN206056861U/en not_active Expired - Fee Related
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107870053B (en) * | 2017-10-10 | 2020-02-21 | 西安航天动力试验技术研究所 | Attitude control engine thrust measuring device |
| CN107870053A (en) * | 2017-10-10 | 2018-04-03 | 西安航天动力试验技术研究所 | A kind of attitude control engine thrust-measuring device |
| CN107588955A (en) * | 2017-10-18 | 2018-01-16 | 中国航发成都发动机有限公司 | It is a kind of to push away experimental rig for the counter of engine THR REV life performance detection |
| CN109060239A (en) * | 2018-06-15 | 2018-12-21 | 西北工业大学 | A kind of pulse-knocking engine test bay thrust test dynamic calibrating method and device |
| CN109556868A (en) * | 2018-10-24 | 2019-04-02 | 中航工程集成设备有限公司 | A kind of load transfer device for high-precision test bay dynamometry |
| CN109807779A (en) * | 2019-01-28 | 2019-05-28 | 上海瑞吉机械传动技术有限公司 | The calibration installation instrument and shaft coupling of reed in elastic damping flat spring coupling |
| CN110411751A (en) * | 2019-07-09 | 2019-11-05 | 中航工程集成设备有限公司 | A kind of thrust calibration system for engine running bench support |
| CN110346145A (en) * | 2019-07-16 | 2019-10-18 | 中国航发四川燃气涡轮研究院 | A kind of boat form aeroengine thrust dynamometry rack |
| CN110346145B (en) * | 2019-07-16 | 2021-03-19 | 中国航发四川燃气涡轮研究院 | Boat type aero-engine thrust force measurement rack |
| CN110716503A (en) * | 2019-10-10 | 2020-01-21 | 西安航天动力试验技术研究所 | High-precision thrust servo controller |
| CN110702292A (en) * | 2019-11-28 | 2020-01-17 | 北京航天三发高科技有限公司 | Engine test bed air inlet thrust measuring device and using method |
| CN110702292B (en) * | 2019-11-28 | 2023-12-19 | 北京航天三发高科技有限公司 | Engine test bed air inlet thrust measuring device and using method |
| CN113218552A (en) * | 2021-03-23 | 2021-08-06 | 中国人民解放军空军工程大学 | Auxiliary equipment and method for evaluating installation thrust of aero-engine |
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
| CN115436065B (en) * | 2022-11-08 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170329 Termination date: 20170823 |
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| CF01 | Termination of patent right due to non-payment of annual fee |