CN106437866B - A kind of discrete gaseous film control pore structure - Google Patents
A kind of discrete gaseous film control pore structure Download PDFInfo
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- CN106437866B CN106437866B CN201610931996.7A CN201610931996A CN106437866B CN 106437866 B CN106437866 B CN 106437866B CN 201610931996 A CN201610931996 A CN 201610931996A CN 106437866 B CN106437866 B CN 106437866B
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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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- 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 kind of discrete gaseous film control pore structures, are related to gas turbine turbine cooling technology.Pass of the invention is implemented in fusiform cross-sectional, and whole is in expanding, is formed by two sections, flat segments are located at cold air side, and expansion segment is located at high-temperature fuel gas side.The cross section of flat segments is in shuttle shape, and shuttle shape is made of 4 sections of circular arcs, and four arcs are tangent, and upstream and downstream wall is in evagination；Expansion segment two sides are formed by the lateral magnification of flat segments two sides circular arc, and expansion segment upstream and downstream wall is the curved surface of evagination.Gaseous film control structure entirety cooling effect of the invention is high, and film overcast area is big；Downstream generates controllable anti-kidney shape vortex pair, and lateral film overcast is uniform；Cold air outlet speed is high, and pneumatic mixing loss is small；Easy to process, existing air film hole processing technology can be realized.Air film pass of the invention is cooling for gas turbine blade, suitable for the pressure face of turbine blade, suction surface and upper and lower end wall surface.
Description
Technical field
The present invention relates to the fields of gas turbine cooling technology, are in particular a kind of discrete gaseous film control pore structures.
Background technique
Gas turbine is widely used in the fields such as aviation, military affairs, traffic, electric power, and pursuing higher efficiency is gas turbine
The important goal of development, improving turbine-inlet temperature is the most effectual way for improving gas turbine overall efficiency.Current terrestrial weight
The resistance to extreme temperature of the turbine-inlet temperature of type combustion engine and high thrust aero-engine far super turbine blade alloy material, it is necessary to adopt
Turbine blade long-time reliability service is ensured with turbine cooling technology.Discrete holes gaseous film control is current gas turbine turbine leaf
The efficient cooling technology that piece generallys use, the basic principle is that introducing cooling air to turbine blade inner cavity, cooling from compressor
Air flows out by the cooling hole being clouded on blade and is covered in blade surface, to reach isolation high temperature mainstream and metal leaf
The purpose on piece surface reduces blade surface temperature.
The most common pass of discrete holes gaseous film control is cylindrical hole, cylindrical hole have structure is simple, do not influence blade strength,
The advantages that handling ease, therefore be widely used on gas turbine blade.But with stepping up for turbine-inlet temperature, cylinder
The weakness of hole gaseous film control starts to show, such as：Cooling effect is lower, film overcast area is small, easily blow off wall under high air blowing ratio
Face, mixing loss are larger etc., at present in addition to blade inlet edge or movable vane leaf top, advanced gas turbine blade (suction surface, pressure face,
End wall) cylindrical hole gaseous film control is seldom used.For many years, domestic and international researcher is developing always efficient film cooling holes
Type.The especially close more than ten years, domestic and international researcher proposes many novel gaseous film control structures or pass successively, to improve gas
Film cooling effect.For example, expanded bore, double spray-holes, Jie Meikong, slot hole, contraction slot etc..Above-mentioned pass is bigger than cylindrical hole
Width improves Film Cooling, and gaseous film control performance is significantly enhanced.Wherein expansion outlet opening is most successful one kind
Pass is currently all using this kind of pass on many advanced combustion engine turbines, and only the export expansion structure of specific pass is poor
It is different.
On the whole, at present domestic and international proposed various gaseous film control structures almost based on cylindrical hole, or
Say constructed based on circular cross section, i.e. the cold air input end of pass is substantially cylindrical hole, improvement part primarily directed to
The outlet end of air film hole carries out.Therefore, most passes can be classified as circular cross section bores scope at present.
In fact, the best gaseous film control structure of generally acknowledged cooling effect is by combining with internal cooling structure at present
And the flute profile gaseous film control structure formed, the cold air which is similar to blade trailing edge, which goes out, flows seam, and flute profile gaseous film control structure can
To form the structure for being similar to succeeding vat in blade surface, there is very high Film Cooling.But, the cooling knot
Structure fundamentally changes the overall construction of blade, and the design of existing gaseous film control and blade machining process are formd and centainly chosen
War, there has been no the precedents of practical application at present.But flute profile gaseous film control structure has the development of discrete holes gaseous film control structure
Certain to inspire, i.e. expansion cross-sectional width is very big to the effect for improving Film Cooling, and traditional circular cross section is turned
The cross section for becoming flattening will be helpful to promote gaseous film control performance, at present the film hole structure of existing rectangular cross section.So
And rectangular cross section air film hole there are wall effect, i.e. side wall leads to the uneven of film overcast.It is flat to further improve
The film overcast uniformity of cross section air film hole, it is necessary to set about from cross-sectional shape, control is reached by cross-sectional shape optimization
The purpose of Film Cooling Flow Inside Linear.
Summary of the invention
(1) technical problems to be solved
In view of this, the present invention discloses a kind of discrete gaseous film control pore structure, to improve the cooling effect of discrete air film hole
Fruit, the mixing loss for obtaining more uniform film overcast, reducing gaseous film control.
(2) technical solution
In order to achieve the above objectives, the present invention provides a kind of discrete holes gaseous film control pore structures, including the more of discrete distribution
A cooling hole flows out to form air film for cooling gas from the cooling hole, and the cross section of the cooling hole is shuttle shape.
The cooling hole includes flat segments and expansion segment along its axis direction as a preferred implementation manner, described straight
Section is located at cold air side, and the expansion segment is located at high-temperature fuel gas side；
The cross section of the flat segments is in shuttle shape as a preferred implementation manner, is made of four arcs, flat segments
The corresponding circle of circular arc and the circular arc of two side wall of the upstream and downstream wall of cross section are tangent, upstream and downstream wall evagination；The expansion segment
It is that lateral magnification based on the cross section of flat segments is formed；
The width of the cross section of the flat segments and the ratio of height are between 3 and 5 as a preferred implementation manner,；
The height of the cross section of the flat segments and the ratio of cylinder bore diameter are 0.4 as a preferred implementation manner,
And between 0.6, the cross-sectional area of the cylindrical hole and the cross-sectional area of the cooling hole are equal；
The evagination height and cylinder bore diameter of the upstream wall of the cross section of the flat segments as a preferred implementation manner,
Ratio between 0.05 and 0.2, the cross-sectional area of the cylindrical hole and the cross-sectional area of the cooling hole are equal；
The downstream wall evagination height of the cross section of the flat segments and cylinder bore diameter as a preferred implementation manner,
For ratio between 0.0 and 0.15, the cross-sectional area of the cylindrical hole and the cross-sectional area of the cooling hole are equal；
As a preferred implementation manner, the ratio of the length of the flat segments and the cooling hole total length 0.25 and
Between 0.5；
Expansion segment two sides lateral magnification forms the angle of flare as a preferred implementation manner, and the angle of flare is at 8 degree
And between 14 degree；
The injection angular region of the cooling hole is between 30 degree and 70 degree as a preferred implementation manner,；
The lateral pitch of holes between the multiple discrete air film hole is S, the transverse holes as a preferred implementation manner,
The ratio of interval S and cylinder bore diameter is not less than 5, the cross-sectional area phase of the cross-sectional area and the cooling hole of the cylindrical hole
Deng.
(3) beneficial effect
The circular cross section in conventional film hole has been carried out flaky process, so that transversal by cooling hole of the present invention
Face is integrally in shuttle shape, so that it is high to obtain more uniform air film flowing and covering, whole Film Cooling；Film overcast area
Greatly；Downstream generates controllable anti-kidney shape vortex pair, and lateral film overcast is uniform；Cold air outlet speed is high, and pneumatic mixing loss is small, easily
In processing, existing air film hole processing technology be can be realized.
Detailed description of the invention
Fig. 1 a is the structural schematic diagram of cooling hole of the invention；
Fig. 1 b is the schematic diagram of the cross section of flat segments of the invention；
Fig. 1 c is the three dimensional structure diagram of cooling hole of the invention；
Fig. 2 a is the structural schematic diagram of existing scallop hole；
Fig. 2 b is the flat segments cross-sectional view of existing scallop hole；
Fig. 2 c is the three dimensional structure diagram of existing scallop hole；
Fig. 3 is that the flat segments cross-sectional aspect ratio of cooling hole of the invention changes；
Fig. 4 is the ratio of width to height and upstream and downstream wall evagination height change of cold air hole of the invention；
Fig. 5 a is that cooling hole of the invention is compared in W=1.7D with the space average cooling effect of existing scallop hole；
Fig. 5 b is that cooling hole of the invention is compared in W=2.0D with the space average cooling effect of existing scallop hole；
Fig. 5 c is that cooling hole of the invention is compared in W=2.3D with the space average cooling effect of existing scallop hole；
Fig. 6 is the lateral arrangement schematic diagram of cooling hole of the invention.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with specific embodiment, and reference
Attached drawing, the present invention is described in further detail.
Fig. 1 a is the structural schematic diagram of cooling hole of the invention.Provided by the present invention for gas-turbine blade blade or leaf
The cooling hole of the gaseous film control of end wall above and below piece channel is divided into flat segments and expansion segment two parts, straight section along cold air flow direction
In cold air inlet side, expansion segment is located at cold air outlet side, and hole is straight, and segment length is indicated with Lt, and the total length in hole is indicated with L, straight
Lt/L is between 1/4 and 1/2 for the ratio between the length of section and the cooling hole total length.Fig. 1 b is that the cross section of flat segments of the invention shows
It is intended to.Flat segments cross section is integrally in flat shuttle shape, and cross-sectional width indicates that cross-sectional height is indicated with H with W.Shuttle shape is horizontal
Section is made of 4 sections of circular arcs, and upstream and downstream wall is in evagination, and the circular arc of the corresponding circle of the circular arc of upstream and downstream wall and two sidewalls is tangent.Two
The side wa ll circle arc radius at end indicates that the radius of upstream wall is indicated with R2 with R1, and the radius of downstream wall is indicated with R3.Expansion segment two sides
Wall is formed from flat segments two sides circular arc to lateral magnification, and lateral magnification angle is indicated with γ.In order to construct shuttle shape structure, one is needed
Based on the rectangle of a auxiliary, as shown in dotted line in Fig. 1 b, assisting the width of rectangle is W, and height is indicated with h.When construction,
Two circles, radius R1=0.5h are first constructed in two sides.For the outer male structure of structurally downstream wall, using lower wall on rectangle as base
Standard, upper wall central point stretch out the building of λ 2 and the tangent circle in two sidewalls, and lower wall central point stretches out the building of λ 1 and two sidewalls
Tangent circle, therefore the height of entire shuttle shape is H=h+ λ 1+ λ 2.Fig. 1 c is the three dimensional structure diagram of cooling hole of the invention.
Fig. 2 a is the structural schematic diagram of existing scallop hole.This is current most widely used cooling hole, than simple cylinder
The cooling effect in hole greatly improves.The hole belongs to expansion outlet type hole, i.e. the front half section of cooling hole is cylindrical hole, after cooling hole
Half section is expansion structure.The straight segment length in hole indicates that the total length in hole is indicated with L with Lt, and lateral magnification angle is indicated with γ.It is aobvious
So, the scallop hole shown is to have carried out divergence process to outlet on the basis of common cylinder hole, to obtain better air film
Cooling effect.Fig. 2 b is the flat segments cross-sectional view of existing scallop hole.Fig. 2 c is the three-dimensional structure of existing scallop hole
Schematic diagram.
Fig. 3 is that the flat segments cross-sectional aspect ratio of cooling hole of the invention changes.Three cross-sectional width sizes are respectively W
=1.7D, 2.0D and 2.3D, D are cylinder aperture.If without the evagination of upstream and downstream wall, in the lesser situation of length-width ratio, then
Cold air easily focuses on hole two sides, and in the biggish situation of length-width ratio, cold air then easily focuses near centerline hole.In other words,
Under small length-width ratio, lateral magnification is too strong, and under aspect ratio, lateral magnification is insufficient.The outer male structure of air film hole upstream and downstream wall, it is main
Syllabus is the lateral magnification degree for adjusting cold air, to obtain more uniform film overcast, to improve whole cooling effect.
Fig. 4 is the ratio of width to height and upstream and downstream wall evagination height change of cold air hole of the invention.Three cross-sectional width sizes
Respectively W=1.7D, 2.0D and 2.3D.In small length-width ratio, by increasing the evagination λ 2 of upstream wall, can increase in air film hole
Air conditioning quantity at heart line, film overcast will be more uniform.In aspect ratio, by increasing the evagination λ 1 of downstream wall, thus
The cold air that will focus on centerline hole is diverted to hole two sides, and as a result and air film distribution is more uniform.In general, in length-width ratio
When smaller, such as W=1.7D, downstream wall can not evagination, and only upstream wall evagination, i.e. λ 1=0, and 2 > 0 of λ.It is bigger in length and width
When, such as W=2.0D and 2.3D, then λ 1 and λ 2 should be greater than 0, and λ 1 and λ 2 can take different value as the case may be.
Fig. 5 a-5c gives the space average cooling effect of the cooling hole of the invention that experiment obtains and existing scallop hole
The case where the case where the case where comparison, Fig. 5 a is W=1.7D, Fig. 5 b is W=2.0D, Fig. 5 c is W=2.3D.Experiment is in low speed
It is carried out on wind-tunnel, model is plate, obtains insulation Film Cooling using presser sensor paint measurement method.The principal flow velocity of experiment
Degree is 25m/s, and density ratio DR=1.38, mainstream turbulivity is 3.5%, and air blowing ratio range is M=0.5-2.5, lateral pitch of holes
With the ratio S/D=6.0 of cylinder aperture.In Fig. 5 a-5c, Fan-Shaped Hole indicates existing scallop hole, and structure is as schemed
Shown in 2a-2c.1.7D-0 and 1.7D-1 respectively indicates the first two pass cross section of one row of the top in Fig. 4.2.0D-0,
2.0D-1,2.0D-2 respectively indicate the pass cross section of an intermediate row in Fig. 4.2.3D-0,2.3D-1,2.3D-2 respectively indicate figure
The pass cross section of a bottom row in 4.ηsIndicate the average insulation Film Cooling of area, area average area is from hole
Export the region 6D × 30D started.It is not difficult to find out that cooling hole of the invention is under all air blowing ratios, in W=1.7D
It significantly improves area than existing scallop hole to be averaged cooling effect, absolute increase rate is more than 0.1.In W=2.0D, this
The area of the cooling hole of the invention cooling effect that is averaged still is much higher than scallop hole, especially in low air blowing ratio range (M=0.5-1.5)
Advantage is bigger.In W=2.3D, the area of the cooling hole of the invention cooling effect that is averaged still is much higher than scallop hole, but cross section
Geometric parameter is affected, and under the conditions of especially high air blowing ratio, the evagination size of upstream and downstream wall should be controlled in lesser range
It is interior.When aspect ratio, λ 1 and 2 value of λ be should not be too large.
Fig. 6 is the lateral arrangement schematic diagram of cooling hole of the invention.When being arranged as a row, lateral pitch of holes is indicated with S,
Since cooling hole exits width is larger, require S/D at least 5 or more when arrangement.
The parameters of cooling hole of the present invention have a significant impact cooling effect, Binding experiment and numerical result, with
The effect and value range of the lower cooling hole parameters that the present invention will be described in detail provides.
Straight segment length Lt：This parameter influences expansion flowing of the cold air in hole, expansion flowing hair when Lt numerical value is smaller
Raw early, evening occurs for expansion flowing when Lt numerical value is larger.In order to keep output flow uniform, the ratio Lt/ of the total length L in Lt and hole
L is appropriate between 1/4 and 1/2, and Lt/L=1/3 is recommendation.
Hole jet angle α：Cooling hole has certain jet angle in arrangement, and hole is arranged in pressure face or suction surface spray
The size of firing angle is variant, and the jet angle in generally cylindrical hole is between 20 and 80 degree, and the jet angle of cooling hole of the present invention is in 30 Hes
It is applicable between 70 degree.
Lateral magnification angle γ：Lateral magnification angle is bigger, then the width of cooling hole exits is bigger.But due to depositing for expansion flowing
Excessive lateral magnification angle is likely to result in flow separation in hole, therefore maximum extension angle value is advisable in γ=14 degree, is
Acquisition lateral magnification effect, minimum angle of flare value are advisable in γ=8 degree.
Transverse holes interval S：Since cooling hole sectional area of the invention is shuttle shape, and length and width are bigger, while having cross
To the angle of flare, therefore cooling hole exits transverse width is significantly greater than common cylinder hole and the improvement based on common cylinder hole
Type expanded bore, therefore using cylinder aperture as reference when using, S/D should be not less than 5.
The ratio of width to height (W/H) in shuttle shape section：In order to which the cross-sectional area with common cylinder hole is of equal value, or keep the matter of single hole
It measures flow to approach, the shuttle shape sectional area of cooling hole provided by the invention requires equal with the circular cross-section of cylindrical hole product.According to figure
The ratio W/H of the experimental result that 5a-5c is provided, cooling hole cross-sectional width W of the invention and height H are relatively closed between 3 and 5
It is suitable.
Basis rectangle height h：Basis rectangle is the two sidewalls in order to construct fusiform cross-sectional, and it is transversal that width is equal to shuttle shape
The width in face, height determine the circular radius of side wall.Under conditions of guaranteeing that flat segments cross-sectional area is constant, h is smaller,
Then mean that cross section two sides scale is smaller, medium scale is bigger.H is bigger, then fusiform cross-sectional is more intended to rectangle.
Upstream and downstream wall evagination dimension, lambda 1 and λ 2：The size of the two parameter values influences greatly cooling effect, and this
The key parameter of invention pass.Due to requiring the cross-sectional area in the shuttle shape section of cooling hole of the present invention and the circle in common cylinder hole
Shape cross-sectional area is consistent, therefore the value of λ 1 and λ 2 are bigger, then h value is smaller.To the fusiform cross-sectional of different in width, λ 1 and λ's 2
Value is variant.When shuttle shape width W is smaller, such as W<When 1.7D, cold air is easy to focus on hole two sides, λ 1 desirable 0 to 0.05D it
Between value, while λ 2 takes the value between 0.05D and 0.2D, can suitably increase the air conditioning quantity at centerline hole configured in this way, closes
Suitable 2 value of λ can obtain highly uniform film overcast.When shuttle shape width W is larger, such as W > 1.7D, cold air is mainly focused on
Centerline hole, λ 1 take 0.05 to the value between 0.15D, can increase the air conditioning quantity of hole two sides in various degree, while λ 2 can take
Value between 0.05D-0.15D.
Cross circular section arc radius R1, R2 and R3：These parameters are related with the value of λ 1 and λ 2, also related with shuttle shape width,
It is the parameter for constructing fusiform cross-sectional.
Particular embodiments described above has carried out further in detail the purpose of the present invention, technical scheme and beneficial effects
Describe in detail bright, it should be understood that the above is only a specific embodiment of the present invention, is not intended to restrict the invention, it is all
Within the spirit and principles in the present invention, any modification, equivalent substitution, improvement and etc. done should be included in protection of the invention
Within the scope of.
Claims (4)
1. a kind of discrete gaseous film control pore structure, multiple cooling holes including discrete distribution, for cooling gas from described cold
But hole flows out to form air film, which is characterized in that the cooling hole includes flat segments and expansion segment, the flat segments along its axis direction
Positioned at cold air side, the expansion segment is located at high-temperature fuel gas side；The cross section of the flat segments is in shuttle shape, and the shuttle shape is both ends
Shape small, broad in the middle, is made of four arcs, the corresponding circle of circular arc of the upstream and downstream wall of the cross section of the flat segments and its
The circular arc of two side walls is tangent, and the width of the cross section of the flat segments and the ratio of height are between 3 and 5；The expansion segment
It is that lateral magnification based on the circular arc of the two sidewalls of the cross section of flat segments is formed；The expansion segment two sides lateral magnification shape
At the angle of flare, the angle of flare is between 8 degree and 14 degree；The ratio of the length of the flat segments and the cooling hole total length exists
Between 0.25 and 0.5；The applicable injection angular region of the cooling hole is between 30 degree and 70 degree；The applicable transverse direction of the cooling hole
The ratio of pitch of holes and cylinder bore diameter is not less than 5；The applicable air blowing ratio of the cooling hole is between 0.5-2.5；The cylinder
The cross-sectional area in hole is equal with the cross-sectional area of the flat segments.
2. discrete gaseous film control pore structure according to claim 1, which is characterized in that the height of the cross section of the flat segments
The ratio of degree and cylinder bore diameter is between 0.4 and 0.6.
3. discrete gaseous film control pore structure according to claim 1, which is characterized in that the cross section of the flat segments it is upper
The evagination height of wall and the ratio of cylinder bore diameter are swum between 0.05 and 0.2.
4. discrete gaseous film control pore structure according to claim 1, which is characterized in that under the cross section of the flat segments
The evagination height of wall and the ratio of cylinder bore diameter are swum between 0.0 and 0.15.
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| US10822958B2 (en) | 2019-01-16 | 2020-11-03 | General Electric Company | Component for a turbine engine with a cooling hole |
| 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 |
| CN112682105B (en) * | 2020-12-20 | 2022-11-11 | 中国航发四川燃气涡轮研究院 | Turbine blade structure with special-shaped micro-group air film cooling holes, preparation method of turbine blade structure and gas turbine |
| CN112682106B (en) * | 2020-12-20 | 2022-11-11 | 中国航发四川燃气涡轮研究院 | Turbine blade end wall structure with special-shaped micro-group air film cooling holes, method and gas turbine |
| CN112682108B (en) * | 2020-12-20 | 2023-07-25 | 中国航发四川燃气涡轮研究院 | Turbine blade end wall structure with D-shaped micro-group air film cooling holes, method thereof and gas turbine |
| 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 |
| CN113356932B (en) * | 2021-07-07 | 2023-04-28 | 西安交通大学 | Air film cooling composite hole structure for turbine blade and turbine blade |
| CN113623015A (en) * | 2021-08-17 | 2021-11-09 | 清华大学 | Sectional type air film cooling hole and design method thereof |
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| EP1967696A1 (en) * | 2005-11-01 | 2008-09-10 | IHI Corporation | Turbine part |
| US8245519B1 (en) * | 2008-11-25 | 2012-08-21 | Florida Turbine Technologies, Inc. | Laser shaped film cooling hole |
| CN104747242A (en) * | 2015-03-12 | 2015-07-01 | 中国科学院工程热物理研究所 | Straggling air film cooling hole |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1967696A1 (en) * | 2005-11-01 | 2008-09-10 | IHI Corporation | Turbine part |
| US8245519B1 (en) * | 2008-11-25 | 2012-08-21 | Florida Turbine Technologies, Inc. | Laser shaped film cooling hole |
| CN104747242A (en) * | 2015-03-12 | 2015-07-01 | 中国科学院工程热物理研究所 | Straggling air film cooling hole |
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