CN109141897A - A kind of aero-engine nozzle flow integrated test system - Google Patents
A kind of aero-engine nozzle flow integrated test system Download PDFInfo
- Publication number
- CN109141897A CN109141897A CN201811004908.4A CN201811004908A CN109141897A CN 109141897 A CN109141897 A CN 109141897A CN 201811004908 A CN201811004908 A CN 201811004908A CN 109141897 A CN109141897 A CN 109141897A
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- nozzle
- aero
- sensor array
- bracket
- test system
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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
- G01M15/04—Testing internal-combustion engines
- G01M15/042—Testing internal-combustion engines by monitoring a single specific parameter not covered by groups G01M15/06 - G01M15/12
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
A kind of aero-engine nozzle flow integrated test system comprising: pedestal, electrical control cabinet, graphic control panel, band decelerator moment motor, lead screw, support base, sliding slot, sensor array bracket, sensor array fixed platform, data acquisition module, circular sensor array mounting plate, pressure sensor, nozzle characteristic testing platform, nozzle characteristic testing platform bracket, oil storage tank, water tank, booster pump, top nozzle fixing clamp, lower nozzle fixing clamp, laser sights receiving end, laser sights transmitting terminal, ultrasonic range finder sensor.The present invention is remarkably improved the detection quality and effect of aero-engine fuel nozzle, and dependence of the domestic air mail engine maintenance enterprise to import detection device, technological deficiency of the China Mi Zu in aero-engine fuel nozzle testing field is effectively reduced.
Description
Technical field
The invention belongs to Aeroengine Test Technology fields, comprehensive more particularly to a kind of aero-engine nozzle flow
Test macro.
Background technique
Fuel nozzle is the core key part of aero-engine, and function is to accelerate fuel-oil atmozation (or vaporization) mixed
It closes gas to be formed, guarantee to stablize burning and improves efficiency of combustion.Therefore, in the turnover job of aero-engine, fuel nozzle
It checks and tests and is most important.
Aeroengine combustor buring chamber interior operating condition is very severe, and fuel nozzle works long hours in the environment of high temperature and pressure
Under, often there is ablation, the failures such as blocking, flow transfinite.With modern Aviation company engine operation hourage and work
The increase at full speed of circulation causes the maintenance workload of fuel nozzle to be continuously increased, and not only needs largely to have specialized maintenance technology
Staff, and relative maintenance of equipment and test equipment made higher requirement and standard.
Domestic air mail engine maintenance enterprise is made a general survey of, still lacks a kind of aero-engine nozzle flow integration test system at present
System.If such test macro can be designed and be developed, it is remarkably improved the detection quality and effect of aero-engine fuel nozzle, is had
Effect reduces dependence of the domestic air mail engine maintenance enterprise to import detection device, and the China Mi Zu is in aero-engine fuel nozzle
The technological deficiency of testing field.
Summary of the invention
To solve the above-mentioned problems, the purpose of the present invention is to provide a kind of aero-engine nozzle flow integration test systems
System.It include: pedestal, electrical control cabinet, graphic control panel, band decelerator moment motor, lead screw, support base, sliding slot, sensor array
Be disbursed from the cost and expenses frame, sensor array fixed platform, data acquisition module, circular sensor array mounting plate, pressure sensor, nozzle survey
Test stand, nozzle characteristic testing platform bracket, oil storage tank, water tank, booster pump, top nozzle fixing clamp, lower nozzle fixing clamp；Wherein, pedestal
Level is fixed, and electrical control cabinet is fixed on the lower left corner of pedestal；Band decelerator moment motor, sliding slot and support base horizontal linear row
Column, and it is fixed on the left side central portion of pedestal；Band decelerator moment motor is coaxially connected with lead screw and by support seat supports, and lead screw drives
Direction is mobile along the chute for dynamic sensor array bracket, and sensor array bracket is fixed in sensor array fixed platform bottom
The heart；Band decelerator moment motor, sliding slot and the arrangement of support base vertical line, and it is fixed on the right side edge of pedestal；Band retarder
Torque motor is coaxially connected with lead screw and by support seat supports, and lead screw drives nozzle characteristic testing platform bracket, and direction is mobile along the chute, spray
Mouth testboard bracket is fixed on nozzle characteristic testing platform bottom centre.
Circular sensor array peace is installed on the sensor array fixed platform top installation data acquisition module, right side
Loading board and its center should be overlapped with the geometric center of mounting plane.
The pressure sensor annular array is mounted on circular sensor array mounting plate, and pressure sensor is adopted with data
Collect module electrical connection.
The lower nozzle fixing clamp is mounted among nozzle characteristic testing platform upper left-hand, is bolted with top nozzle fixing clamp
For fixing nozzle to be tested.
The oil storage tank and water tank is mounted on nozzle characteristic testing platform upper right, and booster pump is mounted on nozzle characteristic testing platform
Among portion, oil storage tank or water tank are connected with pressurization pump hose.
The graphic control panel is mounted on electrical control cabinet top.
The laser is sighted receiving end and is mounted in sensor array bracket right lateral surface horizontal median axis, and laser is sighted
Transmitting terminal is mounted in nozzle characteristic testing platform bracket left-hand face horizontal median axis, and laser sights receiving end and laser sights transmitting terminal
Mounting height is identical.
The ultrasonic range finder sensor is mounted in nozzle characteristic testing platform bracket left-hand face horizontal median axis, and is located at and is swashed
Below the quasi- transmitting terminal of illumination.
A kind of aero-engine nozzle flow integrated test system provided by the invention is remarkably improved aero-engine combustion
Dependence of the domestic air mail engine maintenance enterprise to import detection device is effectively reduced, more in the detection quality and effect of oil burner nozzle
Technological deficiency of the sufficient China in aero-engine fuel nozzle testing field.
Detailed description of the invention
Fig. 1 is a kind of aero-engine nozzle flow integrated test system isometric view 1.
Fig. 2 is a kind of aero-engine nozzle flow integrated test system isometric view 2.
Fig. 3 is a kind of aero-engine nozzle flow integrated test system sensor array fixed platform partial schematic diagram.
Fig. 4 is a kind of aero-engine nozzle flow integrated test system nozzle characteristic testing platform partial schematic diagram.
Specific embodiment
In the following with reference to the drawings and specific embodiments to a kind of aero-engine nozzle flow integration test provided by the invention
System is described in detail.
As shown in Figs 1-4, a kind of aero-engine nozzle flow integrated test system provided by the invention include: pedestal 1,
Electrical control cabinet 2, graphic control panel 3, band decelerator moment motor 4, band decelerator moment motor 13, lead screw 5, lead screw 15, branch
Support seat 6, support base 16, sliding slot 7, sliding slot 14, sensor array bracket 8, sensor array fixed platform 9, data acquisition module
10, circular sensor array mounting plate 11, pressure sensor 12, nozzle characteristic testing platform 21, nozzle characteristic testing platform bracket 23, oil storage tank
20, water tank 22, booster pump 19, top nozzle fixing clamp 17, lower nozzle fixing clamp 18；Wherein, pedestal 1 is horizontal fixed, electric-controlled
Cabinet 2 processed is fixed on the lower left corner of pedestal 1；Band decelerator moment motor 4, sliding slot 7 and the arrangement of 6 horizontal linear of support base, and it is fixed
In the left side central portion of pedestal 1；Band decelerator moment motor 4 is coaxially connected with lead screw 5 and is supported by support base 6, and the driving of lead screw 5 passes
7 directions are mobile along the chute for sensor array bracket 8, and sensor array bracket 8 is fixed in 9 bottom of sensor array fixed platform
The heart；Band decelerator moment motor 13, sliding slot 14 and the arrangement of 16 vertical line of support base, and it is fixed on the right side edge of pedestal 1；Band
Decelerator moment motor 13 is coaxially connected with lead screw 15 and is supported by support base 16, and lead screw 15 drives 23 edge of nozzle characteristic testing platform bracket
14 direction of sliding slot is mobile, and nozzle characteristic testing platform bracket 23 is fixed on 21 bottom centre of nozzle characteristic testing platform.
Circular sensor battle array is installed on the 9 top installation data acquisition module 10 of sensor array fixed platform, right side
Column mounting plate 11 and its center should be overlapped with the geometric center of mounting plane.
12 annular array of pressure sensor is mounted on circular sensor array mounting plate 11, pressure sensor 12 with
Data acquisition module 10 is electrically connected.
The lower nozzle fixing clamp 18 is mounted among 21 upper left-hand of nozzle characteristic testing platform, with 17 spiral shell of top nozzle fixing clamp
It tethers and connects for fixing nozzle to be tested.
The oil storage tank 20 and water tank 22 is mounted on 21 upper right of nozzle characteristic testing platform, and booster pump 19 is mounted on nozzle
Among 21 top of testboard, oil storage tank 20 or water tank 22 are connected with 19 hose of booster pump.
The graphic control panel 3 is mounted on 2 top of electrical control cabinet.
The laser is sighted receiving end 24 and is mounted in 8 right lateral surface horizontal median axis of sensor array bracket, laser
It sights transmitting terminal 25 to be mounted in 23 left-hand face horizontal median axis of nozzle characteristic testing platform bracket, laser sights receiving end 24 and laser
It is identical to sight 25 mounting height of transmitting terminal.
The ultrasonic range finder sensor 26 is mounted in 23 left-hand face horizontal median axis of nozzle characteristic testing platform bracket, and position
25 lower section of transmitting terminal is sighted in laser.
Now a kind of aero-engine nozzle flow integrated test system (hereinafter referred to as: this system) provided by the invention is made
It is described below with method:
Preparation: this system power on self test, such as alarm free can normally start to work.
Nozzle installation: fuel nozzle to be tested is consolidated using top nozzle fixing clamp (17) and lower nozzle fixing clamp (18)
It is fixed；Fuel nozzle tail portion and booster pump (19) outlet are connected using hose, guarantee the leakproofness of connector, it is such as without exception, it is quasi-
Standby work is completed.
Equipment debugging: operation graphic control panel (3) calibrating pressure sensor (12) array；Graphic control panel (3) are operated to drive
Dynamic nozzle characteristic testing platform (21) are mobile along the chute (14), when laser sights receiving end (24) and laser is sighted transmitting terminal (25) and is aligned
When, this system issues prompt, stops movement；Fuel nozzle manual testing is inquired, ultrasonic range finder sensor (26) data, behaviour are read
It is mobile along the chute (7) to make graphic control panel (3) driving sensor array fixed platform (9), when reaching manual testing regulation data
When, stop movement.
Testing process:
A. fuel medium flow rate test: the fuel oil of injection designated with numeral, oil storage tank (20), flowmeter in oil storage tank (20)
It is connected with booster pump (19) using hose.
B. aqueous medium flow rate test: water is injected in water tank (22), water tank (22), flowmeter and booster pump (19) make
It is connected with hose.
Recording nozzles spray configuration and flow simultaneously are completed to test.
It is emphasized that embodiment of the present invention be it is illustrative, without being restrictive, therefore the present invention is simultaneously
It is not limited to embodiment described in specific embodiment.Without departing from the scope of the invention, it can be carried out respectively
Kind is improved or replacement.Especially, as long as there is no the conflict in structure, the feature in each embodiment be can be combined with each other,
Or according to the technique and scheme of the present invention and the other embodiments that obtain of other this similar principles by those skilled in the art, together
Sample belongs to the scope of protection of the invention.
Claims (8)
1. a kind of aero-engine nozzle flow integrated test system, it is characterised in that: the aero-engine nozzle flow
Test macro includes: pedestal (1), electrical control cabinet (2), graphic control panel (3), band decelerator moment motor (4) (13), lead screw
(5) (15), support base (6) (16), sliding slot (7) (14), sensor array bracket (8), sensor array fixed platform (9), number
It is surveyed according to acquisition module (10), circular sensor array mounting plate (11), pressure sensor (12), nozzle characteristic testing platform (21), nozzle
Test stand bracket (23), oil storage tank (20), water tank (22), booster pump (19), top nozzle fixing clamp (17), lower nozzle fixing clamp
(18), laser sights receiving end (24), laser sights transmitting terminal (25), ultrasonic range finder sensor (26)；Wherein, pedestal (1) water
Flat to fix, electrical control cabinet (2) is fixed on the lower left corner of pedestal (1)；Band decelerator moment motor (4), sliding slot (7) and support base
(6) horizontal linear arranges, and is fixed on the left side central portion of pedestal (1)；Band decelerator moment motor (4) with lead screw (5) is coaxial connects
It connects and is supported by support base (6), lead screw (5) drives sensor array bracket (8), and (7) direction is mobile along the chute, sensor array
Bracket (8) is fixed on sensor array fixed platform (9) bottom centre；Band decelerator moment motor (13), sliding slot (14) and branch
The arrangement of seat (16) vertical line is supportted, and is fixed on the right side edge of pedestal (1)；Band decelerator moment motor (13) and lead screw (15)
Coaxially connected and supported by support base (16), lead screw (15) drives nozzle characteristic testing platform bracket (23), and (14) direction is mobile along the chute,
Nozzle characteristic testing platform bracket (23) is fixed on nozzle characteristic testing platform (21) bottom centre.
2. a kind of aero-engine nozzle flow integrated test system according to claim 1, it is characterised in that: described
Circular sensor array mounting plate is installed on sensor array fixed platform (9) top installation data acquisition module (10), right side
(11) and its center should be overlapped with the geometric center of mounting plane.
3. a kind of aero-engine nozzle flow integrated test system according to claim 1, it is characterised in that: described
Pressure sensor (12) annular array is mounted on circular sensor array mounting plate (11), and pressure sensor (12) and data acquire
Module (10) electrical connection.
4. a kind of aero-engine nozzle flow integrated test system according to claim 1, it is characterised in that: described
Lower nozzle fixing clamp (18) is mounted among nozzle characteristic testing platform (21) upper left-hand, is bolted use with top nozzle fixing clamp (17)
In fixation nozzle to be tested.
5. a kind of aero-engine nozzle flow integrated test system according to claim 1, it is characterised in that: described
Oil storage tank (20) and water tank (22) are mounted on nozzle characteristic testing platform (21) upper right, and booster pump (19) is mounted on nozzle characteristic testing platform
(21) among top, oil storage tank (20) or water tank (22) are connected with booster pump (19) hose.
6. a kind of aero-engine nozzle flow integrated test system according to claim 1, it is characterised in that: described
Graphic control panel (3) is mounted on electrical control cabinet (2) top.
7. a kind of aero-engine nozzle flow integrated test system according to claim 1, it is characterised in that: described
Laser is sighted receiving end (24) and is mounted in sensor array bracket (8) right lateral surface horizontal median axis, and laser sights transmitting terminal
(25) it is mounted in nozzle characteristic testing platform bracket (23) left-hand face horizontal median axis, laser sights receiving end (24) and laser is sighted
Transmitting terminal (25) mounting height is identical.
8. a kind of aero-engine nozzle flow integrated test system according to claim 1, it is characterised in that: described
Ultrasonic range finder sensor (26) is mounted in nozzle characteristic testing platform bracket (23) left-hand face horizontal median axis, and is sighted positioned at laser
Below transmitting terminal (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811004908.4A CN109141897A (en) | 2018-08-30 | 2018-08-30 | A kind of aero-engine nozzle flow integrated test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811004908.4A CN109141897A (en) | 2018-08-30 | 2018-08-30 | A kind of aero-engine nozzle flow integrated test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109141897A true CN109141897A (en) | 2019-01-04 |
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ID=64829492
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811004908.4A Pending CN109141897A (en) | 2018-08-30 | 2018-08-30 | A kind of aero-engine nozzle flow integrated test system |
Country Status (1)
| Country | Link |
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| CN (1) | CN109141897A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111896235A (en) * | 2020-07-31 | 2020-11-06 | 西安航天动力研究所 | Multifunctional integrated vertical fixed test bench |
| CN115876265A (en) * | 2023-02-16 | 2023-03-31 | 西安成立航空制造有限公司 | Aero-engine nozzle flow detection device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111896235A (en) * | 2020-07-31 | 2020-11-06 | 西安航天动力研究所 | Multifunctional integrated vertical fixed test bench |
| CN111896235B (en) * | 2020-07-31 | 2021-07-20 | 西安航天动力研究所 | Multifunctional integrated vertical fixed test bench |
| CN115876265A (en) * | 2023-02-16 | 2023-03-31 | 西安成立航空制造有限公司 | Aero-engine nozzle flow detection device |
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Application publication date: 20190104 |