CN202928778U - Orifice plate structure for studying gas turbine blade gas film cooling flow field and temperature field - Google Patents
Orifice plate structure for studying gas turbine blade gas film cooling flow field and temperature field Download PDFInfo
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- CN202928778U CN202928778U CN 201220634512 CN201220634512U CN202928778U CN 202928778 U CN202928778 U CN 202928778U CN 201220634512 CN201220634512 CN 201220634512 CN 201220634512 U CN201220634512 U CN 201220634512U CN 202928778 U CN202928778 U CN 202928778U
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- film cooling
- gas turbine
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- flow field
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Abstract
Disclosed is an orifice plate structure for studying gas turbine blade gas film cooling flow field and temperature field. The orifice plate structure comprises an experiment member (2) and a testing member (8), wherein the experiment member (2) is provided with a channel section protruding member (12); the testing member (8) is provided with a channel section recessed member (13); the experiment member (2) and the testing member (8) are buckled together via the channel section protruding member (12) and the channel section recessed member (13); the experiment member (2) is provided with a gas film cooling aperture (1) and an organic glass tube (3); the lower side of the gas film cooling aperture (1) is connected with the organic glass tube (3) having the caliber equal to that of the gas film cooling aperture (1); the testing member (8) comprises black paint (4), a stainless steel slice (5), an electric heating plate (6), and an organic glass sheet (7); and the black paint (4) is applied upon the stainless steel slice (5).
Description
Technical field
The utility model relates to a kind of gas turbine blades air film Study on Cooling device, particularly a kind of AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field.
Background technology
There is the contradiction that inlet temperature improves and the blade heat resistance is limited in gas turbine: the burning capacity of hydrocarbon fuel can make turbine-inlet temperature reach 2230 ℃, exceeds the permissible value of manufactured materials, and for this reason, this temperature value generally is controlled in below 1900 ℃.The safety of blade etc. ensures with cooling technology, the cooling one that is of air film.Air film is cooling to be improved gas turbine proficiency and serviceable life.This is because according to thermodynamic principles, improving turbine import Temperature of Working will make the equipment work done increase, the high temperature tolerance capabilities limits of material taking full advantage of of fuel combustion energy, implement that air film is cooling will isolate hot working fluid and passage component, can guarantee device security in acquisition gas turbine inlet high temperature.Film Cooling mainly depends on position, shape and the distribution of the Cooling Holes on the pressure ratio of cooling working medium and high-temperature fuel gas, warm ratio and airfilm cooling blade.And in typical gas turbine blades; pressure ratio is relative with the Wen Bi span fixing; generally temperature is than lower under given pressure ratio in addition, and air film cooling protection effect is better, however to constant temperature than the higher air film cooling protection of lower pressure ratio effect better (occur that jet be lifted away from situation except).Therefore in order to design better blade air film refrigerating mode, should more pay attention to studying position, distribution, angle and the shape of air film hole to the impact of Film Cooling.
At present the research of gas turbine blades air film cooling aspect increased gradually, but due to condition restriction, the mode of more employing numerical simulation is investigated.Aspect experimental study, consider that real blade processing has difficulties, and flat plate model can be used for the impact of relatively easy research parameters, its investment simultaneously is not high yet, and just can apply to reality through the verification test result after revising slightly.So, open film cooling holes and namely utilize AND DEWATERING FOR ORIFICE STRUCTURE on flat board, carry out the experimental study in air film coolant flow field and temperature field, be important means and the developing direction of following optimal design.
The research of existing air film cooling technology, perhaps more exploitation or the more exploitation that lays particular emphasis on whole air film refrigeration experiment system that lays particular emphasis on the cooling pass of New Gas Film, less for Gas Film-cooled Flat Plate expansion particular study.Gas Film-cooled Flat Plate is the important place of heat and momentum-exchange, and on flat board, the layout of Cooling Holes directly affects Film Cooling, and on flat board, the test of cooling effect is the foundation of passing judgment on air film cooling technology.When the layout research of carrying out Cooling Holes, must change a plurality of orifice plates, how orifice plate is connected with part of detecting easily is one of problem of needs consideration.In addition when passing judgment on air film cooling technology, mostly be a definition dimensionless group---the cooling availability of air film (or being called gas film cooling efficiency), and heat transfer coefficient can represent dull and stereotyped with extraneous heat transfer capacity more accurately, how to measure accurately dull and stereotyped heat transfer coefficient and be two of the problem that needs consideration.
The utility model content
In order to overcome the above-mentioned technical matters that exists in prior art, the utility model provides a kind of AND DEWATERING FOR ORIFICE STRUCTURE, and it can provide position of opening and part of detecting method of attachment easily, and the structure of measuring dull and stereotyped heat transfer coefficient.The utility model is applicable to the optimal design of gas turbine blades film cooling holes layout.
For achieving the above object, the technical scheme that the utility model is taked is: a kind of AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field, comprise experimental piece and test block, the draw-in groove male member is set on described experimental piece, recessed of draw-in groove is set on described test block, and described experimental piece and test block are fastened togather by described draw-in groove male member and recessed of draw-in groove.
Further, be provided with film cooling holes on described experimental piece, the described film cooling holes below connection plexi-glass tubular identical with its caliber.
Further, that described test block comprises is pitch-dark, stainless steel thin slice, electric heating sheets and organic glass sheet, described pitch-dark being coated on described stainless steel thin slice, and described stainless steel thin slice and electric heating sheets are bolted on described poly (methyl methacrylate) plate with sedimentation.
Further, at the upper surface of described test block, thermopair is set evenly, described thermopair sees through described poly (methyl methacrylate) plate, is connected to data collecting instrument.
Further, comprise a plurality of experimental pieces with quantity and structure of different film cooling holes.
The beneficial effect that the utlity model has is: the utility model is divided into experimental piece and test block two parts with the film cooling holes plate structure.By notch is set, realized the easy disassembly of experimental piece and test block on poly (methyl methacrylate) plate.Test block is comprised of four layer materials, also can record dull and stereotyped heat transfer coefficient when recording the cooling availability of air film.Like this, then be used in conjunction with thermal infrared imager and flow-field visualized instrument, just can study fluid mechanics behavior complicated in film cooling holes mouth jet and main flow blending process.In addition, can this Gas Film-cooled Flat Plate structure be the basis, carry out the research of gas turbine curved surface bucket.
Adopt the optimal design of carrying out the film cooling holes layout that the utility model can be convenient and simple.In addition, the utility model is simple in structure, and cost is lower, is easy to promote.
Description of drawings
Fig. 1 is the structural representation of the utility model device film cooling holes plate.
Fig. 2 is the A-A sectional view in Fig. 1.
Fig. 3 is the notch schematic diagram of the utility model device experimental piece and test block.
Fig. 4 is the film cooling system diagram
each Reference numeral implication in figure: 1, film cooling holes, 2, experimental piece, 3, plexi-glass tubular, 4, pitch-dark, 5, the stainless steel thin slice, 6, electric heating sheets, 7, poly (methyl methacrylate) plate, 8, test block, 9, the sedimentation bolt, 10, thermopair, 11, data collecting instrument, 12, the draw-in groove male member, 13, recessed of draw-in groove, 14, the low-speed DC wind-tunnel, 15, hot-wire anemometer, 16, collection chamber, 17, aerosol producer 18, vortex shedding flow meter, 19, threshold switch, 20, bucket, 21, water pump, 22, constant temperature enclosure, 23, high-pressure air source, 24, industrial computer, 25, halogen lamp, 26, high-speed camera, 27, thermal infrared imager, 28, tripod.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing.
as Fig. 1, Fig. 2, shown in Figure 3: the AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field of the present utility model, comprise film cooling holes 1, experimental piece 2, plexi-glass tubular 3, pitch-dark 4, stainless steel thin slice 5, electric heating sheets 6, poly (methyl methacrylate) plate 7, test block 8, the sedimentation bolt, thermopair 10, data collecting instrument 11, draw-in groove male member 12, recessed 13 of draw-in groove, have film cooling holes 1 on experimental piece 2, film cooling holes 1 below connects the plexi-glass tubular 3 identical with its caliber, plexi-glass tubular 3 is as the entrance of cryogenic gas, the film cooling holes 1 of experimental piece 2 is as the outlet of cryogenic gas, this AND DEWATERING FOR ORIFICE STRUCTURE is positioned in wind-tunnel, what flow in wind-tunnel is high-temperature gas, utilize this AND DEWATERING FOR ORIFICE STRUCTURE cryogenic gas and the mutual blending of high-temperature gas, one branch's cryogenic gas pastes on test block 8 surfaces, stainless steel thin slice 5 and electric heating sheets 6 use sedimentation bolts 9 are fixed on poly (methyl methacrylate) plate 7, upper surface at test block 8 evenly arranges thermopair 10, the saturating poly (methyl methacrylate) plate 7 of thermopair 10, be connected on data collecting instrument 11.
Main points of the present utility model:
Connect experimental piece and test block with draw-in groove:
The utility model is an AND DEWATERING FOR ORIFICE STRUCTURE (seeing accompanying drawing 1), according to the experiment needs, orifice plate is divided into two parts: experimental piece and test block.Experimental piece comprises plexi-glass tubular, poly (methyl methacrylate) plate and film cooling holes; Open film cooling holes on poly (methyl methacrylate) plate, connect the plexi-glass tubular consistent with its caliber below film cooling holes.Test block is comprised of four layer materials, pitch-dark, stainless steel thin slice, electric heating sheets, poly (methyl methacrylate) plate.Having identical part at experimental piece and test block two parts is poly (methyl methacrylate) plate.It is 15mm that experimental piece all forms thickness by poly (methyl methacrylate) plate, test block is comprised of four layer materials, and gross thickness is also 15mm, and wherein the poly (methyl methacrylate) plate plate thickness is 10mm, partly do one recessed at poly (methyl methacrylate) plate bottom 10mm, do in the experimental piece same position male member that a size adapts to.In the optimal design of gas turbine blades film cooling holes, need to change different experimental pieces, by the draw-in groove in the poly (methyl methacrylate) plate bottom, can be with experimental piece and test block dismounting easily.
Can measure the test block structure of dull and stereotyped heat transfer coefficient:
See that accompanying drawing 2 test blocks form by four layers, its order from top to bottom is pitch-dark, stainless steel thin slice, electric heating sheets, poly (methyl methacrylate) plate.The pitch-dark reflectivity that can increase the surface, stainless steel thin slice heat conductivility is good, and electric heating sheets can provide stable, as a to continue thermal source for test block, and poly (methyl methacrylate) plate plays simultaneously and supports and heat insulating function.Thermopair is penetrated poly (methyl methacrylate) plate and is connected to data collecting instrument by the downside of uniform welding at heating plate.With the temperature value that thermopair records, thermal infrared imager is calibrated.Keep the temperature of main flow and jet identical, electric heating sheets energising heating and power are known, consider suitable thermal loss, and flat plate wall temperature difference before and after heating by calculating can be calculated dull and stereotyped heat transfer coefficient.The air film availability also can utilize this test block structure to record: main flow is heated, and jet remains environment temperature, and the electric heating sheets no power can utilize thermal infrared imager to record wall surface temperature.For reducing heat radiation, utilize the sedimentation bolt to fix between four layer materials.
The course of work of the present utility model is as described below:
as shown in Figure 4 in embodiment, installation fixes the AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field of the present utility model, experimental study dry ice used is placed in aerosol producer 17, the power switch of water pump 21 is opened, store the water of normal temperature in bucket 20, after mixing with water, dry ice vaporizes, produce white smoke, the air compressing of high-pressure air source 23 to atmospheric pressure value is 2.5MPa to 3.0Mpa, the threshold switch 19 of opening high pressure source of the gas 23, make the air that high-pressure air source 23 discharges enter aerosol producer 17 by pipeline, adjust air mass flow by vortex shedding flow meter 18, air and dry ice smog enter into collection chamber 16 and are called jet through fully mixing, via plexi-glass tubular 3, enter in film cooling holes, meanwhile the air in wind-tunnel 14 is heated to the 353k left and right, wind speed modulation 10m/s, be called main flow, its temperature value and velocity amplitude can be recorded by hot-wire anemometer 15, experimental piece 2 place's jets and main flow at the film cooling holes plate are mixed mutually, and can observe at test block 8 places its mixing situation that obtains, be evenly arranged thermopair 10 at test block 8 place's electric heating sheets 6, thermopair 10 is connected to data collecting instrument 11 can the displays temperature value, utilize the temperature value that thermopair 10 records that thermal infrared imager 27 is calibrated, can observe on industrial computer 24 and obtain Temperature Distribution, can obtain the air film availability of film cooling holes plate after processing through data, the flow field situation of utilizing simultaneously high-speed camera 2 to take to obtain main flow and jet, electric heating sheets 6 energising heating with test block 8, keeping the interior main flow of wind-tunnel is normal temperature, the temperature that is main flow and jet is identical, do not add dry ice and water pump no power in aerosol producer 17, utilize the thermopair 10 of 6 times layouts of electric heating sheets and the wall surface temperature that data collecting instrument 11 records the film cooling holes plate, temperature and the power of electric heating sheets 6 that electric heating sheets 6 do not switch on before heating have been recorded known, consider suitable thermal loss, can record the heat transfer coefficient of film cooling holes plate.
Through said method; can make with above-mentioned pilot system that in wind-tunnel, the main flow flow velocity reaches 10m/s and remains unchanged; the flow velocity of jet can reach 5m/s～30m/s; main flow and jet can have the temperature difference of 50k left and right; jet and main flow immixture can realize the heat protection to test block 8; the temperature field can and be measured heat transfer coefficient and analyze by thermal infrared imager 27, and the flow field can set off a discussion by high-speed camera 26.Can utilize easily notch to change experimental piece 3 in experimentation, the effect of research film cooling holes layout to cooling effect.In experimentation, test block only has a test block 8, can reduce systematic error.
Shown in the above and figure is only preferred implementation of the present utility model.Should be pointed out that for the person of ordinary skill of the art, under the prerequisite that does not break away from the utility model principle, can also make some modification and improvement, these also should be considered as belonging to protection domain of the present utility model.
Claims (5)
1. AND DEWATERING FOR ORIFICE STRUCTURE that is used for research gas turbine blades air film coolant flow field and temperature field, comprise experimental piece (2) and test block (8), it is characterized in that: draw-in groove male member (12) is set on described experimental piece (2), recessed of draw-in groove (13) is set on described test block (8), and described experimental piece (2) and test block (8) are fastened togather by described draw-in groove male member (12) and draw-in groove recessed (13).
2. the AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field as claimed in claim 1, it is characterized in that: be provided with film cooling holes (1) on described experimental piece (2), described film cooling holes (1) the below connection plexi-glass tubular (3) identical with its caliber.
3. the AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field as claimed in claim 1, it is characterized in that: described test block (8) comprises pitch-dark (4), stainless steel thin slice (5), electric heating sheets (6) and organic glass sheet (7), described pitch-dark (4) are coated on described stainless steel thin slice (5), and described stainless steel thin slice (5) and electric heating sheets (6) are fixed on described poly (methyl methacrylate) plate (7) with sedimentation bolt (9).
4. the AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field as claimed in claim 3, it is characterized in that: the upper surface at described test block (8) evenly arranges thermopair (10), described thermopair (10) sees through described poly (methyl methacrylate) plate (7), is connected to data collecting instrument (11).
5. the AND DEWATERING FOR ORIFICE STRUCTURE for research gas turbine blades air film coolant flow field and temperature field as claimed in claim 2, is characterized in that: comprise a plurality of described experimental pieces (2) with quantity and structure of different film cooling holes (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220634512 CN202928778U (en) | 2012-11-27 | 2012-11-27 | Orifice plate structure for studying gas turbine blade gas film cooling flow field and temperature field |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220634512 CN202928778U (en) | 2012-11-27 | 2012-11-27 | Orifice plate structure for studying gas turbine blade gas film cooling flow field and temperature field |
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| Publication Number | Publication Date |
|---|---|
| CN202928778U true CN202928778U (en) | 2013-05-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220634512 Expired - Fee Related CN202928778U (en) | 2012-11-27 | 2012-11-27 | Orifice plate structure for studying gas turbine blade gas film cooling flow field and temperature field |
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| CN (1) | CN202928778U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869099A (en) * | 2018-06-01 | 2018-11-23 | 北京航空航天大学 | Gaseous film control structure, liquid-propellant rocket engine and its gaseous film control test method |
| CN110737292A (en) * | 2019-09-20 | 2020-01-31 | 江苏大学 | kinds of wall surface temperature control system built in high-temperature high-pressure container |
| CN112283996A (en) * | 2020-09-07 | 2021-01-29 | 西北工业大学 | Cooling method and cooling device for infrared glass window in high-temperature environment |
| CN113899784A (en) * | 2021-12-08 | 2022-01-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring content of complex icing cloud mist water in large icing wind tunnel |
-
2012
- 2012-11-27 CN CN 201220634512 patent/CN202928778U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108869099A (en) * | 2018-06-01 | 2018-11-23 | 北京航空航天大学 | Gaseous film control structure, liquid-propellant rocket engine and its gaseous film control test method |
| CN108869099B (en) * | 2018-06-01 | 2020-07-31 | 北京航空航天大学 | Air film cooling structure, liquid rocket engine and air film cooling test method thereof |
| CN110737292A (en) * | 2019-09-20 | 2020-01-31 | 江苏大学 | kinds of wall surface temperature control system built in high-temperature high-pressure container |
| CN112283996A (en) * | 2020-09-07 | 2021-01-29 | 西北工业大学 | Cooling method and cooling device for infrared glass window in high-temperature environment |
| CN113899784A (en) * | 2021-12-08 | 2022-01-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring content of complex icing cloud mist water in large icing wind tunnel |
| CN113899784B (en) * | 2021-12-08 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring content of complex icing cloud mist water in large icing wind tunnel |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130508 Termination date: 20131127 |