CN109443782A - A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine - Google Patents
A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine Download PDFInfo
- Publication number
- CN109443782A CN109443782A CN201811098616.1A CN201811098616A CN109443782A CN 109443782 A CN109443782 A CN 109443782A CN 201811098616 A CN201811098616 A CN 201811098616A CN 109443782 A CN109443782 A CN 109443782A
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- China
- Prior art keywords
- air
- guide vane
- flow
- turbine guide
- cooled turbine
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Abstract
The present invention relates to a kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine, including flow control valve, air inlet rectifier, exhaust rectifier, air-flow test fixture and sonic nozzles.Air-flow passes through the air inlet rectifier for reducing turbulent flow under the control of flow control valve, into sonic nozzle, sonic nozzle downstream is provided with exhaust rectifier, exhaust rectifier is connected with one end of airflow channel, its other end is connected with the air-flow test fixture for fixing air-cooled turbine guide vane, air-flow test fixture includes two parts, a part is the plug-in unit for having the pedestal of toggle clamp and fixing on the base and be used to place air-cooled turbine guide vane, the side of plug-in unit is to be provided with and the air-cooled consistent slot of turbine guide vane tenon end surface shape, the other side is provided with stomata, slot is communicated with stomata；Air-flow flows to the inlet of air-cooled turbine guide vane bottom again from the stomata discharge on air-cooled turbine guide vane from the inside of air-flow test fixture.
Description
Technical field
The present invention is used to measure the device of the air-cooled turbine guide vane cooling air delivery of aero-engine.
Background technique
For fanjet, turbine inlet fuel gas temperature is improved for improving engine performance, is started as increased
The thrust ratio of machine thrust, the efficiency and engine that improve engine is all extremely important.However, turbine inlet combustion gas
Temperature is but limited by the temperature capacity of turbine material.Currently, the turbine inlet fuel gas temperature of advanced aviation turbofan engine is
Reached 1800K~2050K, have exceeded the limiting temperature that high temperature resistant blade material can be born, so must be using effective cold
But mode reduces the wall surface temperature of turbo blade.
Currently, what is be widely used both at home and abroad is open type cooling means, i.e., cooling air is drawn from compressor, after cooling turbine
It is discharged into turbine channel and combustion gas mixing.The program is fairly simple, easy to accomplish in structure, and it is largely cold not have to extra load
But gas；The disadvantage is that air of the carrying-off part by compressor compression, energy is consumed, and with pressure ratio and flying speed
Increase, cooling air self-temperature increases, and cooling effect is deteriorated.For the different types of cooling, basic cooling principle is
Cold air enters blade interior from blade lower part, is effectively cooled down by inner surface of the cooling duct to blade, then by leaf
The aperture outflow of on piece carries out cooling protection to blade outer surface.
The design of engine-cooling system will guarantee system at runtime, blade surface maximum temperature and temperature gradient with set
Maximum blade thermal stress as defined in the service life is counted to be adapted.It is higher that cooling working medium will lead to leaf temperature very little, to reduce hot portion
Part functional reliability shortens the thermal part service life, but cooling working medium is too many and can reduce engine performance.It must thus rationally design
Engine-cooling system so that cooling compressor sucking rate is minimum, while can improve turbine inlet fuel gas temperature, reach most
Big benefit.
Thus just need to measure the cooling air delivery that the parts such as engine blade pass through
For flow, there are two types of the measurements that testing stand can be used for flow at present.Glass tube flowmeter type, this testing stand is only
There have to be just accurate in the air-flow test of this low discharge in Turbomachinery and movable vane, and the turbine air cooling pipe in big flow is just not allowed
Really.Another kind is orifice plate type flowmeter, but the calculating of flow is very complicated.
Summary of the invention
The object of the present invention is to provide the devices that one kind can accurately measure the flow of turbine guide vane, can be called velocity of sound
Nozzle testing stand.Because it has the characteristics that stability, durability and simple flow rate calculation, it is more applicable come measuring flow.Technical side
Case is as follows:
A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine, including flow control valve, into
Gas rectifier, exhaust rectifier, air-flow test fixture and sonic nozzle, wherein
Air-flow under the control of flow control valve by being used to reduce the air inlet rectifier of turbulent flow, into sonic nozzle,
Sonic nozzle downstream is provided with exhaust rectifier, exhaust rectifier is connected with one end of airflow channel, other end connection
There is the air-flow test fixture for fixing air-cooled turbine guide vane, air-flow test fixture includes two parts, and a part is with hinged
It connects the pedestal of folder and fixes on the base and be used to place the plug-in unit of air-cooled turbine guide vane, the side of plug-in unit is to be provided with and air-cooled whirlpool
The consistent slot of guide vane tenon end surface shape is taken turns, the other side is provided with stomata, and slot is communicated with stomata；Air-flow is out of air-flow test fixture
Portion flows to the inlet of air-cooled turbine guide vane bottom again from the stomata discharge on air-cooled turbine guide vane；
The device is additionally provided with to the pressure gauge of sonic nozzle import stagnation pressure and to measure sonic nozzle outlet
The pressure gauge of stagnation pressure.
Preferably, blade or sieve are provided in air inlet rectifier.It is formed with gas chamber inside air-flow test fixture, to
The pressure gauge of measurement sonic nozzle outlet stagnation pressure is fixed on air-flow test fixture.
Technical effect of the invention is as follows:
1) working principle is clear, and flow rate calculation is simple.
2) gas mass flow measured by is solely dependent upon the fluid parameter of sonic nozzle upstream side, and and sonic nozzle
Interior pressure is linear, and measured signal is static pressure rather than pressure difference, therefore accuracy of measurement is high, and measurement range is wider.
3) structure is simple, and influence factor is few, therefore repeatability is good, and stability is fine.
Detailed description of the invention
Fig. 1 is the device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine of the invention, i.e. sonic nozzle
The schematic diagram of testing stand
Figure label explanation: 1-air supply opening；2-flow control valves；3-sonic nozzle entrance P1 pressure gauges；4-into
Gas rectifier；5-sonic nozzles；6-exhaust rectifiers；7-air-flow test fixtures；8-air-cooled turbine guide vanes；9-air-cooled whirlpools
Take turns guide vane entrance P3 pressure gauge.
Fig. 2 (a) and (b) are respectively air-cooled turbine guide vane and air-cooled turbine guide vane airflow channel schematic diagram
Figure label explanation: 10-surface pores；11,12-rear channel.
Specific embodiment
The present invention is used to measure the test-bed of air-cooled turbine guide vane flow, including flow control valve 2, air inlet rectifier
4, it is vented rectifier 6, air-flow test fixture 7, sonic nozzle 5, with reference to Fig. 1, in which:
1) flow control valve 2 provide the approach that control enters testing stand air mass flow.As flow control valve 2 is opened
The increase of degree, system pressure rise with the increase of air mass flow.
2) sonic nozzle entrance P1 pressure gauge 3 and air-cooled turbine guide vane entrance P3 pressure gauge 9.
3) air inlet rectifier 4, for reducing turbulent flow and increasing the precision of nozzle admission pressure.By a common metal tube
It realizes, rectifier can have blade or sieve.
4) it is vented rectifier 6, controllable and constant expansion is provided in sonic nozzle downstream.One without guide vane and sieve
Common metal pipe is sufficient
5) air-flow test fixture 7 is fixed and the air in testing stand is flowed for fixing air-cooled turbine guide vane 8
To the inlet of air-cooled 8 bottom of turbine guide vane.Air-flow test fixture 7 also provides pressure in the upstream of air-cooled 8 entrance of turbine guide vane
Power ventilating system maintains air-cooled 8 inlet pressure of turbine guide vane.Air-flow test fixture 7 and exhaust rectifier 6 pass through conventional hoses
(airflow channel) connection allows air-flow to flow to the air-cooled turbine guide vane 8 being fixed from exhaust rectifier 6.Air-flow test
Fixture 7 is broadly divided into two parts, and one is to have the pedestal of toggle clamp and for placing the plug-in unit of air-cooled turbine guide vane 8.It inserts
Part be one have through-hole reguline metal block, side be provided with the air-cooled 8 consistent slot of tenon end surface shape of turbine guide vane, separately
Side is provided with stomata, and slot is communicated with stomata.In this way, air-flow enters air-cooled whirlpool by hose, stomata, plug-in unit from exhaust rectifier 6
Take turns guide vane 8.
6) air quality or weight of system are flowed through in sonic nozzle 5, measurement.In such all systems, velocity of sound
The cross-sectional area of 5 throat of nozzle is necessarily less than the area of all air-outlet apertures in engine, i.e. sonic nozzle 5 must be metering
Or the component of control flow.The sky that increase is passed through into system with the increase of valve opening, valve downstream Laboratory air pressure
Gas weight.The pressure and speed of air in system rise to certain point, and in this point, sonic nozzle entrance P1 pressure gauge is measured
5 import stagnation pressure of sonic nozzle be that the sonic nozzle 5 that is measured by air-cooled turbine guide vane entrance P3 pressure gauge exports the 1.89 of stagnation pressure
Times.At this point, that is, when the pressure ratio at 5 both ends of sonic nozzle reaches 1.89, the air velocity of 5 throat of sonic nozzle
Reach a Mach number.Relationship between 5 inlet pressure of sonic nozzle and the air weight for flowing through sonic nozzle 5 keeps line
Property.Due to from sonic nozzle 5 to the distance of air-flow test fixture 7 is very short and air pipe line or hose are relatively large in diameter,
Almost without the linear loss of pressure, thus the gas chamber in air-flow test fixture 7 measure pressure is considered as starting
The pressure in 5 exit of machine components interior and sonic nozzle.
Sonic nozzle 5 is calibrated in systems, and wherein the air velocity of 5 throat of sonic nozzle is 1.0 Mach, and sound
Relationship between fast 5 inlet pressure of nozzle and the air weight for flowing through sonic nozzle 5 is linear.Linear relationship is designated as this
" K " factor of specific nozzle.Each nozzle has " K " factor of oneself.
7) air-cooled turbine guide vane 8, such as Fig. 2.Because the air-cooled work of turbine guide vane 8 is under high temperature environment, need to carry out it
It is air-cooled.Its basic cooling principle is cold air from channel 11,12 behind blade lower part into blade interior, passes through rear channel 11,12
The inner surface of blade is effectively cooled down, then blade outer surface is cooled down by the outflow of surface pores 10 on blade
Protection.
It is illustrated below with reference to embodiment.
1. the type selecting of sonic nozzle 5: different air-cooled turbine guide vanes 8 needs to select the sonic nozzle 5 of different K factors；It is first
The theoretical K factor for obtaining air-cooled turbine guide vane 8 is first calculated, then according to the suitable sonic nozzle 5 of theoretical k selecting predictors.
2. a pair flowmeter is calibrated, practical K factor is obtained.
3. assembling testing stand according to Fig. 1.
4. the leak detection of testing stand: leak detection is carried out to testing stand before experiment, to ensure that testing stand will not be sent out
Raw leakage, and testing stand is demarcated, to determine the precision of testing stand.The leak detection of testing stand includes to air-flow test clip
The leak detection of tool 7 and air-cooled turbine guide vane 8.
5. testing flow meter: it gives 5 entrance of sonic nozzle, one specified pressure (being measured by sonic nozzle entrance P1 pressure gauge 3),
Check engine components inlet pressure (being measured by air-cooled turbine guide vane entrance P3 pressure gauge 9) whether in limit section.
6. measuring sonic nozzle entrance P1 pressure under actual condition, cooling air delivery is calculated.
Claims (3)
1. a kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine, including flow control valve, air inlet
Rectifier, exhaust rectifier, air-flow test fixture and sonic nozzle.Wherein,
Air-flow passes through the air inlet rectifier for being used to reduce turbulent flow under the control of flow control valve, into sonic nozzle, in sound
Fast nozzle downstream is provided with exhaust rectifier, and exhaust rectifier is connected with one end of airflow channel, and other end connection is useful
Fix the air-flow test fixture of air-cooled turbine guide vane, air-flow test fixture includes two parts, a part is with toggle clamp
Pedestal and it is fixed on the base and be used to place the plug-in unit of air-cooled turbine guide vane, the side of plug-in unit is to be provided with to lead with air-cooled turbine
The consistent slot of leaf tenon end surface shape, the other side are provided with stomata, and slot is communicated with stomata；Inside stream of the air-flow from air-flow test fixture
It is discharged again from the stomata on air-cooled turbine guide vane to the inlet of air-cooled turbine guide vane bottom；
The device is additionally provided with to the pressure gauge of sonic nozzle import stagnation pressure and to measure sonic nozzle outlet stagnation pressure
Pressure gauge.
2. the apparatus according to claim 1, which is characterized in that be provided with blade or sieve in air inlet rectifier.
3. the apparatus according to claim 1, which is characterized in that gas chamber is formed with inside air-flow test fixture, to measure
The pressure gauge of sonic nozzle outlet stagnation pressure is fixed on air-flow test fixture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811098616.1A CN109443782A (en) | 2018-09-20 | 2018-09-20 | A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811098616.1A CN109443782A (en) | 2018-09-20 | 2018-09-20 | A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine |
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| CN109443782A true CN109443782A (en) | 2019-03-08 |
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| CN201811098616.1A Pending CN109443782A (en) | 2018-09-20 | 2018-09-20 | A kind of device of the air-cooled turbine guide vane cooling air stream measurement of aero-engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111735844A (en) * | 2020-07-14 | 2020-10-02 | 西安交通大学 | Experimental system and method for cooling test of front edge of turbine blade under rotation condition |
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| US20040221659A1 (en) * | 2003-05-09 | 2004-11-11 | Yoichi Sato | Moving blade support jig, moving blade support apparatus, and flow rate measuring apparatus |
| JP2006208309A (en) * | 2005-01-31 | 2006-08-10 | Central Res Inst Of Electric Power Ind | Flow rate distribution ratio measuring method in each internal flow channel of inspection object, and method and device for determining individual difference between inspection objects using it |
| CN101403654A (en) * | 2008-11-06 | 2009-04-08 | 西安交通大学 | Double-working medium refrigeration experiment system used for turbine blade of gas turbine |
| CN104348300A (en) * | 2014-11-07 | 2015-02-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Air blast cooling method for high-speed brushless direct-current generator |
| CN106643942A (en) * | 2016-12-21 | 2017-05-10 | 四川成发普睿玛机械工业制造有限责任公司 | Aero-engine turbine blade air mass flow testing device |
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2018
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| US20040221659A1 (en) * | 2003-05-09 | 2004-11-11 | Yoichi Sato | Moving blade support jig, moving blade support apparatus, and flow rate measuring apparatus |
| JP2006208309A (en) * | 2005-01-31 | 2006-08-10 | Central Res Inst Of Electric Power Ind | Flow rate distribution ratio measuring method in each internal flow channel of inspection object, and method and device for determining individual difference between inspection objects using it |
| CN101403654A (en) * | 2008-11-06 | 2009-04-08 | 西安交通大学 | Double-working medium refrigeration experiment system used for turbine blade of gas turbine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111735844A (en) * | 2020-07-14 | 2020-10-02 | 西安交通大学 | Experimental system and method for cooling test of front edge of turbine blade under rotation condition |
| CN111735844B (en) * | 2020-07-14 | 2021-07-13 | 西安交通大学 | Experimental system and method for cooling test of front edge of turbine blade under rotation condition |
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Application publication date: 20190308 |
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