CN113266428A - Staggered hole plate rotary piston cooling structure for aero-engine - Google Patents
Staggered hole plate rotary piston cooling structure for aero-engine Download PDFInfo
- Publication number
- CN113266428A CN113266428A CN202110717539.9A CN202110717539A CN113266428A CN 113266428 A CN113266428 A CN 113266428A CN 202110717539 A CN202110717539 A CN 202110717539A CN 113266428 A CN113266428 A CN 113266428A
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- rotary piston
- inclined hole
- combustion chamber
- mounting groove
- piston
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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
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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
- F01D5/141—Shape, i.e. outer, aerodynamic form
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
Abstract
The invention discloses a staggered pore plate rotary piston cooling structure for an aircraft engine, which comprises a plurality of staggered pore plate rotary piston cooling structures uniformly distributed on a flame cylinder wall of a combustion chamber, wherein the upper side of the flame cylinder wall of the combustion chamber is a cold flow side, and the lower side of the flame cylinder wall of the combustion chamber is a hot flow side, wherein: set up the mounting groove that link up from top to bottom on the combustion chamber flame section of thick bamboo wall, install rotary piston in the mounting groove, rotary piston is spacing in the mounting groove, and can be rotatory in the mounting groove, surface mounting flabellum on the rotary piston, the flabellum drives rotary piston and rotates under the cold flow effect of combustion chamber flame section of thick bamboo wall upside, the inclined hole runner that runs through from top to bottom is seted up on the rotary piston, inclined hole runner slope sets up, make the cold flow that gets into the hot stream side through the inclined hole runner paste wall under the combustion chamber flame section of thick bamboo wall, and simultaneously, because rotary piston's rotation, make the cold flow that gets into the hot stream side through the inclined hole runner evenly distribute all around to the inclined hole runner. The invention can greatly improve the cooling efficiency around the lower surface hole of the orifice plate and avoid the waste of cold air.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a staggered pore plate rotary piston cooling structure for an aeroengine.
Background
With the continuous development of aero-engines and gas turbines, the thrust-weight ratio of the aero-engines and the gas turbines is required to be improved continuously, and the pressure increase ratio of a gas compressor and the temperature of gas at the inlet of the turbine are also improved continuously in order to improve the cycle efficiency of the aero-engines and the gas turbines. At present, the boost ratio of an engine compressor with a thrust-weight ratio of 10 reaches 30, the temperature of gas at the inlet of a turbine is close to 2000K and exceeds the temperature resistance limit of aviation materials. The development of aviation materials is difficult to keep up with the increase of required temperature, so that higher requirements are put on the cooling of the flame tube wall and the turbine blade of the combustion chamber, particularly in the main combustion hole of the combustion chamber, the downward covering of a gas film is not long, and the hole plate is also short, so the development of an efficient cooling technology becomes one of the research hot problems in the aviation field. Film cooling is the main cooling measure for high-temperature parts of gas turbine engines, and the main principle is to introduce a stream of secondary fluid with lower temperature through gaps or holes at a certain angle to isolate the main stream of high temperature from the wall surface, thereby protecting the downstream surface of the injection site. Compared with internal cooling (such as jet flow impact, rib wall channels, turbulence columns and the like), the improvement of the air film jet flow cooling capacity has more obvious significance for improving the overall cooling effect of the cooling structure.
The staggered multi-inclined-hole cooling is a common cooling technology in film cooling. The circular hole air film jet flow is mainly established on the basis of a flat plate model, kidney-shaped vortex pairs can be formed at the downstream of a hole by the traditional circular hole air film jet flow, and the mixing of cold air and hot air is aggravated to cause the reduction of cooling performance. And when the blowing rate is higher, the downstream cannot stabilize the air film coverage because of jet flow wall separation, and in addition, the uniform cooling effect is difficult to achieve in the circumferential direction. And the air inlet quantity of the cold air is difficult to control, thus easily causing the waste of the cold air with an excessively large air inlet ratio and the poor cooling effect with an excessively small air inlet ratio.
Disclosure of Invention
The invention aims to solve the problems mentioned in the background technology and provides a staggered orifice plate rotary piston cooling structure for an aeroengine.
In order to achieve the technical purpose, the technical scheme adopted by the invention is as follows:
the utility model provides an aeroengine is with rotatory piston cooling structure of staggered floor board, sets up at combustion chamber flame section of thick bamboo wall including the equipartition, and the upside of combustion chamber flame section of thick bamboo wall is the cold flow side, and the downside is the heat flow side, wherein: set up the mounting groove that link up from top to bottom on the combustion chamber flame section of thick bamboo wall, install rotary piston in the mounting groove, rotary piston is spacing in the mounting groove, and can be rotatory in the mounting groove, surface mounting flabellum on the rotary piston, the flabellum drives rotary piston and rotates under the cold flow effect of combustion chamber flame section of thick bamboo wall upside, the inclined hole runner that runs through from top to bottom is seted up on the rotary piston, inclined hole runner slope sets up, make the cold flow that gets into the hot stream side through the inclined hole runner paste wall under the combustion chamber flame section of thick bamboo wall, and simultaneously, because rotary piston's rotation, make the cold flow that gets into the hot stream side through the inclined hole runner evenly distribute all around to the inclined hole runner.
In order to optimize the technical scheme, the specific measures adopted further comprise:
the upside of foretell mounting groove still is provided with the restriction groove, and the apron is lapped to the internal energy fixed mounting of restriction groove, and when apron contact rotary piston upper surface, apron and rotary piston friction fit reduce rotary piston rotational speed to reduce the noise that the flabellum caused.
The wall of the limiting groove is provided with threads, corresponding thread bodies are arranged on the periphery of the cover plate, and the cover plate is fixedly arranged in the limiting groove through the threads and is adjusted to be in distance with the rotary piston through the threads.
The width of the gap between the rotary piston and the side wall of the mounting groove is 3% -5% of the diameter of the circular surface of the rotary piston.
The mounting groove is of a double-step trapezoidal groove structure, wherein the diameter of the upper-layer step is larger than that of the lower-layer step, the corresponding rotary piston consists of an upper piston body and a lower piston body, the diameter of the upper piston body is larger than that of the lower piston body, an upper end opening of the inclined hole flow channel is formed in the upper surface of the upper piston body, and a lower end opening of the inclined hole flow channel is formed in the lower surface of the lower piston body.
Clearance fit between foretell upper portion piston body lower surface and the lower surface of upper ladder has seted up circumference drainage hole on the piston body of upper portion, circumference drainage hole one end and inclined hole runner intercommunication, and the other end is seted up on the global of upper portion piston body for during the cold flow in the inclined hole runner can get into the clearance between rotary piston and the mounting groove through circumference drainage hole, hold up rotary piston.
And a non-top conical flow passage with a narrow upper part and a wide lower part is arranged on the lower side of the flame cylinder wall of the combustion chamber along the mounting groove, and cold flow flowing out of the inclined hole flow passage enters the hot flow side of the flame cylinder wall of the combustion chamber through the non-top conical flow passage.
The number of the circumferential drainage holes is four, and the circumferential drainage holes are arranged on the upper piston body at equal intervals.
The novel multi-inclined-hole-plate ellipsoidal pendulum cooling structure has the following advantages:
1. according to the invention, the rotary piston is innovatively arranged on the flame cylinder wall of the combustion chamber, the fan blades and the inclined hole flow passages are arranged on the rotary piston, and the fan blades are used for driving the rotary piston to rotate, so that the outlet angle of the inclined hole flow passages is constantly changed, cold flow entering the hot flow side through the inclined hole flow passages is uniformly distributed to the periphery of the inclined hole flow passages, the cooling efficiency of the periphery of the holes on the lower surface of the orifice plate is greatly improved, and cold air waste is avoided.
2. The rotary piston structure can automatically adjust the rotating speed according to different blowing ratios, and cold air is dispersed to the area which cannot be cooled by the traditional air film cooling, so that the cold air coverage area is increased.
3. The threaded cover plate structure ensures that the rotary piston cannot swing randomly due to fluctuation of cold air quantity, and the cooling effect and the noise generation condition can be controlled according to different screwing-in depth degrees of the threaded cover plate.
4. The inner wall of the upper part runner of the piston is communicated with four drainage holes which are vertical to each other and are arranged in the circumferential direction, a small part of air flow is led to the lower ladder layer and is filled with the whole mounting groove, and the rotary piston is floated, so that the rotary resistance is reduced. The rotating speed of the rotary piston can be automatically adjusted along with the change of the cold air quantity along the way, and the air outlet rotating speed of the cold air of the inclined hole flow channel is correspondingly adjusted, so that the self-adaptive drainage system without external energy supply is formed.
5. A non-top conical flow passage is formed at the lower part of the rotary piston and the lower surface of the pore plate along the flow passage, so that the loss of the air flow in the flowing process is reduced. A gap which accounts for 3 to 5 percent of the diameter of the circle is reserved between the stepped hole and the piston, so that gas in the flow channel can be ensured to be filled in the cavity through the small hole, the free rotation of the rotary piston is ensured, and the main flow is not influenced by the large-amount outflow from the gap.
Drawings
FIG. 1 is a schematic diagram of a conventional orifice plate cooling zone configuration;
FIG. 2 is a schematic view of the staggered orifice plate rotary piston cooling area configuration of the present invention;
FIG. 3 is a schematic view of an overall cooling structure of a conventional staggered multi-inclined hole plate;
FIG. 4 is a schematic view of a first example rotary piston configuration;
FIG. 5 is a schematic view of a second example rotary piston configuration;
FIG. 6 is a cross-sectional view of a first example rotary piston structure;
FIG. 7 is a cross-sectional view of a second example rotary piston structure;
FIG. 8 is a first example fan blade structure;
FIG. 9 is a second example fan blade structure;
FIG. 10 is a schematic view of the structure of the mounting groove;
FIG. 11 is a schematic view of the structure of the cover plate;
FIG. 12 is a perspective view one of the rotary piston;
fig. 13 is a second perspective view of the rotary piston.
The label names in the figure: the device comprises a flame tube wall 1 of a combustion chamber, a mounting groove 11, a limiting groove 12, a cover plate 13, a rotary piston 2, an upper piston body 2a, a lower piston body 2b, fan blades 21, an inclined hole flow passage 22, a circumferential drainage hole 23 and a non-tip conical flow passage 3.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings.
The rotatory piston cooling structure of staggered orifice plate for aeroengine of this embodiment sets up at combustion chamber flame section of thick bamboo wall 1 including the equipartition, and the upside of combustion chamber flame section of thick bamboo wall 1 is the cold flow side, and the downside is the heat flow side, wherein: the mounting groove 11 that link up from top to bottom has been seted up on combustion chamber flame section of thick bamboo wall 1, install rotary piston 2 in mounting groove 11, rotary piston 2 is spacing in mounting groove 11, and can be rotatory in mounting groove 11, surface mounting flabellum 21 on rotary piston 2, flabellum 21 is under the cold flow effect of combustion chamber flame section of thick bamboo wall 1 upside, drive rotary piston 2 and rotate, inclined hole runner 22 that runs through from top to bottom has been seted up on rotary piston 2, inclined hole runner 22 slope sets up, make the cold flow that gets into the hot flow side through inclined hole runner 22 paste in combustion chamber flame section of thick bamboo wall 1 wall face down, and simultaneously, because rotary piston 2's rotation, make the cold flow that gets into the hot flow side through inclined hole runner 22 evenly distribute all around to inclined hole runner 22.
In the embodiment, the upper side of the mounting groove 11 is further provided with a limiting groove 12, a cover plate 13 can be fixedly mounted in the limiting groove 12, and when the cover plate 13 contacts the upper surface of the rotary piston 2, the cover plate 13 is in friction fit with the rotary piston 2, so that the rotating speed of the rotary piston 2 is reduced, and the noise caused by the fan blades 21 is reduced.
In the embodiment, the wall of the limiting groove 12 is provided with a thread, the periphery of the cover plate 13 is provided with a corresponding thread body, and the cover plate 13 is fixedly installed in the limiting groove 12 through the thread and adjusts the distance between the cover plate and the rotary piston 2 through the thread.
In the embodiment, the width of the gap between the rotary piston 2 and the side wall of the mounting groove 11 is 3% -5% of the diameter of the circular surface of the rotary piston 2.
In the embodiment, the mounting groove 11 has a double step trapezoidal groove structure, wherein the diameter of the upper step is larger than that of the lower step, the corresponding rotary piston 2 is composed of an upper piston body 2a and a lower piston body 2b, the diameter of the upper piston body 2a is larger than that of the lower piston body 2b, the upper opening of the inclined hole flow passage 22 is opened on the upper surface of the upper piston body 2a, and the lower opening of the inclined hole flow passage 22 is opened on the lower surface of the lower piston body 2 b.
In the embodiment, the lower surface of the upper piston body 2a is in clearance fit with the lower surface of the upper step, the upper piston body 2a is provided with a circumferential drainage hole 23, one end of the circumferential drainage hole 23 is communicated with the inclined hole runner 22, and the other end of the circumferential drainage hole is arranged on the circumferential surface of the upper piston body 2a, so that cold flow in the inclined hole runner 22 can enter a clearance between the rotary piston 2 and the mounting groove 11 through the circumferential drainage hole 23 to lift the rotary piston 2.
In the embodiment, a non-top tapered flow passage 3 with a narrow top and a wide bottom is arranged on the lower side of the flame tube wall 1 of the combustion chamber along the mounting groove 11, and cold flow flowing out of the inclined hole flow passage 22 enters the hot flow side of the flame tube wall 1 of the combustion chamber through the non-top tapered flow passage 3.
In the embodiment, the number of the circumferential drainage holes 23 is four, and the circumferential drainage holes are arranged on the upper piston body 2a at equal intervals.
The wall surface of the invention is provided with three stages of stepped holes (the limiting groove 12 is in one stage, the two-stage stepped groove of the mounting groove 11 is in two stages) which are arranged in a staggered way, the height ratio of the stepped holes from top to bottom is 4:4:7, each stage of the stepped holes are round holes, and the hole diameter ratio is 15:11: 7. The reasonable arrangement of the threaded cover plate 13 and the rotary piston 2 can be ensured under the proportion, and the tip-free tapered runner 3 with the same direction as the inclined hole runner 22 is arranged below the rotary piston 2, so that the air flow is easier to distribute around the hole, and the air flow loss is reduced.
A threaded cover plate 13 is arranged on the first layer of stepped hole, the threaded cover plate 13 is connected with the inner wall of the stepped hole through fine threads, and the distance between the threaded cover plate 13 and the rotary piston 2 can be controlled by rotating the threaded cover plate 13. And the device has certain position self-locking performance due to the fine thread connection. When the cover plate 13 is located closer to the piston face, reducing the distance between the two increases resistance, impairs the rotational performance of the piston, thereby affecting the performance of cooling air, but can greatly reduce noise. On the other hand, when the distance between the two is large, the noise is large but the rotation performance is good and the cooling efficiency is high. The distance between the two devices can be adjusted according to the actual application scene, and the applicability of the device is improved. And secondly, the three layers of stepped holes are provided with rotary pistons 2, and a gap of 3% -5% of the diameter of the circular surface of each rotary piston 2 is kept between each rotary piston 2 and the inner surface of each stepped hole. The gap between the piston and the inner wall of the stepped hole is less than 3%, so that the drainage effect of the drainage hole is influenced, and the air flow cannot fill the cavity to lift the piston to rotate freely; above 5% increases the cold flow dissipation rate resulting in a decrease in both cooling range and cooling efficiency. The clearance between the two is comprehensively considered to be maintained at the best of 3-5% of the diameter of the circular hole. An inclined bore flow channel is arranged in the interior of the rotary piston 2, the bore diameter of which is approximately 1/4 times the diameter of the circle of the upper part of the piston. The inclined hole and the air inlet direction form a certain angle, and the angle coefficient can influence the flow coefficient of cold flow, so that the cold flow can be guided to better enter air, and meanwhile, the cold flow can easily form an adherent air film on the periphery of the lower wall surface. And the upper part of the piston is provided with circumferential drainage holes 23 which vertically penetrate through the inclined-hole flow passage 22, and the diameter of each circumferential drainage hole 23 is about 1/20 of that of the inclined-hole flow passage 22. The air flow is guided to the chamber through the circumferential drainage holes 23, the rotary piston 2 is pushed to float upwards, and friction loss during rotation is reduced. A tip-free conical flow passage 3 is formed in the lower portion of the rotary piston 2, air inlet loss is reduced, and a bending angle is formed in the other side of the air flow direction, so that cold flow mixing can be prevented to a certain degree. In the first example, the installed attached-surface fan blades 21 have six blades, the blades are uniformly distributed at 300 degrees in the circumferential direction, the opening position of the inclined-hole flow passage 22 is avoided, and the influence on air inlet is reduced to the minimum extent. The fan that example two was selected comprises an axis body and three circular arc blades, and three circular arc blades evenly arrange 360 degrees in axis body upper portion circumference and blade length is comparatively reasonable not influence admit air. The blades of the first example have wider windward area and larger effective contact area with the surface of the piston, so that the piston can be better driven to rotate, but the cold air loss caused by the blades is larger than that of the second example at the same time due to the large windward area. And example one has a small cooling loss although the performance of driving the piston to rotate is insufficient. The fan blade structures of the first and second examples have adaptive adjustment functions for decreasing the rotation speed along the way as the amount of cold air decreases. The first instance and the second instance can be selectively used according to specific use scenes.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may be made by those skilled in the art without departing from the principle of the invention.
Claims (8)
1. The utility model provides an aeroengine is with rotatory piston cooling structure of staggered floor board, sets up at combustion chamber flame section of thick bamboo wall (1) including the equipartition, the upside of combustion chamber flame section of thick bamboo wall (1) be the cold flow side, the downside is the heat flow side, characterized by: the flame tube wall (1) of the combustion chamber is provided with an installation groove (11) which is communicated up and down, a rotary piston (2) is arranged in the mounting groove (11), the rotary piston (2) is limited in the mounting groove (11), and can rotate in the mounting groove (11), the upper surface of the rotary piston (2) is provided with fan blades (21), the fan blades (21) drive the rotary piston (2) to rotate under the action of cold flow on the upper side of the flame cylinder wall (1) of the combustion chamber, an inclined hole runner (22) which penetrates through the rotary piston (2) up and down is arranged on the rotary piston, the inclined hole flow passage (22) is obliquely arranged, so that cold flow entering the hot flow side through the inclined hole flow passage (22) is attached to the lower wall surface of the flame cylinder wall (1) of the combustion chamber, and simultaneously, due to the rotation of the rotary piston (2), the cold flow entering the hot flow side through the inclined hole flow passage (22) is uniformly distributed around the inclined hole flow passage (22).
2. The alternate-row orifice plate rotary piston cooling structure for the aircraft engine as claimed in claim 1, wherein: the upside of mounting groove (11) still be provided with restriction tank (12), restriction tank (12) can fixed mounting apron (13), apron (13) when contacting rotary piston (2) upper surface, apron (13) and rotary piston (2) friction fit reduce rotary piston (2) rotational speed to reduce the noise that flabellum (21) caused.
3. The alternate-row orifice plate rotary piston cooling structure for the aircraft engine as claimed in claim 2, wherein: the groove wall of the limiting groove (12) is provided with threads, corresponding thread bodies are arranged on the periphery of the cover plate (13), and the cover plate (13) is fixedly arranged in the limiting groove (12) through the threads and is adjusted to be away from the rotary piston (2) through the threads.
4. The alternate-row orifice plate rotary piston cooling structure for the aircraft engine as claimed in claim 3, wherein: the width of a gap between the rotary piston (2) and the side wall of the mounting groove (11) is 3% -5% of the diameter of the circular surface of the rotary piston (2).
5. The alternate-row orifice plate rotary piston cooling structure for the aircraft engine as claimed in claim 4, wherein: the mounting groove (11) is of a double-step trapezoidal groove structure, wherein the diameter of the upper step is larger than that of the lower step, the corresponding rotary piston (2) consists of an upper piston body (2a) and a lower piston body (2b), the diameter of the upper piston body (2a) is larger than that of the lower piston body (2b), the upper end opening of the inclined hole flow channel (22) is formed in the upper surface of the upper piston body (2a), and the lower end opening of the inclined hole flow channel (22) is formed in the lower surface of the lower piston body (2 b).
6. The alternate-row orifice plate rotary piston cooling structure for the aircraft engine as claimed in claim 5, wherein: the lower surface of the upper piston body (2a) is in clearance fit with the lower surface of the upper ladder, a circumferential drainage hole (23) is formed in the upper piston body (2a), one end of the circumferential drainage hole (23) is communicated with the inclined hole flow channel (22), and the other end of the circumferential drainage hole is formed in the circumferential surface of the upper piston body (2a), so that cold flow in the inclined hole flow channel (22) can enter a gap between the rotary piston (2) and the mounting groove (11) through the circumferential drainage hole (23) to lift the rotary piston (2).
7. The alternate-row orifice plate rotary piston cooling structure for the aircraft engine as claimed in claim 6, wherein: and a non-top tapered flow channel (3) with a narrow top and a wide bottom is arranged on the lower side of the flame cylinder wall (1) of the combustion chamber along the mounting groove (11), and cold flow flowing out of the inclined hole flow channel (22) enters the hot flow side of the flame cylinder wall (1) of the combustion chamber through the non-top tapered flow channel (3).
8. The alternate-row orifice plate rotary piston cooling structure for an aircraft engine according to claim 7, characterized in that: the number of the circumferential drainage holes (23) is four, and the circumferential drainage holes are distributed on the upper piston body (2a) at equal intervals.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110717539.9A CN113266428B (en) | 2021-06-28 | 2021-06-28 | Staggered hole plate rotary piston cooling structure for aero-engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110717539.9A CN113266428B (en) | 2021-06-28 | 2021-06-28 | Staggered hole plate rotary piston cooling structure for aero-engine |
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| CN113266428A true CN113266428A (en) | 2021-08-17 |
| CN113266428B CN113266428B (en) | 2022-02-01 |
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| US20050042074A1 (en) * | 2002-09-05 | 2005-02-24 | Siemens Westinghouse Power Corporation | Combustion turbine with airfoil having multi-section diffusion cooling holes and methods of making same |
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| CN107143383A (en) * | 2017-07-18 | 2017-09-08 | 中国科学院工程热物理研究所 | A kind of turbine rotor blade pressure face and top compound angle air film hole layout structure |
| CN108138575A (en) * | 2015-10-22 | 2018-06-08 | 三菱日立电力系统株式会社 | The manufacturing method of blade, the gas turbine for having the blade and blade |
| CN111075510A (en) * | 2020-01-06 | 2020-04-28 | 大连理工大学 | Turbine blade honeycomb spiral cavity cooling structure |
| CN112761733A (en) * | 2021-01-08 | 2021-05-07 | 西安交通大学 | Cross air film cooling hole structure capable of inhibiting development of kidney-shaped vortex pairs and application thereof |
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2021
- 2021-06-28 CN CN202110717539.9A patent/CN113266428B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050042074A1 (en) * | 2002-09-05 | 2005-02-24 | Siemens Westinghouse Power Corporation | Combustion turbine with airfoil having multi-section diffusion cooling holes and methods of making same |
| CN104197373A (en) * | 2014-08-26 | 2014-12-10 | 南京航空航天大学 | Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used |
| CN108138575A (en) * | 2015-10-22 | 2018-06-08 | 三菱日立电力系统株式会社 | The manufacturing method of blade, the gas turbine for having the blade and blade |
| CN107143383A (en) * | 2017-07-18 | 2017-09-08 | 中国科学院工程热物理研究所 | A kind of turbine rotor blade pressure face and top compound angle air film hole layout structure |
| CN111075510A (en) * | 2020-01-06 | 2020-04-28 | 大连理工大学 | Turbine blade honeycomb spiral cavity cooling structure |
| CN112761733A (en) * | 2021-01-08 | 2021-05-07 | 西安交通大学 | Cross air film cooling hole structure capable of inhibiting development of kidney-shaped vortex pairs and application thereof |
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| CN113266428B (en) | 2022-02-01 |
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