CN113047912A - Laminate cooling structure with quincunx turbulence columns - Google Patents
Laminate cooling structure with quincunx turbulence columns Download PDFInfo
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- CN113047912A CN113047912A CN202110420526.5A CN202110420526A CN113047912A CN 113047912 A CN113047912 A CN 113047912A CN 202110420526 A CN202110420526 A CN 202110420526A CN 113047912 A CN113047912 A CN 113047912A
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- quincunx
- turbulence
- turbulence columns
- column
- holes
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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
- F01D5/187—Convection 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
- F01D5/18—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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a laminate cooling structure with quincunx turbulence columns, which comprises a laminate main body, wherein the laminate main body comprises an outer side plate and an inner side plate, a cooling channel is arranged between the outer side plate and the inner side plate, the quincunx turbulence columns are arranged in the cooling channel, the quincunx turbulence columns are arranged in a staggered manner, inclined air film holes are formed in the outer side plate, impact holes are formed in the inner side plate, and the air film holes and the impact holes are both connected with the cooling channel; the quincunx turbulence columns can reduce the flow resistance of gas, and cold air can form a better attached gas film behind the gas film holes and on the outer side of the outer side plate after flowing through the inclined gas film holes.
Description
Technical Field
The invention relates to the technical field of gas turbine cooling, in particular to a laminate cooling structure with a quincunx turbulence column.
Background
The pre-turbine temperature of turbocharged engines has currently reached 2000K and has increased year by year at an average rate of 20C per year. Far exceeds the temperature resistance of the existing metal material. In order to meet the temperature resistance requirements of turbine blades, cooling techniques are required to maximize cooling efficiency as much as possible. According to the working principle of the gas turbine, most of high pressure obtained by compressing air by the air compressor is used for participating in combustion reaction, and the generated heat energy pushes turbine blades to do work; a small portion of the gas is required to cool the high temperature components of the gas turbine by bleed air, and the more this portion of the gas is consumed, the less efficient the compressor. In order to ensure the efficient operation of the engine and the safe and reliable operation of the turbine, the development of an efficient turbine cooling technology with higher cooling efficiency and less cold air consumption is required. There have been many achievements in the technology of efficient turbine cooling, in which the laminar cooling technology provided with the turbulence columns is one of the effective measures for cooling the turbine blades.
The turbulator posts may be disposed at any location within the internal cooling passageway of the turbine blade. And is currently typically located at the trailing edge of the blade. The cooling gas flowing through the cooling channel increases the turbulence intensity thereof through the turbulence of the turbulence column, increases the heat exchange intensity with the wall surface of the laminate, and the turbulence column can also serve as a heat transfer element, so that the cooling efficiency of the laminate cooling technology is increased, and the shape of the turbulence column is an important factor influencing the cooling efficiency of the laminate. At present, the square turbulence columns which are researched more have better heat exchange strength, but have larger flow resistance; circular, elliptical, drop-shaped turbulence columns have a low coefficient of resistance, but their trade strength is limited.
Disclosure of Invention
The invention aims to solve the technical problems in the prior art and provides a laminate cooling structure with a quincunx turbulence column.
In order to achieve the purpose, the technical scheme provided by the invention is as follows: the utility model provides a take plywood cooling structure of plum blossom shape turbulence column, includes the plywood main part, the plywood main part includes outer panel and interior plate, be provided with cooling channel between outer panel and the interior plate, be provided with plum blossom shape turbulence column in the cooling channel, plum blossom shape turbulence column adopts the fork row to arrange, be provided with the air film hole of slope on the outer panel, be provided with on the interior plate and strike the hole, the air film hole with strike the hole all with cooling channel connects.
Preferably, the quincunx turbulence column is composed of four identical circles, two adjacent circles are connected by a section of circular arc, and the diameter d of the quincunx turbulence column is 0.5-1 mm.
Preferably, the radius r corresponding to the circular arc of the quincunx turbulence column is 0.1 mm-0.5 mm, and the included angle beta between the direction of the air flow in the cooling channel and the two adjacent circles is 30-60 degrees.
Preferably, the thickness H of the quincunx turbulence columns is 0.5-2 mm, the spanwise distance P of the quincunx turbulence columns is 4-8 mm, and the flow direction distance W of the quincunx turbulence columns is 3-6 mm.
Preferably, the diameter of the impact holes is 0.5-2 mm, the air film holes are distributed in a plurality of ways, adjacent air film holes are arranged in a staggered manner, and the distance L between two adjacent air inlet holes of the air film holes ranges from 10mm to 20 mm.
The invention has the beneficial effects that:
the quincunx turbulence columns are arranged in a staggered manner, so that the heat exchange area can be effectively increased, and the internal heat exchange is enhanced; the quincunx turbulence columns can reduce the flow resistance of gas, and cold air can form a better attached gas film behind the gas film holes and on the outer side of the outer side plate after flowing through the inclined gas film holes.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
FIG. 1 is a schematic view of the overall structure of the preferred embodiment of the present invention;
FIG. 2 is a side view of the overall structure of the preferred embodiment of the present invention;
FIG. 3 is a schematic plan view of a quincunx turbulence column in accordance with a preferred embodiment of the present invention;
fig. 4 is a top view of a quincunx turbulence column in accordance with a preferred embodiment of the present invention.
The attached drawings are marked as follows:
1-air film hole 2-quincunx turbulence column 3-impact hole 4-cooling channel 5-inner side plate 6-outer side plate.
Detailed Description
Reference will now be made in detail to the present preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.
In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.
Referring to fig. 1 to 4, in a preferred embodiment of the present invention, a laminate cooling structure with a quincunx turbulence column includes a laminate main body, the laminate main body includes an outer side plate 6 and an inner side plate 5, a cooling channel 4 is disposed between the outer side plate 6 and the inner side plate 5, a quincunx turbulence column 2 is disposed in the cooling channel 4, an inclined film hole 1 is disposed on the outer side plate 6, an impact hole 3 is disposed on the inner side plate 5, and both the film hole 1 and the impact hole 3 are connected to the cooling channel 4.
In this embodiment, air conditioning is through the impact hole 3 impact outer panel 6 earlier, the back gets into cooling channel 4 and the enhancement heat transfer of plum blossom shape turbulence column 2, air conditioning is because the pressure is less in the seam after the separation of plum blossom shape turbulence column 2 boundary layer before through, the drainage is carried out to air conditioning, air conditioning after the separation then need flow around next plum blossom shape turbulence column 2 again, air conditioning's utilization efficiency in cooling channel 4 improves, the refrigerated homogeneity of outer panel 6 has also been improved simultaneously, the gas after the vortex flows out along the gas film hole 1 of outer panel 6, air conditioning can form better attached gas film in gas film hole 1 rear and the outer panel outside after flowing through inclined gas film hole 1, play fine guard action to the blade.
The invention provides a laminate cooling structure with quincunx turbulence columns, wherein the quincunx turbulence columns 2 are arranged in the laminate cooling structure, and the quincunx turbulence columns 2 are arranged in a staggered manner. The laminate cooling structure with the quincunx turbulence columns 2 can effectively improve the heat exchange area and enhance the internal heat exchange; the quincunx turbulence columns 2 can reduce the flow resistance of gas, effectively improve the spread coverage area of cooling gas, and after cold gas flows through the inclined gas film holes 1, a better attached gas film can be formed behind the gas film holes 1 and outside the outer side plate 6.
As a preferred embodiment of the present invention, it may also have the following additional technical features:
in this embodiment, the quincunx turbulence column 2 is composed of four identical circles, two adjacent circles are connected by a section of circular arc, and the circular diameter d of the quincunx turbulence column 2 is 0.5 mm-1 mm.
In this embodiment, the radius r corresponding to the arc of the quincunx turbulence column 2 is 0.1mm to 0.5mm, and the included angle β between the direction of the air flow in the cooling channel 4 and the two adjacent circles is 30 ° to 60 °.
In the embodiment, the thickness H of the quincunx turbulence columns 2 is 0.5-2 mm, the span-wise distance P of the quincunx turbulence columns 2 is 4-8 mm, and the flow direction distance W of the quincunx turbulence columns 2 is 3-6 mm.
In the embodiment, the diameter of the impact holes 3 is 0.5-2 mm, the air film holes 1 are distributed in a plurality, the adjacent air film holes 1 are arranged in a staggered manner, and the range of the value of the distance L between the two adjacent air inlet holes of the air film holes 1 is 10-20 mm.
The working principle of the invention is as follows: cooling gas gets into the turbine blade inner chamber through compressor bleed air, and the cooling gas of inner chamber strikes the outer panel through impingement hole 3 on 5 inner plates, behind the 2 vortex of quincunx vortex column of cooling channel 4, increases gaseous turbulence intensity, and the vortex structure that forms can increase cooling gas's utilization ratio, then flows into the blade grid through film hole 1 in, forms the film cooling with 6 heat source mainstream air currents of outer panel.
The above additional technical features can be freely combined and used in superposition by those skilled in the art without conflict.
The above description is only a preferred embodiment of the present invention, and the technical solutions that achieve the objects of the present invention by basically the same means are all within the protection scope of the present invention.
Claims (5)
1. The utility model provides a take plywood cooling structure of plum blossom shape turbulence column which characterized in that: including the plywood main part, the plywood main part includes outer panel (6) and interior plate (5), be provided with cooling channel (4) between outer panel (6) and interior plate (5), be provided with plum blossom shape turbulence column (2) in cooling channel (4), plum blossom shape turbulence column (2) adopt the fork row to arrange, be provided with the air film hole (1) of slope on outer panel (6), be provided with on interior plate (5) and strike hole (3), air film hole (1) with strike hole (3) all with cooling channel (4) are connected.
2. The laminate cooling structure with quincunx turbulence columns as set forth in claim 1, wherein: the quincunx flow disturbing column (2) is composed of four identical circles, two adjacent circles are connected through a section of circular arc, and the diameter d of the quincunx flow disturbing column (2) is 0.5-1 mm.
3. The laminate cooling structure with quincunx turbulence columns as set forth in claim 2, wherein: the radius r corresponding to the circular arc of the quincunx turbulence column (2) is 0.1-0.5 mm, and the included angle beta between the direction of the air flow in the cooling channel (4) and the two adjacent circles is 30-60 degrees.
4. The laminate cooling structure with quincunx turbulence columns as set forth in claim 1, wherein: the thickness H of the quincunx turbulence columns (2) is 0.5-2 mm, the span-wise distance P of the quincunx turbulence columns (2) is 4-8 mm, and the flow-direction distance W of the quincunx turbulence columns (2) is 3-6 mm.
5. The laminate cooling structure with quincunx turbulence columns as set forth in claim 1, wherein: the diameter of the impact holes (3) is 0.5-2 mm, the air film holes (1) are distributed in a plurality of ways, the adjacent air film holes (1) are arranged in a staggered manner, and the distance L between the two adjacent air inlet holes of the air film holes (1) ranges from 10mm to 20 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110420526.5A CN113047912A (en) | 2021-04-19 | 2021-04-19 | Laminate cooling structure with quincunx turbulence columns |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110420526.5A CN113047912A (en) | 2021-04-19 | 2021-04-19 | Laminate cooling structure with quincunx turbulence columns |
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| CN113047912A true CN113047912A (en) | 2021-06-29 |
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| CN202110420526.5A Pending CN113047912A (en) | 2021-04-19 | 2021-04-19 | Laminate cooling structure with quincunx turbulence columns |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114109515A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Turbine blade suction surface cooling structure |
| CN114991880A (en) * | 2022-08-01 | 2022-09-02 | 中国航发沈阳发动机研究所 | Double-wall rotor blade of high-pressure turbine of aircraft engine |
| CN116950724A (en) * | 2023-09-20 | 2023-10-27 | 中国航发四川燃气涡轮研究院 | Internal cooling structure applied to turbine blade trailing edge and design method thereof |
-
2021
- 2021-04-19 CN CN202110420526.5A patent/CN113047912A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114109515A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Turbine blade suction surface cooling structure |
| CN114109515B (en) * | 2021-11-12 | 2024-01-30 | 中国航发沈阳发动机研究所 | Turbine blade suction side cooling structure |
| CN114991880A (en) * | 2022-08-01 | 2022-09-02 | 中国航发沈阳发动机研究所 | Double-wall rotor blade of high-pressure turbine of aircraft engine |
| CN116950724A (en) * | 2023-09-20 | 2023-10-27 | 中国航发四川燃气涡轮研究院 | Internal cooling structure applied to turbine blade trailing edge and design method thereof |
| CN116950724B (en) * | 2023-09-20 | 2024-01-09 | 中国航发四川燃气涡轮研究院 | Internal cooling structure applied to turbine blade trailing edge and design method thereof |
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