CN106401654A - Disperse air film cooling hole structure - Google Patents
Disperse air film cooling hole structure Download PDFInfo
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- CN106401654A CN106401654A CN201610931944.XA CN201610931944A CN106401654A CN 106401654 A CN106401654 A CN 106401654A CN 201610931944 A CN201610931944 A CN 201610931944A CN 106401654 A CN106401654 A CN 106401654A
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- pore structure
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a disperse air film cooling hole structure which is used for air film cooling of bodies or upper edge plates and lower edge plates of turbine blades of a gas turbine. A cooling hole is overall of the expansion structure and is divided into a straight section and an expansion section in the cold air flow direction; the straight section is located on the cold air side; and the expansion section is located on the gas side. The cross section profile of the straight section is a flat rectangle, and each of short edges at the two sides of the flat rectangle has an inwards-contracting structure. The disperse air film cooling hole has the advantages that an air film is large in transverse width and uniform in covering, and the air film cooling effect is good; a stable reverse-kidney-shaped vortex pair is formed at the downstream position, and the air film is not prone to being separated from the wall face under a high blowing ratio; the cold air outlet velocity is high, and the pneumatic mixing loss is small; and the disperse air film cooling hole is simple in structure and can be easily achieved in actual turbine cooling blades.
Description
Technical field
The present invention relates to gas turbine technology field, it is a kind of discrete gaseous film control pore structure, combustion gas can be greatly improved
The Film Cooling of turbo blade and horizontal film overcast area, mixing loss is also less it is adaptable to gas turbine leaf simultaneously
The surface cooling down is needed in piece passage.
Background technology
Gas turbine is widely used in the fields such as aviation, military affairs, traffic, electric power, in order to improve the whole machine thermal efficiency, combustion gas wheel
The turbine inlet temperature (TIT) more and more higher of machine, the resistance to extreme temperature of far super turbo blade alloy material at present.Discrete holes gaseous film control
It is currently commonly used efficient cooling technology, be widely used in turbine blade of gas turbine blade and listrium cooling.Its
General principle is to introduce cooling air to turbo blade from compressor, and cooling air is by the discrete Cooling Holes being clouded on blade
Flowing out and be covered in blade surface, thus reaching the purpose completely cutting off hot main flow and metal blade surface, reducing blade surface temperature,
Ensure the reliability of turbo blade longtime running.
The most frequently used Cooling Holes of discrete holes gaseous film control are cylindrical holes, and cylindrical hole has that structure is simple, it is strong not affect blade
The advantages of degree, handling ease, therefore it is widely used on gas-turbine blade.But stepping up with turbine inlet temperature (TIT),
Cylindrical hole cooling effect is low, under little, the high air blowing ratio of film overcast area air film easily depart from wall, mixing loss larger the shortcomings of
More and more obvious, in addition to blade costal field, on currently advanced gas-turbine blade, (suction surface, pressure face, end wall) is seldom adopted
Use cylindrical hole gaseous film control.
In recent years, the defect not enough in order to improve cylindrical hole cooling effect, domestic and international researcher proposes multiple new successively
The Cooling Holes of grain husk, to improve cooling effect.Such as, expanded bore, double spray-hole, Jie Meikong, slot hole, contraction slotted eye etc..Above-mentioned
Cooling pore structure is all greatly improved cooling effectiveness than cylindrical hole, and wherein expanded bore is most successful cooling pore structure, applies
Turbo blade in multiple actual aero-engines and ground heavy duty gas turbine.On the whole, proposed at present various changes
Enter type Cooling Holes almost all based on cylindrical hole, that is, the cold air of Cooling Holes end of entering is substantially cylindrical hole, or all with circle
Based on cross section, the port of export that improvement part is primarily directed to Cooling Holes is carried out.Therefore, most Cooling Holes at present
It is considered the improvement based on cylindrical hole or circular cross section bores.
In fact, the proposition earliest of gaseous film control concept is the prototype structure using is bathtub construction, or it is referred to as two dimension continuously
Groove, does not affect for the ease of practical application and blade strength, continuous slot structure is gradually evolved into the hole of discrete distribution, due to structure
Simple and easy to process, cylindrical hole becomes the Cooling Holes commonly using, and this is also current most improved high-efficiency gas
The reason air inlet side of film cooling hole still adopts cylindrical hole.However, in terms of cooling effect rice, the gaseous film control effect of continuous slot structure
The various Cooling Holes based on cylindrical hole of fruit discretization to be substantially better than, only because succeeding vat is in manufacture, structure, arrangement
Etc. aspect some problems, limit its use on turbine cooling blade, but this basic structure of trench structure be permissible
Use for reference and be used for developing more efficiently cooling pore structure.
Content of the invention
(1) technical problem to be solved
In view of this, the present invention discloses a kind of discrete gaseous film control pore structure, in order to increase substantially discrete Cooling Holes
Film Cooling, increases film overcast area, obtains favourable downstream vortex structure, and the air film strengthening under high air blowing ratio attaches
Property.
(2) technical scheme
For reaching above-mentioned purpose, the invention provides a kind of discrete gaseous film control pore structure, for gas-turbine blade leaf
The gaseous film control of inframarginal on body or blade, described discrete gaseous film control pore structure includes multiple Cooling Holes of discrete distribution, uses
Flow out from described Cooling Holes in cooling gas and form air film, the cross section of described Cooling Holes is with the flat square receiving structure in the wall of side
Shape.
In such scheme, described Cooling Holes are in integrally two-part expansion structure, including flat segments and expansion segment, described straight
The cross-sectional profiles of section are in flat rectangle, and described flat rectangle two side has interior receipts structure, and described expansion segment is by described flat square
The lateral magnification of shape two side is formed；
In such scheme, the ratio of width to height W/H of the cross section of described flat segments is between 3 and 8；
In such scheme, the height H of the cross section of described flat segments is 0.3 to 0.6 times of cylinder bore diameter D, described circle
The cross-sectional area of post holes is equal with the cross-sectional area of described Cooling Holes；
In such scheme, the ratio Lt/L of the length of described flat segments and described Cooling Holes total length is between 1/4 and 1/2；
In such scheme, the two side of the cross section of described flat segments has interior receipts structure, and described interior receipts structure is to pass through
Cooling Holes downstream wall is made to be formed to contract；
In such scheme, the interior receipts dimension delta of described downstream wall at 0.1 to 0.3 times of cylinder bore diameter D, described cylindrical hole
Cross-sectional area equal with the cross-sectional area of described Cooling Holes；
In such scheme, described expansion segment both sides have lateral magnification angle γ, and described lateral magnification angle γ is at 10 ° and 14 °
Between；
In such scheme, the jet angle α scope that described Cooling Holes are suitable for is between 30 ° and 70 °；
In such scheme, the horizontal pitch of holes between the plurality of Cooling Holes is S, described transverse holes interval S and cylindrical hole
The ratio S/D of footpath D is not less than 5, and the cross-sectional area of described cylindrical hole is equal with the cross-sectional area of described Cooling Holes.
(3) beneficial effect
The Cooling Holes that the present invention provides, are that the circular cross section in conventional expansion hole is changed into receipts structure in the wall of side
Flat rectangular cross section, effectively expands the exit width in hole, is conducive to the cooling effect that the film overcast obtaining big width reaches
Really high.By the interior receipts structure of flat rectangular cross section both sides downstream wall, the expansion flowing of cooling in the hole can be controlled, cold
But hole downstream obtains favourable anti-kidney type vortex pair, adjusts the lateral magnification degree of air film, so that air film is distributed and more they tends to uniformly, and strengthens
Air film under the high air blowing ratio attaches ability.
Brief description
Fig. 1 a is existing fan expanded bore structural representation；
Fig. 1 b is existing dust-pan shaped hole structural representation；
Fig. 2 a is the Cooling Holes structural representation of the present invention；
Fig. 2 b is the shape of cross section schematic diagram of the flat segments of the present invention；
Fig. 2 c is the various ways schematic diagram received in the cross section end wall of the flat segments of the present invention；
Fig. 2 d is multiple Cooling Holes lateral arrangement schematic three dimensional views of the present invention；
Fig. 2 e is multiple Cooling Holes horizontal spacing schematic diagrames of the present invention；
Fig. 3 a is the flat rectangular cross section change schematic diagram of the flat segments of the present invention；
Fig. 3 b is the structural representation under different flat rectangle the ratio of width to height of Cooling Holes of the present invention；
Fig. 3 c is the averagely cold effect experimental result of Cooling Holes semicircular wall time space of the present invention；
Fig. 3 d is the averagely cold effect experimental result of Cooling Holes linear side wall time space of the present invention；
Fig. 4 a is the structural representation during Cooling Holes lateral magnification angle change of the present invention；
Fig. 4 b is the experiment knot of effect cold on space average impact in lateral magnification angle during the Cooling Holes semicircular wall of the present invention
Really；
Fig. 4 c is the experiment knot of effect cold on space average impact in lateral magnification angle during the Cooling Holes linear side wall of the present invention
Really；
Fig. 5 is the cooling effect at downstream x/D=10 during debit's case in the side wall of Cooling Holes corresponding diagram 2c of the present invention
Distribution values result of calculation；
Fig. 6 is debit's case schematic diagram in Cooling Holes side wall in big rectangle the ratio of width to height of the present invention.
Specific embodiment
For making the object, technical solutions and advantages of the present invention become more apparent, below in conjunction with specific embodiment, and reference
Accompanying drawing, the present invention is described in further detail.
Fig. 1 a and Fig. 1 b respectively show the structure of existing fan-shaped and dustpan-shaped expanded bore, and this is the application of mesh first two
Widest Cooling Holes, are all greatly improved than the cooling effect of simple cylindrical hole.Holes broadly falls into expansion type hole, i.e. Cooling Holes
Front half section is cylindrical hole, and the second half section of Cooling Holes is expansion structure, including lateral magnification and front expansion.The straight segment length in hole is used
Lt represents, the total length in hole is represented with L, and lateral magnification angle is represented with γ, and the front angle of flare is represented with ε.Obviously, two kinds being shown
Existing typical case's expansion type hole is all to have carried out divergence process to outlet on the basis of common cylinder hole, to obtain more preferable gas
Film cooling effect.
Fig. 2 a is the Cooling Holes structural representation of the present invention.Provided by the present invention for gas-turbine blade blade or blade
The Cooling Holes of the gaseous film control of the upper and lower end wall of passage, are divided into flat segments and expansion segment two parts along cold air flow direction, flat segments are located at
Cold air side, expansion segment is located at combustion gas side, and the ratio Lt/L of the length of flat segments and this Cooling Holes total length is between 1/4 to 1/2.Figure
2b is the shape of cross section schematic diagram of the flat segments of the present invention, and flat segments cross section is in integrally flat rectangle, as shown in phantom in FIG.,
Length-width ratio W/H between 3 and 8, expansion segment based on rectangle two side to both sides lateral magnification, lateral magnification angle at 10 ° and
Between 14 °.It should be noted that the both sides minor face of rectangle has interior receipts structure, interior receipts dimension delta is between 0.1D and 0.3D.Remove
Semicircle shown in Fig. 2 b, the interior receipts of realizing two side also can be realized by modes such as camber line, rounding, oblique lines, such as Fig. 2 c
Shown.The situation receiving structure (scheme 5 and 6) in structure (scheme 1) and upstream wall of receiving in no is contained in Fig. 2 c, mainly as
Contrast uses.Fig. 2 d is multiple Cooling Holes lateral arrangement schematic three dimensional views of the present invention.Fig. 2 e is multiple Cooling Holes of the present invention
Horizontal spacing schematic diagram, when being arranged as a row, pitch of holes is represented with S, because hole width of going out is larger, requires S/D during arrangement
At least more than 5.
The cooling pore structure of the present invention being shown by Fig. 2 a, Fig. 2 b and Fig. 2 c is visible, the cross section of pass of the present invention
The flat rectangle that iso-cross-section amasss is switched to by the circle in conventional expansion hole, remains the version (present invention of expansion of going out simultaneously
Pass only has lateral magnification), the Cooling Holes that therefore present invention provides are the transversal of Cooling Holes with the essential distinction of existing Cooling Holes
Face switchs to the very big flat rectangle of the ratio of width to height by circle.Importantly, due to receive the presence of structure in the wall of side so that the expansion of in the hole
Flowing is rationally controlled, and can produce favourable anti-kidney type vortex pair in hole downstream, the gentle film of attaching performance strengthening air film covers
The uniformity of lid.For the expanded bore based on cylindrical hole, advantage is the Cooling Holes that the present invention provides：First, transversal
Face lateral dimension effectively expands, and coordinates lateral magnification angle, and the transverse width of cooling hole exits is bigger, the horizontal area coverage of air film
Wider；Secondly, by footage cun in reasonable control, evenly stable film overcast can be obtained in hole downstream；Finally, only
On the premise of having lateral magnification angle, the discrete film cooling holes discharge area that the present invention provides is less than the expansion based on cylindrical hole
Hole, the cold air outlet speed of pass therefore of the present invention is higher, is conducive to improving the cooling effect in remote downstream, and reduces pneumatic blending
Loss.
Each parameter of Cooling Holes of the present invention all has a significant impact to Film Cooling, and Binding experiment and numerical computations are tied
Really, the effect of each parameter and span in the discrete gaseous film control structure that the present invention described further below provides.Each ginseng
Number definition can be found in Fig. 2 a-2d.Numerical computations are that the situation for D=10mm is carried out for aperture, and computation model is flat board, main
Stream Mach number Ma=0.3, cold air-main flow density ratio is DR=1.75, air blowing ratio scope M=0.5-2.5, and main flow turbulivity is Tu
=5%, pitch of holes S/D=6.Experiment is to carry out in flat plate model, obtains Film Cooling using PSP measuring method, wherein
Mainstream speed is Vm=25m/s, aperture D=4mm, and cold air-main flow density ratio is DR=1.38, air blowing ratio scope M=0.5-
2.5, main flow turbulivity is Tu=3.5%, pitch of holes S/D=6.
The ratio of width to height (W/H) of square-section：For the cross-sectional area equivalence with common cylinder hole, or the matter keeping single hole
Amount flow is close, and the flat square-section of the Cooling Holes that the present invention provides is amassed requirement and amassed equal or phase with the circular cross-section of cylindrical hole
Seemingly, simultaneously in order that shape is amassed closer to slot structure it is desirable to W/H at least 3 is it is contemplated that process issues in flat square-section,
It is assumed that the coolant aperture of actual turbo blade is as D=1mm on the basis of the common cylinder hole of a diameter of D, if rectangular cross section
Both sides be semicircle, during W/H=3.5, then corresponding cross-sectional height is H=0.49.If using different in Fig. 2 c
Flat rectangular side wall shape, then H value may have little change within the specific limits.In fact, flat square-section the ratio of width to height W/H is got over
Greatly, then the average Film Cooling of cooled flat board is higher.Fig. 3 a gives three kinds of typical rectangle aspect ratio change, corresponding
Every kind of rectangle the ratio of width to height, sets forth two kinds of sidewall shape, i.e. semicircular wall and straight sidewall.Fig. 3 b is different rectangle width
High than under Cooling Holes structural representation, wherein 17D, 20D, 23D represent 1.7 that rectangular cross section width is cylinder aperture respectively
Again, 2.0 times and 2.3 times, Cir and Str represents semicircular wall and straight sidewall respectively, and 14deg represents that lateral magnification angle is 14
Degree.Space average Film Cooling in the range of Fig. 3 c and 3d downstream 30D × 6D that respectively experiment obtains is with air blowing ratio
Change.Arrive from the experimental results, rectangle the ratio of width to height is bigger, then space average cooling effect is higher, even the rectangle width of minimum
High ratio situation, space average cooling effect also significantly improves than scallop hole.Additionally, semicircular wall is more suitable than linear pattern side wall
Answer high air blowing ratio situation, this is also that the reason receive structure in the wall of setting square-section side is located.
Lateral magnification angle γ：Lateral magnification angle is bigger, then the width of cooling hole exits is bigger.But due to depositing of expansion flowing
Excessive lateral magnification angle is likely to result in the hole flow separation, and therefore maximum extension angle value is advisable in γ=14 °.As
Fruit will reach certain Cooling Holes and go out width, can be using the slightly smaller lateral magnification angle of larger rectangle the ratio of width to height W/H cooperation
γ realizes.Fig. 4 a shows that two kinds of the ratio of width to height coordinate the situation of two kinds of angles of flare, and the cooling hole exits width of four kinds of schemes is substantially
Unanimously, in figure 12deg and 10deg represent that lateral magnification angle is 12 degree and 10 degree respectively, and other symbols are consistent with Fig. 3 b.Fig. 4 b
Show with the space average cooling effect of Fig. 4 c, in blowing ratio M ＜ 2.0, somewhat reduce lateral magnification angle and do not reduce totally
Cooling effect, but during blowing ratio M ＞ 2.0, large expansion angle is favourable for increasing overall cooling effect.In addition, semicircle side
Wall is favourable to high air blowing ratio condition.
Straight segment length Lt：This parameter affects cold air and flows in the expansion of in the hole, and expansion flowing when Lt numerical value is less is sent out
Raw early, there is evening in expansion flowing when Lt numerical value is larger.In order to keep going out flowing uniformly, the ratio Lt/ of the total length L in Lt and hole
L is appropriate between 1/4-1/2, and Lt/L=1/3 is recommendation.
Hole jet angle α：Film cooling holes all have certain jet angle in arrangement, and hole is arranged in pressure face or suction
The size of face jet angle is variant, and between 20-80 degree, the jet angle of Cooling Holes of the present invention exists the jet angle in generally cylindrical hole
All applicable between 30-70 degree.
Pitch of holes S：Cooling Holes sectional area due to the present invention is flat rectangle, and the ratio of width to height is larger, has laterally simultaneously
The angle of flare, therefore cooling hole exits transverse width are significantly greater than common cylinder hole and the modified based on common cylinder hole
Expanded bore, using cylinder aperture as reference when being therefore used, S/D should be not less than 5.
Dimension delta is received in the wall of side：This parameter has strong influence to Film Cooling distribution.Fig. 5 shows Fig. 2 c
In 8 kinds of sidewall shape holes the distribution of horizontal Film Cooling, this result rice is from numerical computations.It is seen that, receive in the wall of side
Receive in size and side wall is all Film Cooling distribution to be had in upstream wall or downstream wall to significantly affect.Side wall
In the event of in upstream wall, then downstream air film distribution is mono-modal to interior receipts.In the wall of side, transmitting-receiving life is in downstream wall, then downstream air film
Distribution is bimodal or three peak forms, and relevant with square-section length-width ratio.Obviously, the overall cooling effect of bimodal or three peak forms
Higher.Therefore, receive in the wall of side and should be taken at downstream wall, the scheme 2,3,4,7,8 in such as Fig. 2 c.In the wall of side, footage cun is big, then be inclined to
In bimodal pattern, side wall, footage cun is little, then tend to three peak patterns.The less rectangular cross section for length-width ratio, in the wall of side
Footage cun should get the small value.For the rectangular cross section that length-width ratio is larger, footage cun in the wall of side should take slightly larger value.In general,
In the wall of side footage cun take appropriate between 0.1D-0.3D.As long as have in the wall of side being stored in, then air film hole downstream can produce anti-kidney type
Vortex pair is favourable to the stable of air film and uniform fold.
Fig. 6 shows a kind of situation of larger rectangle the ratio of width to height, and in such cases, footage cun in larger downstream wall is compared
It is easy to obtain uniform film overcast in downstream.
Particular embodiments described above, has carried out detailed further to the purpose of the present invention, technical scheme and beneficial effect
Describing in detail bright it should be understood that the foregoing is only the specific embodiment of the present invention, being not limited to the present invention, all
Within the spirit and principles in the present invention, any modification, equivalent substitution and improvement done etc., should be included in the protection of the present invention
Within the scope of.
Claims (10)
1. a kind of discrete gaseous film control pore structure, including multiple Cooling Holes of discrete distribution, for cooling gas from described cooling
Hole is flowed out and is formed air film it is characterised in that the cross section of described Cooling Holes is with the flat rectangle receiving structure in the wall of side.
2. discrete gaseous film control pore structure according to claim 1 is it is characterised in that described Cooling Holes are in integrally two-part
Expansion structure, including flat segments and expansion segment, the cross-sectional profiles of described flat segments are in flat rectangle, described flat rectangle two side tool
There is interior receipts structure, described expansion segment is to be formed by the lateral magnification of described flat rectangle two side.
3. discrete gaseous film control pore structure according to claim 2 is it is characterised in that the width of the cross section of described flat segments
Ratios are between 3 and 8.
4. discrete gaseous film control pore structure according to claim 3 is it is characterised in that the height of the cross section of described flat segments
Degree H is 0.3 to 0.6 times of cylinder bore diameter D, the cross-sectional area phase of the cross-sectional area of described cylindrical hole and described Cooling Holes
Deng.
5. discrete gaseous film control pore structure according to claim 2 it is characterised in that the length of described flat segments with described
The ratio of Cooling Holes total length is between 1/4 and 1/2.
6. discrete gaseous film control pore structure according to claim 2 it is characterised in that the cross section of described flat segments two
Side wall has interior receipts structure, and described interior receipts structure is to be formed to contract by making Cooling Holes downstream wall.
7. discrete gaseous film control pore structure according to claim 6 is it is characterised in that the interior footage cun of described downstream wall is
0.1 to 0.3 times of cylinder bore diameter D, the cross-sectional area of described cylindrical hole is equal with the cross-sectional area of described Cooling Holes.
8. discrete gaseous film control pore structure according to claim 2 is it is characterised in that described expansion segment both sides have laterally
The angle of flare, described lateral magnification angle is between 10 ° and 14 °.
9. discrete gaseous film control pore structure according to claim 1 it is characterised in that described Cooling Holes be suitable for jet angle
Scope is between 30 ° and 70 °.
10. discrete gaseous film control pore structure according to claim 1 is it is characterised in that between the plurality of Cooling Holes
Laterally pitch of holes is S, and described transverse holes interval S is not less than 5 with the ratio of cylinder aperture D, the cross-sectional area of described cylindrical hole
Equal with the cross-sectional area of described Cooling Holes.
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| CN107725115B (en) * | 2017-04-28 | 2019-07-30 | 中国航发湖南动力机械研究所 | The aerofoil profile air film hole and electrode of aero-engine hot-end component |
| CN107725115A (en) * | 2017-04-28 | 2018-02-23 | 中国航发湖南动力机械研究所 | The aerofoil profile air film hole and electrode of aero-engine hot-end component |
| WO2019104786A1 (en) * | 2017-12-01 | 2019-06-06 | 上海海洋大学 | Elongated funnel-shaped jet nozzle structure |
| US10602760B2 (en) | 2017-12-01 | 2020-03-31 | Shanghai Ocean University | Slender and funnel-shaped jet nozzle structure |
| CN111441829A (en) * | 2019-01-16 | 2020-07-24 | 通用电气公司 | Turbine engine component with cooling holes |
| US11873734B2 (en) | 2019-01-16 | 2024-01-16 | General Electric Company | Component for a turbine engine with a cooling hole |
| CN111441829B (en) * | 2019-01-16 | 2023-02-24 | 通用电气公司 | Turbine engine component with cooling holes |
| CN111120009A (en) * | 2019-12-30 | 2020-05-08 | 中国科学院工程热物理研究所 | Ribbed transverse flow channel with rows of film holes having channel-shaped cross-sections |
| CN111042872A (en) * | 2019-12-31 | 2020-04-21 | 中国科学院工程热物理研究所 | Transverse expansion meridian contraction groove-shaped air film hole |
| US20220170375A1 (en) * | 2020-01-06 | 2022-06-02 | Dalian University Of Technology | Honeycomb-like helically cavity cooling structure of turbine blade |
| CN111412020A (en) * | 2020-03-30 | 2020-07-14 | 中国科学院工程热物理研究所 | Turbine blade trailing edge cooling structure |
| CN112627904A (en) * | 2020-12-23 | 2021-04-09 | 西北工业大学 | Novel bucket type air film cooling hole and design method thereof |
| CN112833424A (en) * | 2021-01-08 | 2021-05-25 | 西北工业大学 | Novel volute type combustion chamber flame tube wall surface structure |
| CN113279818B (en) * | 2021-06-24 | 2022-10-21 | 中国科学院工程热物理研究所 | Contraction type double-jet air film hole |
| CN113279818A (en) * | 2021-06-24 | 2021-08-20 | 中国科学院工程热物理研究所 | Contraction type double-jet air film hole |
| CN114863783A (en) * | 2022-05-27 | 2022-08-05 | 中国科学院工程热物理研究所 | Turbine blade leading edge simulation piece |
| CN114863783B (en) * | 2022-05-27 | 2024-02-27 | 中国科学院工程热物理研究所 | Turbine blade leading edge simulation piece |
| CN115493163A (en) * | 2022-09-06 | 2022-12-20 | 清华大学 | Combustor flame tube and efficient cooling method for combustor flame tube |
| CN115493163B (en) * | 2022-09-06 | 2024-02-20 | 清华大学 | Combustion chamber flame tube and high-efficiency cooling method thereof |
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Application publication date: 20170215 |