CN108444723A - A kind of blade inlet edge eddy flow cooled flow local heat transfer system - Google Patents
A kind of blade inlet edge eddy flow cooled flow local heat transfer system Download PDFInfo
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- CN108444723A CN108444723A CN201810168006.8A CN201810168006A CN108444723A CN 108444723 A CN108444723 A CN 108444723A CN 201810168006 A CN201810168006 A CN 201810168006A CN 108444723 A CN108444723 A CN 108444723A
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- heat transfer
- transfer system
- inlet edge
- blade inlet
- local heat
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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
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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a kind of blade inlet edge eddy flow cooled flow local heat transfer systems, including air compressor, solenoid valve, tube of pressure-stabilizing, vortex-shedding meter, honeycomb screen, test section, electrical heating constant heat flow amount control system and measurement monitoring system；Test section includes test section inlet plenum, nozzle and spin chamber, and spin chamber upper surface is the slide cover board for opening up infrared optical window, and inner surface welds several thermocouples, and outer surface connects electrical heating constant heat flow amount control system；The present invention realizes the amplification to blade inlet edge channel, solves the experiment difficult point that minim channel is difficult to measure, and the theoretical foundation of model amplification is：For the flow performance in blade interior cooling duct, mainly by viscous force, the effect of pressure and inertia force.For such flowing, according to the principle of similitude, the similar decisive criterion of flow phenomenon is geometric similarity and reynolds analogue.It, can be according to geometric scale-up geometric dimension under the premise of reynolds analogue.
Description
Technical field
The present invention relates to a kind of blade inlet edge eddy flow cooled flow local heat transfer systems.
Background technology
Gas turbine is widely used in the fields such as land power generation, Ship Propeling, aviation power, and gas turbine blade is as combustion
The key position of gas-turbine needs to ensure the normal operation under severe hot conditions using the efficient type of cooling.For blade
Front edge area is also directly washed away by high-temperature fuel gas, needs highly efficient reliable cooling technology.Eddy flow cooling possesses height
Heat transfer intensity and more uniform temperature distribution can be applicable to front edge area and further increase cooling performance, and then promote import temperature
Degree increases gas turbine thermal power and efficiency.Therefore, blade inlet edge eddy flow cooled flow local heat transfer platform, realization pair are built
The measurement of heat transfer path heat exchange parameter under different aerodynamic parameters and geometric parameter has the development of turbine blade inside cooling
Significance.
The experiment of related eddy flow cooling is less at present, and design difficulty is mainly reflected in following three aspects：1. practical leaf
Piece leading edge portion internal cooling channel is very narrow, and for channel width in tens millimeters of orders of magnitude, processing and design are more difficult；2. due to
The limitation of leading edge structure, eddy flow cooling duct wall surface curvature is larger, thus has difficulties for the measurement of curved surface Temperature Distribution；3.
For the influence of systematic research difference aerodynamic parameter and geometric parameter, experiment condition is more, to which there are many workpieces processing, the period
It is long, it is of high cost.
Since there are above-mentioned difficulties for research, the more rational experiment porch of design is needed to carry out the cooling of pilot blade leading edge eddy flow
Heat-transfer character.
Invention content
It is an object of the invention to overcome the above-mentioned prior art, a kind of blade inlet edge eddy flow cooled flow is provided and is changed
Hot experimental system, for become in gas turbine turbine blade leading edge inner eddy flow cooling duct pneumatic and geometric parameter operating mode into
Row experiment obtains the transient state temperature field cloud charts in eddy flow Cooling Heat Transfer face, so analyze the part that heat-transfer area is calculated and
Overall heat exchange coefficient cloud charts.
In order to achieve the above objectives, the present invention is achieved by the following scheme：
A kind of blade inlet edge eddy flow cooled flow local heat transfer system, includes the air compressor machine being made of several air compressors
Group, the outlet of air compressor unit are sequentially connected tube of pressure-stabilizing, honeycomb screen and test section inlet plenum, on test section inlet plenum
Several nozzles are connected with, test section inlet plenum is connected by several nozzles with vortex chamber, and arrangement of nozzles is in vortex chamber side
Make cold air grazing incidence vortex chamber；Infrared optics eyeglass is arranged in the top of vortex chamber, and top is provided with thermal infrared imager, for saturating
Cross the Temperature Distribution cloud atlas in infrared optics eyeglass shooting vortex chamber.
The present invention, which further improves, to be：
The outlet of air-compressor set is connected by solenoid valve with tube of pressure-stabilizing；Tube of pressure-stabilizing passes through vortex-shedding meter and honeycomb screen
It is connected, vortex-shedding meter is used to measure the flow of import；The import of test section inlet plenum goes out to be provided with for measuring air inlet
Three hole probes of cold air stagnation pressure and static pressure have been used to measure the PT100 temperature sensors of import cold air static temperature.
Vortex chamber outer surface, which connects, is provided with the first heating film, forms horizontal heat flow boundary condition；Inner surface even application is used
In the sub-gloss varnish of enhancing reflectivity, and it is welded with the first thermocouple for realizing temperature calibration；Upper surface is provided with packaged type
Aluminum cover, infrared optics eyeglass are embedded in packaged type Aluminum cover, and thermal infrared imager and the first thermocouple are all connected to measurement
In monitoring system.
The cavity cross section top of vortex chamber is rectangle, and lower part is semicircle, and is made of stainless steel.
Packaged type Aluminum cover is realized by ladder connection method and is sealed.
First heating film outer surface package heat-barrier material and the second thermocouple, the second heating film of heat-barrier material appearance face paste and
Third thermocouple, the second heating film outer surface wrap up heat-barrier material；Cut-offfing for second heating film is controlled by electromagnetic relay
System, when the second thermocouple and third thermoelectric current signal then stop the second heating film less than relay disconnection setting value and add
Heat, on the contrary continue to heat；By controlling the identical setting for realizing adiabatic boundary condition of heat-barrier material both sides temperature, reduces first and add
Hotting mask radiation loss.
Vortex chamber and other structures glass fiber insulation interval, reduce radiation loss.
Test section inlet plenum and nozzle are made of organic glass.
Nozzle length-width ratio is 0.5~5.
Honeycomb screen and vortex chamber pass through flanged joint；Flowmeter becomes square flange using circle with honeycomb screen and connect.
Compared with prior art, the invention has the advantages that：
The present invention realizes the amplification to blade inlet edge channel, solves the experiment difficult point that minim channel is difficult to measure,
Model amplification theoretical foundation be：For the flow performance in blade interior cooling duct, mainly by viscous force, pressure and used
The effect of property power.For such flowing, according to the principle of similitude, the similar decisive criterion of flow phenomenon is geometric similarity and thunder
Promise is similar.It, can be according to geometric scale-up geometric dimension under the premise of reynolds analogue.
Further, the present invention realizes being precisely controlled for adiabatic boundary condition using adiabatic control device, subtracts to greatest extent
The loss of small heating surface heat flow；
Further, the present invention realizes instantaneous, the non-contact survey of heat exchanging face Temperature Distribution cloud atlas using thermal infrared imager
Amount solves the experiment difficult point of curved surface temperature measurement；
Further, the present invention, can quickly more in such a way that test section inlet plenum and nozzle are individually designed into component
It changes test section inlet plenum and nozzle realizes the measurement of different geometric parameter and aerodynamic parameter, enormously simplify the experiment process-cycle
And cost；
Further, present invention employs packaged type cover board, the measurement to large area heat-transfer surface Temperature Distribution is overcome,
And the shortcomings that infrared eyeglass of bulk is of high cost and cracky, enhance experiment serious forgiveness.
Description of the drawings
Fig. 1 is experimental system overall schematic of the present invention；
Fig. 2 is vortex chamber cross-sectional view；
Fig. 3 is packaged type Aluminum cover schematic diagram；
Fig. 4 is adiabatic control device schematic diagram.
Wherein, 1- air compressors；2- solenoid valves；The tube of pressure-stabilizing of honeycomb screen built in 3-；4- vortex-shedding meters；5- is whole
Flow grid；6- test section inlet plenums；7- nozzles；8- vortex chambers；9- measures monitoring system；10- barrier materials；11- packaged type aluminium
Cover board；12- infrared optics eyeglasses；The first thermocouples of 13-；The first heating films of 14-；15- thermal infrared imagers；Tri- hole probes of 16-；
17-PT100 temperature sensors；The second heating films of 18-；The second thermocouples of 19-；20- third thermocouples；21- heat-barrier materials；22-
Electromagnetic relay.
Specific implementation mode
The present invention is described in further detail below in conjunction with the accompanying drawings：
Referring to Fig. 1-4, blade inlet edge eddy flow cooled flow local heat transfer system of the present invention, including by several air compressors
The air-compressor set of 1 composition, the outlet of air compressor unit are sequentially connected tube of pressure-stabilizing 3, honeycomb screen 5 and test section inlet plenum 6,
Honeycomb screen 5 and vortex chamber 8 pass through flanged joint；Flowmeter 4 becomes square flange using circle with honeycomb screen 5 and connect.Test section inlet chamber
Several nozzles 7 are connected on room 6, test section inlet plenum 6 is connected by several nozzles 7 with vortex chamber 8, and nozzle 7 is arranged in
8 side of vortex chamber makes cold air grazing incidence vortex chamber 8；Test section inlet plenum 6 and nozzle 7 are made of organic glass.Nozzle 7
Length-width ratio is 0.5~5.The outlet of air-compressor set is connected by solenoid valve 2 with tube of pressure-stabilizing 3；Tube of pressure-stabilizing 3 passes through flux of vortex street
Meter 4 is connected with honeycomb screen 5, and vortex-shedding meter 4 is used to measure the flow of import；The import of test section inlet plenum 6 goes out to be provided with
The PT100 temperature that the three hole probes 16 for measuring air inlet cold air stagnation pressure and static pressure have been used to measure import cold air static temperature passes
Sensor 17.
The top setting infrared optics eyeglass 12 of vortex chamber 8, top is provided with thermal infrared imager 15, for penetrating infrared light
Learn the Temperature Distribution cloud atlas in the shooting vortex chamber 8 of eyeglass 12.8 outer surface of vortex chamber, which connects, is provided with the first heating film 14, is formed horizontal
Heat flow boundary condition；Inner surface even application is used to enhance the sub-gloss varnish of reflectivity, and is welded with for realizing temperature calibration
First thermocouple 13；Upper surface is provided with packaged type Aluminum cover 11, and infrared optics eyeglass 12 is embedded in packaged type Aluminum cover
In 11, thermal infrared imager 15 and the first thermocouple 13 are all connected to and measure in monitoring system 9.On the cavity cross section of vortex chamber 8
Portion is rectangle, and lower part is semicircle, and is made of stainless steel.Packaged type Aluminum cover 11 passes through ladder connection method
Realize sealing.Heat-barrier material and the second thermocouple 19 are wrapped up in first heating film, 14 outer surface, and heat-barrier material appearance face paste second adds
Heat-barrier material is wrapped up in hotting mask 18 and third thermocouple 20,18 outer surface of the second heating film.
The operation principle of the present invention：
Cut-offfing for second heating film 18 is controlled by electromagnetic relay 22, when the second thermocouple 19 and third thermocouple
20 thermocurrent signals disconnect setting value less than relay 22 and then stop the heating of the second heating film 18, otherwise continue to heat；Pass through
The identical setting for realizing adiabatic boundary condition of heat-barrier material both sides temperature is controlled, 14 radiation loss of the first heating film is reduced.Eddy flow
Chamber 8 and other structures glass fiber insulation interval, reduce radiation loss.
The above content is merely illustrative of the invention's technical idea, and protection scope of the present invention cannot be limited with this, every to press
According to technological thought proposed by the present invention, any change done on the basis of technical solution each falls within claims of the present invention
Protection domain within.
Claims (10)
1. a kind of blade inlet edge eddy flow cooled flow local heat transfer system, which is characterized in that including by several air compressors (1)
The outlet of the air-compressor set of composition, air compressor unit is sequentially connected tube of pressure-stabilizing (3), honeycomb screen (5) and test section inlet chamber
Room (6), is connected with several nozzles (7) on test section inlet plenum (6), test section inlet plenum (6) by several nozzles (7) with
Vortex chamber (8) is connected, and nozzle (7), which is arranged in vortex chamber (8) side, makes cold air grazing incidence vortex chamber (8)；Vortex chamber (8)
Infrared optics eyeglass (12) is arranged in top, and top is provided with thermal infrared imager (15), for being clapped through infrared optics eyeglass (12)
Take the photograph the Temperature Distribution cloud atlas in vortex chamber (8).
2. blade inlet edge eddy flow cooled flow local heat transfer system according to claim 1, which is characterized in that air-compressor set
Outlet be connected with tube of pressure-stabilizing (3) by solenoid valve (2)；Tube of pressure-stabilizing (3) passes through vortex-shedding meter (4) and honeycomb screen (5)
It is connected, vortex-shedding meter (4) is used to measure the flow of import；The import of test section inlet plenum (6) goes out to be provided with for measuring
Three hole probes (16) of air inlet cold air stagnation pressure and static pressure have been used to measure the PT100 temperature sensors of import cold air static temperature
(17)。
3. blade inlet edge eddy flow cooled flow local heat transfer system according to claim 1, which is characterized in that vortex chamber
(8) outer surface, which connects, is provided with the first heating film (14), forms horizontal heat flow boundary condition；Inner surface even application is anti-for enhancing
The sub-gloss varnish of rate is penetrated, and is welded with the first thermocouple (13) for realizing temperature calibration；Upper surface is provided with packaged type aluminium lid
Plate (11), infrared optics eyeglass (12) are embedded in packaged type Aluminum cover (11), thermal infrared imager (15) and the first thermocouple
(13) it is all connected to and measures in monitoring system (9).
4. blade inlet edge eddy flow cooled flow local heat transfer system according to claim 3, which is characterized in that vortex chamber
(8) cavity cross section top is rectangle, and lower part is semicircle, and is made of stainless steel.
5. blade inlet edge eddy flow cooled flow local heat transfer system according to claim 3, which is characterized in that packaged type
Aluminum cover (11) is realized by ladder connection method and is sealed.
6. blade inlet edge eddy flow cooled flow local heat transfer system according to claim 3, which is characterized in that the first heating
Wrap up heat-barrier material and the second thermocouple (19), heat-barrier material appearance the second heating film of face paste (18) and third in film (14) outer surface
Heat-barrier material is wrapped up in thermocouple (20), the second heating film (18) outer surface；Second heating film (18) is cut-off through electromagnetism relay
Device (22) is controlled, when the second thermocouple (19) and third thermocouple (20) thermocurrent signal are disconnected less than relay (22)
Setting value then stops the second heating film (18) heating, otherwise continues to heat；By controlling the identical realization of heat-barrier material both sides temperature
The setting of adiabatic boundary condition reduces the first heating film (14) radiation loss.
7. the blade inlet edge eddy flow cooled flow local heat transfer system according to claim 1-6 any one, feature exist
In radiation loss is reduced at vortex chamber (8) and other structures glass fiber insulation interval.
8. blade inlet edge eddy flow cooled flow local heat transfer system according to claim 1, which is characterized in that test section into
Gas chamber (6) and nozzle (7) are made of organic glass.
9. the blade inlet edge eddy flow cooled flow local heat transfer system according to claim 1 or 8, which is characterized in that nozzle
(7) length-width ratio is 0.5~5.
10. blade inlet edge eddy flow cooled flow local heat transfer system according to claim 1, which is characterized in that honeycomb screen
(5) and vortex chamber (8) passes through flanged joint；Flowmeter (4) becomes square flange using circle with honeycomb screen (5) and connect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810168006.8A CN108444723A (en) | 2018-02-28 | 2018-02-28 | A kind of blade inlet edge eddy flow cooled flow local heat transfer system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810168006.8A CN108444723A (en) | 2018-02-28 | 2018-02-28 | A kind of blade inlet edge eddy flow cooled flow local heat transfer system |
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| Publication Number | Publication Date |
|---|---|
| CN108444723A true CN108444723A (en) | 2018-08-24 |
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ID=63193040
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810168006.8A Pending CN108444723A (en) | 2018-02-28 | 2018-02-28 | A kind of blade inlet edge eddy flow cooled flow local heat transfer system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113006881A (en) * | 2021-04-09 | 2021-06-22 | 西安交通大学 | Blade leading edge double-cyclone impact cooling experiment test system and method |
| CN113758968A (en) * | 2021-09-30 | 2021-12-07 | 西安交通大学 | Experimental system and steady-state experimental method for measuring heat exchange coefficient of blade top of turbine movable blade |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5111046A (en) * | 1991-03-18 | 1992-05-05 | General Electric Company | Apparatus and method for inspecting cooling holes |
| CN101393071A (en) * | 2007-09-19 | 2009-03-25 | 中国科学院工程热物理研究所 | Visual observation and transient measurement method and apparatus for cooling process of turbine blade |
| CN102384928A (en) * | 2011-08-22 | 2012-03-21 | 东南大学 | Device and method for measuring thermal conductivity of high-conductivity thermal solid material |
| CN103968254A (en) * | 2014-04-29 | 2014-08-06 | 中国石油大学(北京) | Buried crude oil pipeline shutdown temperature drop experimental device |
| CN104267060A (en) * | 2014-09-25 | 2015-01-07 | 上海依阳实业有限公司 | Method for measuring heat conductivity of active heat-protection type calorimeter by virtue of quasi-steady-state method and correction method of active heat-protection type calorimeter |
| WO2015058045A1 (en) * | 2013-10-18 | 2015-04-23 | United Technologies Corporation | Method and assembly for inspecting engine component |
| CN106248724A (en) * | 2016-07-19 | 2016-12-21 | 西安交通大学 | A kind of turbine blade cooling duct heat transfer experiment system with ball-and-socket/ball male structure |
-
2018
- 2018-02-28 CN CN201810168006.8A patent/CN108444723A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5111046A (en) * | 1991-03-18 | 1992-05-05 | General Electric Company | Apparatus and method for inspecting cooling holes |
| CN101393071A (en) * | 2007-09-19 | 2009-03-25 | 中国科学院工程热物理研究所 | Visual observation and transient measurement method and apparatus for cooling process of turbine blade |
| CN102384928A (en) * | 2011-08-22 | 2012-03-21 | 东南大学 | Device and method for measuring thermal conductivity of high-conductivity thermal solid material |
| WO2015058045A1 (en) * | 2013-10-18 | 2015-04-23 | United Technologies Corporation | Method and assembly for inspecting engine component |
| CN103968254A (en) * | 2014-04-29 | 2014-08-06 | 中国石油大学(北京) | Buried crude oil pipeline shutdown temperature drop experimental device |
| CN104267060A (en) * | 2014-09-25 | 2015-01-07 | 上海依阳实业有限公司 | Method for measuring heat conductivity of active heat-protection type calorimeter by virtue of quasi-steady-state method and correction method of active heat-protection type calorimeter |
| CN106248724A (en) * | 2016-07-19 | 2016-12-21 | 西安交通大学 | A kind of turbine blade cooling duct heat transfer experiment system with ball-and-socket/ball male structure |
Non-Patent Citations (2)
| Title |
|---|
| 杜长河 等: "叶片前缘旋流蒸汽冷却流动和传热的数值研究", 《西安交通大学学报》 * |
| 迟重然: "燃气轮机透平冷却结构作用机制与设计优化方法", 《中国博士学位论文全文数据库 工程科技II辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113006881A (en) * | 2021-04-09 | 2021-06-22 | 西安交通大学 | Blade leading edge double-cyclone impact cooling experiment test system and method |
| CN113758968A (en) * | 2021-09-30 | 2021-12-07 | 西安交通大学 | Experimental system and steady-state experimental method for measuring heat exchange coefficient of blade top of turbine movable blade |
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Application publication date: 20180824 |