CN106643942A - Aero-engine turbine blade air mass flow testing device - Google Patents
Aero-engine turbine blade air mass flow testing device Download PDFInfo
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- CN106643942A CN106643942A CN201611193859.4A CN201611193859A CN106643942A CN 106643942 A CN106643942 A CN 106643942A CN 201611193859 A CN201611193859 A CN 201611193859A CN 106643942 A CN106643942 A CN 106643942A
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- engine turbine
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
- G01F1/76—Devices for measuring mass flow of a fluid or a fluent solid material
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
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Abstract
The invention provides an aero-engine turbine blade air mass flow testing device. The testing device comprises an inlet valve, a pressure gauge, a filter, a self-operated pressure maintaining valve, a main path adjustment valve, a bypass fluid passage provided with a bypass adjustment valve, at least two multipled measuring by-paths, a temperature sensor, a pressure sensor, a blade clamp and a worktable. Each measuring by-path is provided with a stop valve and a flowmeter from an inlet end to an outlet end in sequence, and the flowmeter of each measuring by-path has different measuring ranges. The provided aero-engine turbine blade air mass flow testing device is used for making testing the conditions of film holes of turbine blades and internal fluid passage processing convenient, and provides reference for choosing installed blades.
Description
Technical field
The invention belongs to aero-engine non-standard field, especially a kind of aero engine turbine blades air mass flow test
Device.
Background technology
According to engine turbine blade apparatus manufacture claim, air mass flow test need to be carried out to surveyed blade, i.e., in measurement
By the MAF of blade under test pressure, by the air mass flow inspection for measuring turbine blade film cooling holes and runner
Blade air film hole situation and inner flow passage processing situation, to select installation blade reference is provided.This just needs to use air mass flow
Experimental rig.At present the air mass flow experimental rig of measurement aero engine turbine blades is a kind of fixture, the pipeline of its connection
Need to be fixed in a specific test bay, inconvenience is carried, take up room big, and measurement range is non-adjustable, certainty of measurement
Not high, operation is time-consuming.There is presently no a kind of special air mass flow experimental rig of aero engine turbine blades.
The content of the invention
Present invention aims to the deficiencies in the prior art, there is provided a kind of aero engine turbine blades air mass flow
Experimental rig, in order to check turbine blade film cooling holes situation and inner flow passage processing situation, and improves air mass flow test
Convenience and accuracy.
Aero engine turbine blades air mass flow experimental rig of the present invention, the experimental rig includes intake valve, pressure
Power table, filter, pressure maintaining valve of relying on oneself, main road regulating valve, be provided with bypass valve bypass stream, the survey of at least two parallel connections
Amount branch road and temperature sensor, pressure sensor, blade fixture and workbench, each measurement branch road from inlet end to outlet side according to
Flowmeter on one stop valve of secondary installation and a flowmeter, and each measurement branch road has different ranges；
The air inlet of the filter is connected by pipe fitting with the air supply opening of compressed air source, the intake valve, pressure gauge
On pipe fitting of the connection filter with compressed air source, and pressure gauge is located between filter and intake valve, the filtration
The gas outlet of device is connected by pipe fitting with the air inlet of pressure maintaining valve of relying on oneself, and the air inlet of the main road pressure regulator valve passes through pipe fitting and oneself
The gas outlet connection of power pressure maintaining valve, the gas outlet of main road pressure regulator valve is by a pipe fitting and multiple way union and each measurement branch road
Inlet end is connected, and respectively the outlet side of measurement branch road is pressed from both sides by multiple way union and a pipe fitting with the blade placed on the table
The air inlet connection of tool, the gas outlet of blade fixture communicates with air, and the temperature sensor, pressure sensor are arranged on connection
On the pipe fitting of multiple way union and blade fixture air inlet, its end of entering of the bypass stream connects with the gas outlet of main road pressure regulator valve
Logical, the outlet side for bypassing stream communicates with air.
Above-mentioned aero engine turbine blades air mass flow experimental rig, main road regulating valve is by main road main inlet control valve and main road
Fine adjustment valve is connected in parallel composition.
Above-mentioned aero engine turbine blades air mass flow experimental rig, the device is provided with switch board, the intake valve,
In pressure gauge, filter, pressure maintaining valve of relying on oneself, main road regulating valve, bypass valve, thermometer, pressure sensor, each measurement branch road
Stop valve and flowmeter and relevant connection pipeline be located in switch board, the survey measurements dial plate of each instrument and the control of each valve
In the window reserved on the control panel of button or the embedded switch board of knob, connect the pipe of filter and compressed air source air supply opening
Part, the via that one end that it is connected with compressed air source air supply opening is arranged through on switch board is located at outside switch board.
Above-mentioned aero engine turbine blades air mass flow experimental rig, the device is provided with working cabined, the blade folder
Tool and workbench are located at and are provided with the working cabined of cabinet door, and the pressure sensor is located at outside working cabined.
Above-mentioned aero engine turbine blades air mass flow experimental rig, the main road main inlet control valve, main road fine adjustment valve,
Bypass valve is manual needle valve, and the stop valve in each measurement branch road is magnetic valve, and the intake valve is ball valve.
Above-mentioned aero engine turbine blades air mass flow experimental rig, the flow is calculated as mass flowmenter.
It is of the present invention to carry out engine turbine leaf using above-mentioned aero engine turbine blades air mass flow experimental rig
The method of piece air-flow measurement, step is as follows：
(1) by engine turbine blade clamping on blade fixture, the survey of matching is selected according to blade reference range of flow
Amount branch road, opens the stop valve of corresponding measurement branch road, closes the stop valve of other measurement branch roads；
(2) intake valve is opened, while adjusting main road main inlet control valve, main road fine adjustment valve and bypass valve, makes pressure gauge
Numerical value is identical with measurement request numerical value, then reads the meter readings on measurement branch road, obtains the air flow value of the blade；
(3) main road regulating valve, main road fine adjustment valve and bypass valve are closed, removes the turbo blade for having measured, clamping
On the turbo blade that need to measure with the next one in the range of same reference flow in batch,
(4) main road main inlet control valve, main road fine adjustment valve and bypass valve are readjusted, the number that pressure sensor is measured is made
Value is identical with the numerical value of measurement request, reads the meter readings on measurement branch road, obtains the air flow value of the blade；
(5) repeat the above steps (3), the operation of step (4), until with the turbine in the range of same reference flow in batch
Leaf-Air flow measurement is finished.
Reference flow in said method is calculated by threedimensional model during Design Turbine Blade.
Compared with prior art, the invention has the advantages that:
1. the invention provides it is a kind of suitable for aero engine turbine blades air mass flow test device, in order to navigate
The carrying out of empty engine turbine Leaf-Air flow test.
2. engine turbine Leaf-Air device for testing flow of the present invention is due in parallel on same measurement main road
The flowmeter of multiple different ranges, forms multiple measurement branch roads, can meet the runner of different turbo blades and the air of air film hole
The needs of flow measurement convection current flowmeter measurement range, make different turbo blades runner and air film hole air mass flow in flow
In the optimum measurement precision range of meter, thus not only realize the runner that same experimental rig measures various different turbo blades
And the air mass flow of air film hole, and with high certainty of measurement.
3. engine turbine Leaf-Air device for testing flow of the present invention take up room it is little, be easy to carry, user
Just quick, operation is time-consuming short, and measurement range is adjustable.
Description of the drawings
Fig. 1 is the structure principle chart of aero engine turbine blades air mass flow experimental rig of the present invention；
Fig. 2 is the side front stereogram of aero engine turbine blades air mass flow experimental rig of the present invention；
Fig. 3 is the cut-away view of Fig. 2；
Fig. 4 is the side rear perspective view of aero engine turbine blades air mass flow experimental rig of the present invention；
Fig. 5 is the cut-away view of Fig. 4.
In figure, 1-intake valve, 2-pressure gauge, 3-filter, 4-pressure maintaining valve of relying on oneself, 5-1-main road main inlet control valve, 5-
2-main road fine adjustment valve, 6-bypass valve, 7-1-the first stop valve, 7-2-the second stop valve, 7-3-the 3rd ends
Valve, 8-1-first flowmeter, 8-2-second flowmeter, 8-3-the 3rd flowmeter, 9-temperature sensor, 10-pressure sensing
Device, 11-blade fixture, 12-workbench, 13-switch board, 13-1-control panel, 14-working cabined, 15-flexible pipe.
Specific embodiment
Aero engine turbine blades air mass flow experimental rig of the present invention is done below by specific embodiment
Further illustrate.
In the present embodiment, aero engine turbine blades air mass flow experimental rig structure as shown in Fig. 1～5, including entering
Air valve 1, pressure gauge 2, filter 3, pressure maintaining valve 4 of relying on oneself, main road regulating valve, the bypass stream for being provided with bypass valve 6, three
The measurement branch road and temperature sensor 9, pressure sensor 10, blade fixture 11 and workbench 12 of parallel connection；The measurement of three parallel connections
Branch road be first measurement branch road, second measurement branch road, the 3rd measurement branch road, first measurement branch road from inlet end to outlet side successively
First stop valve 7-1 is installed, first flowmeter 8-1, the second measurement branch road installs successively the second cut-off from inlet end to outlet side
Valve 7-2, second flowmeter 8-2, the 3rd measurement branch road installs successively the 3rd stop valve 7-3, the 3rd stream from inlet end to outlet side
Gauge 8-3；
The air inlet of the filter 3 is connected by pipe fitting with the air supply opening of compressed air source, the intake valve 1, pressure
Table 2 is arranged on the pipe fitting of connection filter and compressed air source, and pressure gauge 2 is located between filter and intake valve 1, described
The gas outlet of filter is connected by pipe fitting with the air inlet of pressure maintaining valve 4 of relying on oneself, and the air inlet of the main road pressure regulator valve is by pipe
Part is connected with the gas outlet of pressure maintaining valve 4 of relying on oneself, and the gas outlet of main road pressure regulator valve is by a pipe fitting and tee pipe coupling and each survey
The inlet end connection of amount branch road, the outlet side of each measurement branch road passes through tee pipe coupling and a pipe fitting and is placed on workbench 12
On blade fixture 11 air inlet connection, the gas outlet of blade fixture communicates with air, the temperature sensor 9, pressure biography
Sensor 10 is arranged on the pipe fitting of connecting tee pipe joint and blade fixture air inlet, the inlet end and main road of the bypass stream
The gas outlet connection of pressure regulator valve, the outlet side for bypassing stream communicates with air.
The device is provided with switch board 13, and the intake valve 1, pressure gauge 2, filter 3, pressure maintaining valve 4, main road of relying on oneself are adjusted
Stop valve and flowmeter and associated in valve, bypass valve 6, temperature sensor 9, pressure sensor 10, each measurement branch road
Adapter road is located in switch board 13, and the survey measurements dial plate of each instrument and the control button or knob of each valve are embedded in switch board
In the window reserved on control panel 13-1, connect the pipe fitting of filter and compressed air source air supply opening, itself and compressed air source
The via that the connected one end of air supply opening is arranged through on switch board is located at outside switch board.The switch board back side relative with control panel
Dismountable door panel structure is set to a side.The device is provided with working cabined 14, the blade fixture 11 and workbench
12 positioned at being provided with the working cabined 14 of cabinet door, and the pressure sensor 10 is located at outside working cabined.
The main road regulating valve is connected in parallel and is constituted by main road main inlet control valve 5-1 and main road fine adjustment valve 5-2, main road homophony
Section valve, main road fine adjustment valve, bypass valve are manual needle valve, and the stop valve in each measurement branch road is magnetic valve, it is described enter
Air valve is ball valve.First stop valve, the second stop valve, the 3rd stop valve are magnetic valve, first flowmeter, second flow
Meter, the 3rd flowmeter are mass flowmenter.The range of the first mass flowmenter be 0～28000Kg/h, the second mass flowmenter
Range be 0～23.7Kg/h, the range of the 3rd mass flowmenter is 0～86.4Kg/h.
Engine turbine Leaf-Air flow is carried out using above-mentioned aero engine turbine blades air mass flow experimental rig
The method of measurement, step is as follows：
(1) by engine turbine blade clamping on blade fixture, according to blade reference range of flow 5.4Kg/h～
23.7Kg/h, selects second to measure branch road, opens the magnetic valve of corresponding measurement branch road, closes the first, the 3rd electricity for measuring branch road
Magnet valve；
(2) intake valve is opened, while adjusting main road main inlet control valve, main road fine adjustment valve and bypass valve, makes pressure gauge
Numerical value is identical with measurement request numerical value, then reads the meter readings on measurement branch road, obtains the air flow value of the blade；
(3) main road regulating valve, main road fine adjustment valve and bypass valve are closed, removes the turbo blade for having measured, clamping
On the turbo blade that need to measure with the next one in the range of same reference flow in batch,
(4) main road main inlet control valve, main road fine adjustment valve and bypass valve are readjusted, the number that pressure sensor is measured is made
Value is identical with the numerical value of measurement request, reads the meter readings on measurement branch road, obtains the air flow value of the blade；
(5) repeat the above steps (3), the operation of step (4), until with the turbine in the range of same reference flow in batch
Leaf-Air flow measurement is finished.
Claims (10)
1. aero engine turbine blades air mass flow experimental rig, it is characterised in that the experimental rig includes intake valve (1), pressure
Power table (2), filter (3), pressure maintaining valve of relying on oneself (4), main road regulating valve, the bypass stream for being provided with bypass valve (6), at least
The measurement branch road and temperature sensor (9) of two parallel connections, pressure sensor (10), blade fixture (11) and workbench (12), respectively
Measurement branch road installs successively the flow on a stop valve and a flowmeter, and each measurement branch road from inlet end to outlet side
Meter has different ranges；
The air inlet of the filter (3) is connected by pipe fitting with the air supply opening of compressed air source, the intake valve (1), pressure
Table (2) on the pipe fitting of connection filter and compressed air source, and pressure gauge (2) positioned at filter and intake valve (1) it
Between, the gas outlet of the filter is connected by pipe fitting with the air inlet of pressure maintaining valve of relying on oneself (4), the air inlet of the main road pressure regulator valve
Mouth is connected by pipe fitting with the gas outlet of pressure maintaining valve of relying on oneself (4), and the gas outlet of main road pressure regulator valve is by a pipe fitting and many siphunculus
Joint is connected with the inlet end of each measurement branch road, and the outlet side of each measurement branch road passes through multiple way union and a pipe fitting and places
The air inlet connection of the blade fixture (11) on workbench (12), the gas outlet of blade fixture communicates with air, the temperature
Sensor (9), pressure sensor (10) installed in connection multiple way union and blade fixture air inlet pipe fitting on, the bypass
Its end of entering of stream connects with the gas outlet of main road pressure regulator valve, and the outlet side for bypassing stream communicates with air.
2. aero engine turbine blades air mass flow experimental rig according to claim 1, it is characterised in that main road is adjusted
Valve is connected in parallel and is constituted by main road main inlet control valve (5-1) and main road fine adjustment valve (5-2).
3. aero engine turbine blades air mass flow experimental rig according to claim 1 or claim 2, it is characterised in that the device
It is provided with switch board (13), the intake valve, pressure gauge, filter, pressure maintaining valve of relying on oneself, main road regulating valve, bypass valve, temperature
Stop valve and flowmeter and relevant connection pipeline in degree sensor, pressure sensor, each measurement branch road is located at switch board (13)
In, it is pre- on the control panel (13-1) of the survey measurements dial plate of each instrument and the embedded switch board of the control button or knob of each valve
In the window for staying, connect the pipe fitting of filter and compressed air source air supply opening, its one end being connected with compressed air source air supply opening
The via arranged through on switch board is located at outside switch board.
4. aero engine turbine blades air mass flow experimental rig according to claim 1 or claim 2, it is characterised in that the device
Working cabined (14) is provided with, the blade fixture and workbench are located at and are provided with the working cabined of cabinet door (14), and the pressure is passed
Sensor is located at outside working cabined.
5. aero engine turbine blades air mass flow experimental rig according to claim 3, it is characterised in that the device sets
Working cabined (14) is equipped with, the blade fixture and workbench are located at and are provided with the working cabined of cabinet door (14), the pressure sensing
Device is located at outside working cabined.
6. aero engine turbine blades air mass flow experimental rig according to claim 1 or claim 2, it is characterised in that the master
Road main inlet control valve, main road fine adjustment valve, bypass valve are manual needle valve, and the stop valve in each measurement branch road is magnetic valve,
The intake valve is ball valve.
7. aero engine turbine blades air mass flow experimental rig according to claim 3, it is characterised in that the main road
Main inlet control valve, main road fine adjustment valve, bypass valve are manual needle valve, and the stop valve in each measurement branch road is magnetic valve, institute
Intake valve is stated for ball valve.
8. aero engine turbine blades air mass flow experimental rig according to claim 1 or claim 2, it is characterised in that the stream
Amount is calculated as mass flowmenter.
9. aero engine turbine blades air mass flow experimental rig according to claim 3, it is characterised in that the flow
It is calculated as mass flowmenter.
10. entered using aero engine turbine blades air mass flow experimental rig described in any claim in claim 1～9
The method of row engine turbine Leaf-Air flow measurement, it is characterised in that step is as follows：
(1) by engine turbine blade clamping on blade fixture, the measurement of matching is selected according to blade reference range of flow
Road, opens the stop valve of corresponding measurement branch road, closes the stop valve of other measurement branch roads；
(2) intake valve is opened, while adjusting main road main inlet control valve, main road fine adjustment valve and bypass valve, makes pressure gauge numerical value
It is identical with measurement request numerical value, the meter readings on measurement branch road are then read, obtain the air flow value of the blade；
(3) main road regulating valve, main road fine adjustment valve and bypass valve are closed, removes the turbo blade for having measured, it is same on clamping
The turbo blade that the next one in batch in the range of same reference flow need to be measured,
(4) main road main inlet control valve, main road fine adjustment valve and bypass valve are readjusted, make numerical value that pressure sensor measures with
The numerical value of measurement request is identical, reads the meter readings on measurement branch road, obtains the air flow value of the blade；
(5) repeat the above steps (3), the operation of step (4), until with the turbo blade in the range of same reference flow in batch
Air-flow measurement is finished.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611193859.4A CN106643942A (en) | 2016-12-21 | 2016-12-21 | Aero-engine turbine blade air mass flow testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611193859.4A CN106643942A (en) | 2016-12-21 | 2016-12-21 | Aero-engine turbine blade air mass flow testing device |
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| Publication Number | Publication Date |
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| CN106643942A true CN106643942A (en) | 2017-05-10 |
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|---|---|---|---|
| CN201611193859.4A Pending CN106643942A (en) | 2016-12-21 | 2016-12-21 | Aero-engine turbine blade air mass flow testing device |
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|---|---|---|---|---|
| CN107560837A (en) * | 2017-05-24 | 2018-01-09 | 天津成立航空技术有限公司 | A kind of fuel nozzle cyclone air mass flow testing stand and its test method |
| CN107588819A (en) * | 2017-09-28 | 2018-01-16 | 中国航发动力股份有限公司 | A kind of micro-porous electrode flow testing device and method |
| CN108061624A (en) * | 2017-11-21 | 2018-05-22 | 四川成发普睿玛机械工业制造有限责任公司 | The air mass flow of aerial motor spare part and seal tightness test platform and test method |
| CN108121370A (en) * | 2017-12-23 | 2018-06-05 | 东北大学 | A kind of investigating method and TT＆C system of vacuum environment gas flow |
| CN108982111A (en) * | 2018-08-23 | 2018-12-11 | 天津大学 | Engine turbine blade cooling air flow meter and method based on sonic nozzle |
| CN109443782A (en) * | 2018-09-20 | 2019-03-08 | 天津大学 | A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine |
| CN110887665A (en) * | 2019-11-05 | 2020-03-17 | 芜湖市极星航空科技有限公司 | Air flow test device for compact aero-engine case |
| CN110895202A (en) * | 2018-09-12 | 2020-03-20 | 北京振兴计量测试研究所 | Test device for researching influence of environmental factors on flow measurement |
| CN111998227A (en) * | 2020-08-20 | 2020-11-27 | 湖北三江航天红峰控制有限公司 | Air supply system and air supply method for attitude and orbit control engine cold debugging |
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| CN112345219A (en) * | 2020-10-29 | 2021-02-09 | 中国航发南方工业有限公司 | Blade air flow test system |
| CN112945534A (en) * | 2021-02-07 | 2021-06-11 | 浙江燃创透平机械股份有限公司 | Gas turbine component air flow test bed and test method |
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| CN107560837A (en) * | 2017-05-24 | 2018-01-09 | 天津成立航空技术有限公司 | A kind of fuel nozzle cyclone air mass flow testing stand and its test method |
| CN107560837B (en) * | 2017-05-24 | 2024-01-26 | 成立航空股份有限公司 | Swirler air flow test bed for fuel nozzle and test method thereof |
| CN107588819A (en) * | 2017-09-28 | 2018-01-16 | 中国航发动力股份有限公司 | A kind of micro-porous electrode flow testing device and method |
| CN108061624A (en) * | 2017-11-21 | 2018-05-22 | 四川成发普睿玛机械工业制造有限责任公司 | The air mass flow of aerial motor spare part and seal tightness test platform and test method |
| CN108061624B (en) * | 2017-11-21 | 2019-08-02 | 四川成发普睿玛机械工业制造有限责任公司 | The air mass flow and seal tightness test platform and test method of aerial motor spare part |
| CN108121370A (en) * | 2017-12-23 | 2018-06-05 | 东北大学 | A kind of investigating method and TT＆C system of vacuum environment gas flow |
| CN108982111A (en) * | 2018-08-23 | 2018-12-11 | 天津大学 | Engine turbine blade cooling air flow meter and method based on sonic nozzle |
| CN110895202A (en) * | 2018-09-12 | 2020-03-20 | 北京振兴计量测试研究所 | Test device for researching influence of environmental factors on flow measurement |
| CN109443782A (en) * | 2018-09-20 | 2019-03-08 | 天津大学 | A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine |
| CN110887665A (en) * | 2019-11-05 | 2020-03-17 | 芜湖市极星航空科技有限公司 | Air flow test device for compact aero-engine case |
| CN111998227A (en) * | 2020-08-20 | 2020-11-27 | 湖北三江航天红峰控制有限公司 | Air supply system and air supply method for attitude and orbit control engine cold debugging |
| CN112161662A (en) * | 2020-09-29 | 2021-01-01 | 辽宁工程技术大学 | Vortex guide and combustion engine blade water flow testing device and method |
| CN112345219A (en) * | 2020-10-29 | 2021-02-09 | 中国航发南方工业有限公司 | Blade air flow test system |
| CN112945534A (en) * | 2021-02-07 | 2021-06-11 | 浙江燃创透平机械股份有限公司 | Gas turbine component air flow test bed and test method |
| CN112945534B (en) * | 2021-02-07 | 2022-10-11 | 浙江燃创透平机械股份有限公司 | Gas turbine component air flow test bed and test method |
| CN113074949A (en) * | 2021-04-02 | 2021-07-06 | 南京赛恩通航科技有限公司 | System and method for detecting parameters of miniature aviation turbojet engine |
| CN113252291A (en) * | 2021-07-15 | 2021-08-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel air supply system and method |
| CN113358319A (en) * | 2021-08-09 | 2021-09-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Air inlet simulation system and method |
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Application publication date: 20170510 |