CN205297652U - Turbine cooling blade - Google Patents
Turbine cooling blade Download PDFInfo
- Publication number
- CN205297652U CN205297652U CN201521005473.7U CN201521005473U CN205297652U CN 205297652 U CN205297652 U CN 205297652U CN 201521005473 U CN201521005473 U CN 201521005473U CN 205297652 U CN205297652 U CN 205297652U
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- blade
- cooling
- cooling chamber
- turbulence columns
- chamber
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Abstract
The utility model relates to a turbine cooling blade, including blade main part and cooling chamber, be equipped with a plurality of baffles along blade radial array on the blade main part inner wall, one of them baffle will cool off the chamber and divide into first cooling chamber of mutually independent and second cooling chamber, and the cavity that becomes a plurality of mutual intercommunications is cut apart with first cooling chamber and second cooling chamber to all the other baffles, blade leading edge is last to be equipped with the air film hole of running through inside and outside a plurality of, still be equipped with a plurality of vortex posts on the blade main part inner wall, the terminal surface of vortex post is the ellipse, and oval -shaped major axis direction is unanimous with the flow direction of cooling blast. The utility model discloses a cooling chamber is divide into two cavitys of mutually independent by the baffle for cooling gas trailing edge position in the front all has higher heat exchange coefficient, is equipped with the vortex post of oval terminal surface simultaneously on the inner wall, can strengthen the heat transfer of cooling intracavity, and the orientation to cooling gas is met with less cross -section to the vortex post simultaneously, has reduced cooling gas's flow resistance, has improved cooling efficiency.
Description
Technical field
The utility model relates to a kind of turbine blade, particularly relates to a kind of turbine cooling blade.
Background technology
From the development course of engine turbine blade, the trend of material, technology and design integration is all the more obvious. Engine design develops to high level by low-level, and blade material design is also like this, and the design phase is different, and design requirements is different, and method of design is different, and the material of employing is not identical with manufacturing process yet. It is therefore necessary to continually develop new type high temperature material according to blade construction design requirements, expand blade selection range, ensure improving constantly of motor performance.
Advanced cooling technology can make hot-end component can bear higher working temperature, it is to increase the thermal efficiency of cycle of engine turbine, extends engine turbine work-ing life, it is to increase the safety and reliability of system works. It is estimated that, if the use temperature without cooling blade material can reach 1470K, when same blade material adopts internal convection to cool, turbine intake temperature can be made to bring up to 2200K. It thus is seen that the research tool carrying out technique for cooling blades is of great significance.
Practical novel content
The purpose of this utility model is to provide a kind of has better heat exchange property and the turbine cooling blade of less resistance to flow.
The technical scheme realizing the utility model object is: a kind of turbine cooling blade, comprises blade body and cooling chamber; Described blade body is by end face, blade inlet edge, blade trailing edge and extends to the pressure face part of blade trailing edge from blade inlet edge and surface part is formed; Described blade body inwall is provided with multiple dividing plate along blade radial arrangement, and cooling chamber is divided into the first separate cooling chamber by one of them dividing plate, and the first cooling chamber is partitioned into multiple cavity being interconnected by all the other dividing plates; Described blade inlet edge be provided with multiple inside and outside the air film hole that runs through; Described blade body inwall is also provided with multiple turbulence columns; The end face ovalize of described turbulence columns, oval long axis direction is consistent with the flow direction of cooling draught.
In described multiple dividing plate, the dividing plate nearest apart from blade inlet edge is provided with multiple impinging cooling hole.
One end of described turbulence columns is fixedly connected with blade body inwall, and the other end is unsettled end.
The slope structure that the end face of the unsettled end of described turbulence columns is low after being front height along the flow direction of cooling gas.
Described turbulence columns is crisscross arranged in the inwall both sides of blade body.
The utility model has positive effect: (1) cooling chamber of the present utility model is divided into separate two cavity by dividing plate, cooling gas is made all to have the higher coefficient of heat transfer in front and rear edge position, on inwall, it is provided with the turbulence columns of oval end face simultaneously, the heat exchange in cooling chamber can be strengthened, turbulence columns meets the direction to cooling gas with less cross section simultaneously, reduce the resistance to flow of cooling gas of knowing clearly, it is to increase cooling efficiency.
(2) in the utility model, the dividing plate nearest apart from blade inlet edge is provided with multiple impinging cooling hole, it is possible to blade inlet edge inwall is carried out impinging cooling, reduces the temperature of blade inlet edge further.
(3) slope structure that the end face of the unsettled end of turbulence columns of the present utility model is low after being front height along the flow direction of cooling gas, slope structure can produce wake's flow field, and strengthening is through the heat exchange effect of turbulence columns further.
(4) turbulence columns of the present utility model is crisscross arranged in the inwall both sides of blade body, and flow resistance loss is little, and flow-disturbing is effective.
Accompanying drawing explanation
In order to make content of the present utility model more easily be clearly understood, below according to specific embodiment and by reference to the accompanying drawings, the utility model is described in further detail, wherein
Fig. 1 is longitudinal cross-section figure of the present utility model.
Fig. 2 is view in transverse section of the present utility model.
Accompanying drawing is labeled as:
Blade body 1, end face 1-1, blade inlet edge 1-3, blade trailing edge 1-4, pressure face part 1-5, surface part 1-6, dividing plate 1-7, air film hole 1-8, turbulence columns 1-9, impinging cooling hole 1-10, cooling chamber 2, first cooling chamber 2-1.
Embodiment
(embodiment 1)
As depicted in figs. 1 and 2, the turbine cooling blade of the present embodiment, comprises blade body 1 and cooling chamber 2. Blade body 1 is made up of end face 1-1, blade inlet edge 1-3, blade trailing edge 1-4 and the pressure face part 1-5 and surface part 1-6 that extend to blade trailing edge 1-4 from blade inlet edge 1-3.
Blade inlet edge 1-3 be provided with multiple inside and outside the air film hole 1-8 that runs through. Blade body 1 inwall is provided with multiple dividing plate 1-7 along blade radial arrangement, cooling chamber 2 is divided into the first separate cooling chamber 2-1 by one of them dividing plate 1-7, first cooling chamber 2-1 is partitioned into multiple cavity being interconnected by all the other dividing plates 1-7, and the dividing plate nearest apart from blade inlet edge 1-3 is provided with multiple impinging cooling hole 1-10. Also being provided with multiple turbulence columns 1-9 on blade body 1 inwall, the end face ovalize of turbulence columns 1-9, oval long axis direction is consistent with the flow direction of cooling draught. One end of turbulence columns 1-9 is fixedly connected with blade body 1 inwall, and the other end is unsettled end, the slope structure that the end face of the unsettled end of turbulence columns 1-9 is low after being front height along the flow direction of cooling gas. Turbulence columns 1-9 is crisscross arranged in the inwall both sides of blade body 1.
Above-described specific embodiment; the purpose of this utility model, technical scheme and useful effect have been further described; it is it should be understood that; the foregoing is only specific embodiment of the utility model; it is not limited to the utility model; all within spirit of the present utility model and principle, any amendment of making, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (5)
1. a turbine cooling blade, comprises blade body (1) and cooling chamber (2); Described blade body (1) is by end face (1-1), blade inlet edge (1-3), blade trailing edge (1-4) and extends to the pressure face part (1-5) of blade trailing edge (1-4) from blade inlet edge (1-3) and surface part (1-6) is formed; It is characterized in that: described blade body (1) inwall is provided with multiple dividing plate (1-7) along blade radial arrangement, cooling chamber (2) is divided into separate the first cooling chamber (2-1) by one of them dividing plate (1-7), and the first cooling chamber (2-1) is partitioned into multiple cavity being interconnected by all the other dividing plates (1-7); Described blade inlet edge (1-3) be provided with multiple inside and outside the air film hole (1-8) that runs through; Described blade body (1) inwall is also provided with multiple turbulence columns (1-9); The end face ovalize of described turbulence columns (1-9), oval long axis direction is consistent with the flow direction of cooling draught.
2. a kind of turbine cooling blade according to claim 1, it is characterised in that: in described multiple dividing plate (1-7), the dividing plate nearest apart from blade inlet edge (1-3) is provided with multiple impinging cooling hole (1-10).
3. a kind of turbine cooling blade according to claim 1, it is characterised in that: one end of described turbulence columns (1-9) is fixedly connected with blade body (1) inwall, and the other end is unsettled end.
4. a kind of turbine cooling blade according to claim 3, it is characterised in that: the slope structure that the end face of the unsettled end of described turbulence columns (1-9) is low after being front height along the flow direction of cooling gas.
5. a kind of turbine cooling blade according to claim 3, it is characterised in that: described turbulence columns (1-9) is crisscross arranged in the inwall both sides of blade body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521005473.7U CN205297652U (en) | 2015-12-07 | 2015-12-07 | Turbine cooling blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521005473.7U CN205297652U (en) | 2015-12-07 | 2015-12-07 | Turbine cooling blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205297652U true CN205297652U (en) | 2016-06-08 |
Family
ID=56436930
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521005473.7U Active CN205297652U (en) | 2015-12-07 | 2015-12-07 | Turbine cooling blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205297652U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107060889A (en) * | 2017-04-19 | 2017-08-18 | 西北工业大学 | A kind of double disc turbine disks with disk chamber turbulence columns |
| CN111485957A (en) * | 2020-04-29 | 2020-08-04 | 中国航发湖南动力机械研究所 | Turbine guide cooling blade |
-
2015
- 2015-12-07 CN CN201521005473.7U patent/CN205297652U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107060889A (en) * | 2017-04-19 | 2017-08-18 | 西北工业大学 | A kind of double disc turbine disks with disk chamber turbulence columns |
| CN111485957A (en) * | 2020-04-29 | 2020-08-04 | 中国航发湖南动力机械研究所 | Turbine guide cooling blade |
| CN111485957B (en) * | 2020-04-29 | 2022-11-25 | 中国航发湖南动力机械研究所 | Turbine guide cooling blade |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |