CN114856715B - Boss and pit combined type blade air film cooling hole structure - Google Patents
Boss and pit combined type blade air film cooling hole structure Download PDFInfo
- Publication number
- CN114856715B CN114856715B CN202210511753.3A CN202210511753A CN114856715B CN 114856715 B CN114856715 B CN 114856715B CN 202210511753 A CN202210511753 A CN 202210511753A CN 114856715 B CN114856715 B CN 114856715B
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- boss
- pit
- section
- cylindrical hole
- edge surface
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- 238000001816 cooling Methods 0.000 title claims abstract description 63
- 230000007704 transition Effects 0.000 claims abstract description 7
- 102000001999 Transcription Factor Pit-1 Human genes 0.000 description 22
- 108010040742 Transcription Factor Pit-1 Proteins 0.000 description 22
- 239000007789 gas Substances 0.000 description 10
- 238000000034 method Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A boss and pit combined type blade air film cooling hole structure comprises a boss, pits, cylindrical holes and wall surfaces; the boss, the pit and the cylindrical hole are all arranged in the wall surface, and the central lines of the boss, the pit and the cylindrical hole are positioned in the same plane; the cylindrical hole is communicated with the pit, and an orifice at the end of the cylinder Kong Chuqi is positioned on the bottom surface of the pit; the boss is arranged in the pit, and an orifice at the end of the cylinder Kong Chuqi is opposite to the boss; the height of the boss is the same as the depth of the pit; the whole boss is crescent, and the orifice at the end of the cylinder Kong Chuqi is opposite to the front edge surface of the boss; the cross section of the front edge surface of the boss is semi-elliptical, the cross section of the rear edge surface of the boss is semi-circular, and the joint transition surface of the front edge surface and the rear edge surface of the boss is a plane; the section of the front section surface of the pit is semi-elliptic and is connected with the vent end orifice of the cylindrical hole, the section of the middle section surface of the pit is gradually expanded, and the section of the rear section surface of the pit is square. The invention can increase the transverse coverage of the cooling air film and inhibit the lifting of the cooling air flow.
Description
Technical Field
The invention belongs to the technical field of cooling of blades of gas turbines and aeroengines, and particularly relates to a boss and pit combined type blade air film cooling hole structure.
Background
In order to further increase the output power and the cycle efficiency of gas turbines and aeroengines, it is common practice to continuously increase the turbine inlet temperature, however, the gas turbine and aeroengine turbine inlet temperatures are already far above the allowable temperatures of the high temperature component materials, so in order to ensure the operational safety and economy of the high temperature components of gas turbines and aeroengines, efficient cooling techniques must be designed.
Existing cooling techniques mainly include divergent cooling, impingement cooling, and film cooling. The air film cooling is a cooling technology for isolating the wall surface of the hot end part from the high-temperature main flow by using a cooling air film, the cooling air flow flows out of cooling holes in the wall surface of the blade, and the cooling air film is formed on the high-temperature wall surface, so that the high-temperature part is protected from being ablated by high-temperature gas. In addition, the film cooling efficiency is used as an important index for evaluating the film cooling performance, and only if the film cooling efficiency is higher, the smaller the amount of cold air required under the same cooling condition can be ensured, so that on one hand, the consumption of cold air can be reduced, and on the other hand, the blending of the cold air and the main flow can be reduced, so that the pneumatic and thermal efficiency loss of a turbine can be reduced.
At present, the gas film cooling technology applied to gas turbines and aeroengines still widely adopts cylindrical holes as cooling holes, and although the cylindrical holes have the characteristics of simple processing and easy engineering application, the cooling gas film formed by the cylindrical holes is narrower in coverage area, and poor in spanwise coverage, particularly under high blowing ratio, the gas film can be separated from the wall surface, so that the gas film cooling efficiency is drastically reduced.
Therefore, in order to increase the coverage and cooling efficiency of the cooling film, a variety of different cooling hole structures, such as sister cooling holes, fan-shaped holes, slots, etc., have been proposed in the industry. However, these different cooling hole structures have limited lateral (perpendicular to the flow direction) expansion of the cooling film, and cannot effectively control the interaction between the main flow and the cooling flow, and cannot effectively suppress the lifting of the cooling flow.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the boss and pit combined type blade air film cooling hole structure which can effectively increase the transverse coverage of a cooling air film, form effective air film cooling coverage and effectively inhibit the lifting of cooling air flow.
In order to achieve the above purpose, the present invention adopts the following technical scheme: a boss and pit combined type blade air film cooling hole structure comprises a boss, pits, cylindrical holes and wall surfaces; the boss, the pit and the cylindrical hole are all arranged in the wall surface; the cylindrical hole is communicated with the pit, and an outlet end orifice of the cylindrical hole is positioned on the pit bottom surface of the pit; the boss is arranged in the pit, and the orifice of the air outlet end of the cylindrical hole is opposite to the boss.
The center lines of the boss, the pits and the cylindrical holes are positioned in the same plane.
The height of the boss is the same as the depth of the pit.
The whole boss is crescent, the exit end drill way of cylinder hole is just right with the leading edge surface of boss.
The cross section of the front edge surface of the boss is semi-elliptical, the cross section of the rear edge surface of the boss is semi-circular, and the joint transition surface of the front edge surface and the rear edge surface of the boss is a plane.
The cross section of the front section surface of the pit is semi-elliptical and is connected with the vent end orifice of the cylindrical hole, the cross section of the middle section surface of the pit is gradually expanded, and the cross section of the rear section surface of the pit is square.
The ratio of the diameter to the length of the cylindrical hole is 1 (1-10).
The included angle between the central line of the cylindrical hole and the main flow direction is 10-40 degrees.
The invention has the beneficial effects that:
the boss and pit combined blade air film cooling hole structure can effectively increase the transverse coverage of a cooling air film, form effective air film cooling coverage and effectively inhibit lifting of cooling air flow.
Drawings
FIG. 1 is a perspective view of a boss and pit combined vane film cooling hole structure of the present invention;
FIG. 2 is a top view of a boss and pit combined vane film cooling hole structure of the present invention;
FIG. 3 is a side cross-sectional view of a boss and pit combined vane film cooling hole structure of the present invention;
in the figure, 1-boss, 2-pit, 3-cylindrical hole and 4-wall.
Detailed Description
The invention will now be described in further detail with reference to the drawings and to specific examples.
As shown in fig. 1-3, a boss and pit combined type blade air film cooling hole structure comprises a boss 1, pits 2, a cylindrical hole 3 and a wall surface 4; the boss 1, the pit 2 and the cylindrical hole 3 are all arranged in the wall surface 4; the cylindrical hole 3 is communicated with the pit 2, and an outlet end orifice of the cylindrical hole 3 is positioned on the pit bottom surface of the pit 2; the boss 1 is arranged in the pit 2, and the vent hole opening of the cylindrical hole 3 is opposite to the boss 1.
The center lines of the boss 1, the pit 2 and the cylindrical hole 3 are positioned in the same plane.
The height of the boss 1 is the same as the depth of the pit 2.
The whole boss 1 is crescent, and the vent end orifice of the cylindrical hole 3 is opposite to the front edge surface of the boss 1.
The cross section of the front edge surface of the boss 1 is semi-elliptical, the cross section of the rear edge surface of the boss 1 is semi-circular, and the joint transition surface of the front edge surface and the rear edge surface of the boss 1 is a plane.
The cross section of the front section surface of the pit 2 is semi-elliptical and is connected with the vent end orifice of the cylindrical hole 3, the cross section of the middle section surface of the pit 2 is gradually expanded, and the cross section of the rear section surface of the pit 2 is square.
The ratio of the diameter to the length of the cylindrical hole 3 is 1 (1-10).
The included angle between the central line of the cylindrical hole 3 and the main flow direction is 10-40 degrees.
As shown in fig. 2 and 3, P is the width of the spanwise boundary of the boss and pit combined type vane air film cooling hole structure, S is the vertical distance between the rear edge point of the outlet end orifice of the cylindrical hole 3 and the front edge surface of the boss 1, M is the spanwise width of the pit 2, C is the vertical distance between the joint transition surface of the front and rear edge surfaces of the boss 1 and the rear end surface of the pit 2, D is the vertical distance between the spanwise boundary of the rear section of the pit 2 and the spanwise boundary of the boss and pit combined type vane air film cooling hole structure, D is the diameter of the cylindrical hole 3, L is the length of the cylindrical hole 3, and H is the depth of the pit 2.
In the embodiment, the width P of the spanwise boundary of the boss and pit combined type blade air film cooling hole structure is 16mm; the diameter D of the cylindrical hole 3 is 4mm; the length L of the cylindrical hole 3 is 12mm; the vertical distance S between the rear edge point of the vent hole opening of the cylindrical hole 3 and the front edge surface of the boss 1 is 0.5D, and S is 2mm; the included angle between the central line of the cylindrical hole 3 and the main flow direction is 30 degrees; the semi-elliptic long half axis of the front edge surface of the boss 1 is 1.5D, and then is 6mm; the semi-elliptic minor semi-axis of the front edge surface of the boss 1 is D, and is 4mm; the semicircular radius of the rear edge surface of the boss 1 is 0.875D, and then the radius is 3.5mm; the spanwise width of the joint transition surface of the front edge surface and the rear edge surface of the boss 1 is 0.125D, and then the spanwise width is 0.5mm; the vertical distance C between the joint transition surface of the front edge surface and the rear edge surface of the boss 1 and the rear end surface of the pit 2 is 0.5D, and then C is 2mm; the depth H of the pit 2 is 1.5D, and H is 6mm; the width M of the pit 2 in the spreading direction is 3.5D, and M is 14mm; and D is 1mm when the vertical distance D between the spreading boundary of the rear section of the pit 2 and the spreading boundary of the combined type blade air film cooling hole structure of the boss and the pit is 0.25D.
When only the boss 1 is provided, although the spanwise coverage of the air film is also improved, the spanwise cooling efficiency is not effectively improved in the middle region between the cylindrical hole 3 and the boss 1; when only the pit 2 is provided, the film cooling efficiency inside the pit 2 is good, but the spanwise film cooling efficiency outside the pit 2 is not good. Therefore, after the boss 1 and the pit 2 are combined, the lifting of the cooling air flow is effectively restrained, and the spreading coverage of the cooling air film is effectively increased. In addition, pit 2 in cylinder hole 3 gas outlet end drill way department can make the cooling flow take place the secondary expansion, reduces the momentum of cooling flow, and boss 1 can shunt the cooling air current to both sides simultaneously, and then can produce favourable vortex, further presses down the lifting of cooling air film, compares with traditional cooling technique, under the same condition of cooling flow, can play the cooling effect to the wall of bigger area.
The embodiments are not intended to limit the scope of the invention, but rather are intended to cover all equivalent implementations or modifications that can be made without departing from the scope of the invention.
Claims (1)
1. A boss and pit combined type blade air film cooling hole structure is characterized in that: comprises a boss, a pit, a cylindrical hole and a wall surface; the boss, the pit and the cylindrical hole are all arranged in the wall surface; the cylindrical hole is communicated with the pit, and an outlet end orifice of the cylindrical hole is positioned on the pit bottom surface of the pit; the boss is arranged in the pit, and the boss is not contacted with the wall surface of the pit; the vent hole opening of the cylindrical hole is opposite to the boss; the central lines of the boss, the pits and the cylindrical holes are positioned in the same plane; the height of the boss is the same as the depth of the pit; the whole boss is crescent, and the vent hole opening of the air outlet end of the cylindrical hole is opposite to the front edge surface of the boss; the cross section of the front edge surface of the boss is semi-elliptical, the cross section of the rear edge surface of the boss is semi-circular, and the joint transition surface of the front edge surface and the rear edge surface of the boss is a plane; the section of the front section surface of the pit is semi-elliptical and is connected with the vent end orifice of the cylindrical hole, the section of the middle section surface of the pit is gradually expanded, and the section of the rear section surface of the pit is square; the ratio of the diameter to the length of the cylindrical hole is 1 (1-10); the included angle between the central line of the cylindrical hole and the main flow direction is 10-40 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210511753.3A CN114856715B (en) | 2022-05-12 | 2022-05-12 | Boss and pit combined type blade air film cooling hole structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210511753.3A CN114856715B (en) | 2022-05-12 | 2022-05-12 | Boss and pit combined type blade air film cooling hole structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114856715A CN114856715A (en) | 2022-08-05 |
| CN114856715B true CN114856715B (en) | 2024-05-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210511753.3A Active CN114856715B (en) | 2022-05-12 | 2022-05-12 | Boss and pit combined type blade air film cooling hole structure |
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| Country | Link |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102140964A (en) * | 2010-02-03 | 2011-08-03 | 中国科学院工程热物理研究所 | Structure for improving cooling efficiency of gas film of discrete hole |
| EP2666964A2 (en) * | 2012-05-22 | 2013-11-27 | Honeywell International, Inc. | Gas turbine engine blades with cooling hole trenches |
| CN105298649A (en) * | 2015-11-20 | 2016-02-03 | 清华大学 | Gas film cooling hole structure used for thin-walled hot end part of gas turbine engine |
| CN205225342U (en) * | 2015-12-24 | 2016-05-11 | 河北工业大学 | Improve upper reaches structure of subassembly external cooling effect |
| CN207245863U (en) * | 2017-08-30 | 2018-04-17 | 河北工业大学 | A kind of new construction for improving cooling effect |
| CN112031877A (en) * | 2020-08-21 | 2020-12-04 | 天津理工大学 | Expanding-direction asymmetric pit air film cooling hole pattern |
| CN112282857A (en) * | 2020-10-26 | 2021-01-29 | 上海交通大学 | Air film cooling hole type structure |
| CN213478402U (en) * | 2020-10-12 | 2021-06-18 | 青岛科技大学 | Novel slotting structure for improving cooling efficiency of turbine blade air film |
-
2022
- 2022-05-12 CN CN202210511753.3A patent/CN114856715B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102140964A (en) * | 2010-02-03 | 2011-08-03 | 中国科学院工程热物理研究所 | Structure for improving cooling efficiency of gas film of discrete hole |
| EP2666964A2 (en) * | 2012-05-22 | 2013-11-27 | Honeywell International, Inc. | Gas turbine engine blades with cooling hole trenches |
| CN105298649A (en) * | 2015-11-20 | 2016-02-03 | 清华大学 | Gas film cooling hole structure used for thin-walled hot end part of gas turbine engine |
| CN205225342U (en) * | 2015-12-24 | 2016-05-11 | 河北工业大学 | Improve upper reaches structure of subassembly external cooling effect |
| CN207245863U (en) * | 2017-08-30 | 2018-04-17 | 河北工业大学 | A kind of new construction for improving cooling effect |
| CN112031877A (en) * | 2020-08-21 | 2020-12-04 | 天津理工大学 | Expanding-direction asymmetric pit air film cooling hole pattern |
| CN213478402U (en) * | 2020-10-12 | 2021-06-18 | 青岛科技大学 | Novel slotting structure for improving cooling efficiency of turbine blade air film |
| CN112282857A (en) * | 2020-10-26 | 2021-01-29 | 上海交通大学 | Air film cooling hole type structure |
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| Publication number | Publication date |
|---|---|
| CN114856715A (en) | 2022-08-05 |
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