CN205876398U - Gas turbine blade with vertical crossing rib cooling structure - Google Patents
Gas turbine blade with vertical crossing rib cooling structure Download PDFInfo
- Publication number
- CN205876398U CN205876398U CN201620711394.6U CN201620711394U CN205876398U CN 205876398 U CN205876398 U CN 205876398U CN 201620711394 U CN201620711394 U CN 201620711394U CN 205876398 U CN205876398 U CN 205876398U
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- China
- Prior art keywords
- baffle
- blade
- rib
- gas turbine
- leading edge
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The utility model discloses a gas turbine blade with vertical crossing rib cooling structure, including the leaf with platform and blade, the leaf is located the top of blade with the platform, the leaf is with being equipped with first baffle in the platform, first baffle is with the leaf with separating into first air inlet and second air inlet in the platform, the top of first baffle is equipped with the second baffle, the second baffle is the U -shaped structure, and is equipped with the third baffle in the second baffle, the blade includes leading edge and tail edge, be equipped with a film cooling hole in the leading edge, the intermediate position at leading edge and tail edge top is equipped with the 2nd film cooling hole, one side that the second baffle is close to the leading edge is equipped with the fourth baffle, be equipped with the impact opening on the fourth baffle. The utility model relates to a rationally, have better cooling effect, effectively improved heat exchange efficiency, avoided cooling gas and the loss that the mainstream mixing caused among the air cooling simultaneously, reduce the impact to the blade, improve the life of this gas turbine blade.
Description
Technical field
This utility model relates to gas turbine technology field, particularly relates to a kind of combustion having and longitudinally intersecting rib cooling structure
Gas turbine blade.
Background technology
Gas turbine, as a kind of important heat to power output device, obtains day in fields such as aviation, boats and ships, generating and chemical industry
Benefit is widely applied, particularly important with the status in national defense construction in national economy.Under the trend of Present Global energy scarcity,
The related scientific research designer of various countries is making great efforts raising gas turbine proficiency.Improve an important channel of gas turbine performance
It is to improve turbine inlet gas temperature.Along with improving constantly of turbine inlet gas temperature, its running temperature is far above metal
Allow temperature, as in current state-of-the-art aero-gas turbine, turbine inlet gas temperature has reached 2000K, advanced Heavy duty gas wheel
The turbine-inlet temperature of machine has reached 1873K, is up to 1973K grinding heavy duty gas turbine turbine-inlet temperature.Combustion gas to be ensured is taken turns
Machine can mainly have two kinds of approach by reliability service in high temperature environments for a long time, a kind of is to improve further the heat-resisting of blade material
Performance, another kind is to use advanced cooling technology to reduce leaf temperature.The raising 70% of turbine inlet gas temperature be due to
Have employed effective air Cooling Design, other 30% is the progress of the development due to heat proof material and processing technology.Visible, thoroughly
Flat Cooling Design, to improving turbine-inlet temperature, increases gas turbine specific power and the thermal efficiency is most important.Turbine blade is
In order to guide fluid to flow in certain direction in flat gas turbine, and the vitals that drive rotor rotates.It is contained on housing
Blade claims stator blade or stator, and the blade being contained on rotor is referred to as moving vane.The main body of turbine blade is blade, its size relationship
Negotiability to turbine.In high rate turbine machinery, the disconnected of any movable vane falls all to cause vibration, even causes damage, needs
Critical jerk machine overhauling.Therefore, the reliability of blade is most important.
Utility model content
The purpose of this utility model is to solve shortcoming present in prior art, and the one proposed has longitudinal phase
Hand over the gas turbine blade of rib cooling structure.
To achieve these goals, this utility model adopts the technical scheme that
A kind of have the gas turbine blade longitudinally intersecting rib cooling structure, including leaf with platform and blade, described leaf with
Platform is positioned at the top of blade, and described leaf is with being provided with the first baffle plate in platform, leaf is separated into by described first baffle plate with in platform
First air inlet and the second air inlet, the top of described first baffle plate is provided with second baffle, and described second baffle is U-shaped structure,
And in second baffle, it is provided with third gear plate, described blade includes that leading edge and trailing edge, described leading edge are provided with the first film cooling holes,
The centre position at described leading edge and trailing edge top is provided with the second film cooling holes, and described second baffle is provided with near the side of leading edge
Fourth gear plate, described fourth gear plate is provided with impact opening, and described second baffle is provided with Circular Cylinder group, institute near the side of trailing edge
State trailing edge and be provided with the 3rd film cooling holes, described fourth gear plate and second baffle, second baffle and third gear plate and second gear
The most arranged in parallel between plate and Circular Cylinder group have flow-disturbing rib, and described flow-disturbing rib is provided with turbulent flow generator, described flow-disturbing rib it
Between run through to have and longitudinally intersect rib.
Preferably, described first film cooling holes is angularly disposed in leading edge, and the first film cooling holes and impact opening phase
Coordinate.
Preferably, described Circular Cylinder group is six to two ten row, and Circular Cylinder group is corresponding with flow-disturbing rib.
Preferably, the bottom of described fourth gear plate is arcuate structure, and described fourth gear plate is connected with leading edge.
Preferably, described Circular Cylinder group is additionally provided with through hole.
The beneficial effects of the utility model are: reasonable in design, operation and simple in construction, utilize flow-disturbing rib and longitudinally intersect rib
Staggered form design, has more preferably cooling effect, is effectively increased heat exchange efficiency, avoids in air cooling simultaneously and cools down gas
Blend, with main flow, the loss caused, reduce the impact to blade, improve the service life of this gas turbine blade.
Accompanying drawing explanation
Fig. 1 is that a kind of structure with the gas turbine blade longitudinally intersecting rib cooling structure that the utility model proposes is shown
It is intended to.
In figure: 1 leaf with platform, 2 flow-disturbing ribs, 3 impact openings, 4 leading edges, 5 fourth gear plates, 6 first film cooling holes, 7 second
Film cooling holes, 8 third gear plates, 9 second baffles, 10 trailing edges, 11 Circular Cylinder groups, 12 the 3rd film cooling holes, 13 turbulent flows are sent out
Raw device, 14 the most crossing rib, 15 first air inlets, 16 first baffle plates, 17 second air inlets.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole
Embodiment.
Embodiment
With reference to Fig. 1, a kind of have the gas turbine blade longitudinally intersecting rib cooling structure, including leaf with platform 1 and blade,
Leaf is positioned at the top of blade with platform 1, leaf with being provided with the first baffle plate 16 in platform 1, the first baffle plate 16 by leaf with in platform 1 separate
Becoming the first air inlet 15 and the second air inlet 17, the top of the first baffle plate 16 is provided with second baffle 9, and second baffle 9 is tied for U-shaped
Being provided with third gear plate 8 in structure, and second baffle 9, blade includes leading edge 4 and trailing edge 10, and leading edge 4 is provided with the first film cooling holes
6, the centre position at leading edge 4 and trailing edge 10 top is provided with the second film cooling holes 7, and second baffle 9 is provided with near the side of leading edge 4
Fourth gear plate 5, fourth gear plate 5 is provided with impact opening 3, and second baffle 9 is provided with Circular Cylinder group 11, tail near the side of trailing edge 10
Edge 10 is provided with the 3rd film cooling holes 12, fourth gear plate 5 and second baffle 9, second baffle 9 and third gear plate 8 and second gear
The most arranged in parallel between plate 9 and Circular Cylinder group 11 have flow-disturbing rib 2, and flow-disturbing rib 2 is provided with turbulent flow generator 13, flow-disturbing rib 2 it
Between run through to have and longitudinally intersect rib 14.The beneficial effects of the utility model are: reasonable in design, operation and simple in construction, utilize flow-disturbing
Rib 2 intersects rib 14 staggered form design with longitudinal, has more preferably cooling effect, is effectively increased heat exchange efficiency, avoids simultaneously
Air cooling cools down gas and blends, with main flow, the loss caused, reduce the impact to blade, improve this gas turbine blade
Service life.
First film cooling holes 6 is angularly disposed in leading edge 4, and the first film cooling holes 6 matches with impact opening 3, around
Stream cylinder group 11 is six to two ten row, and Circular Cylinder group 11 is corresponding with flow-disturbing rib 2, and the bottom of fourth gear plate 5 is arc knot
Structure, fourth gear plate 5 is connected with leading edge 4, and Circular Cylinder group 11 is additionally provided with through hole.The beneficial effects of the utility model are: set
Meter rationally, operates and simple in construction, utilizes flow-disturbing rib 2 and longitudinally intersects rib 14 staggered form design, having more preferably cooling effect,
It is effectively increased heat exchange efficiency, avoids simultaneously and air cooling cools down the loss that gas causes with main flow blending, reduce leaf
The impact of sheet, improves the service life of this gas turbine blade.
Example one: during work, cooling air enters blade, fourth gear plate 5 from the first air inlet 15 and the second air inlet 17
And the most arranged in parallel between second baffle 9, second baffle 9 and third gear plate 8 and second baffle 9 and Circular Cylinder group 11 have flow-disturbing
Rib 2, flow-disturbing rib 2 is provided with turbulent flow generator 13, runs through to have and longitudinally intersects rib 14, utilize flow-disturbing rib 2 with longitudinal between flow-disturbing rib 2
Intersect rib 14 staggered form design, there is more preferably cooling effect, be effectively increased heat exchange efficiency, avoid in air cooling simultaneously
Cooling gas blends, with main flow, the loss caused, and reduces the impact to blade, improves the service life of this gas turbine blade.
The above, only this utility model preferably detailed description of the invention, but protection domain of the present utility model is not
Being confined to this, any those familiar with the art is in the technical scope that this utility model discloses, according to this practicality
Novel technical scheme and utility model thereof conceive equivalent or change in addition, all should contain at protection model of the present utility model
Within enclosing.
Claims (5)
1. there is the gas turbine blade longitudinally intersecting rib cooling structure, exist with platform (1) and blade, its feature including leaf
In, described leaf is positioned at the top of blade with platform (1), and described leaf is provided with the first baffle plate (16), described first gear with in platform (1)
Plate (16) by leaf with being separated into the first air inlet (15) and the second air inlet (17) in platform (1), described first baffle plate (16)
Top is provided with second baffle (9), and described second baffle (9) is U-shaped structure, and is provided with third gear plate (8) in second baffle (9),
Described blade includes leading edge (4) and trailing edge (10), and described leading edge (4) is provided with the first film cooling holes (6), described leading edge (4)
Being provided with the second film cooling holes (7) with the centre position at trailing edge (10) top, described second baffle (9) is near the one of leading edge (4)
Side is provided with fourth gear plate (5), and described fourth gear plate (5) is provided with impact opening (3), and described second baffle (9) is near trailing edge (10)
Side be provided with Circular Cylinder group (11), described trailing edge (10) is provided with the 3rd film cooling holes (12), described fourth gear plate (5)
And it is the most parallel between second baffle (9), second baffle (9) and third gear plate (8) with second baffle (9) and Circular Cylinder group (11)
Being arranged with flow-disturbing rib (2), described flow-disturbing rib (2) is provided with turbulent flow generator (13), and running through between described flow-disturbing rib (2) has longitudinal direction
Intersect rib (14).
A kind of gas turbine blade with the most crossing rib cooling structure the most according to claim 1, it is characterised in that
Described first film cooling holes (6) is angularly disposed in leading edge (4), and the first film cooling holes (6) matches with impact opening (3)
Close.
A kind of gas turbine blade with the most crossing rib cooling structure the most according to claim 1, it is characterised in that
Described Circular Cylinder group (11) is six to two ten row, and Circular Cylinder group (11) is corresponding with flow-disturbing rib (2).
A kind of gas turbine blade with the most crossing rib cooling structure the most according to claim 1, it is characterised in that
The bottom of described fourth gear plate (5) is arcuate structure, and described fourth gear plate (5) is connected with leading edge (4).
A kind of gas turbine blade with the most crossing rib cooling structure the most according to claim 1, it is characterised in that
It is additionally provided with through hole on described Circular Cylinder group (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620711394.6U CN205876398U (en) | 2016-07-07 | 2016-07-07 | Gas turbine blade with vertical crossing rib cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620711394.6U CN205876398U (en) | 2016-07-07 | 2016-07-07 | Gas turbine blade with vertical crossing rib cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205876398U true CN205876398U (en) | 2017-01-11 |
Family
ID=57695991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620711394.6U Expired - Fee Related CN205876398U (en) | 2016-07-07 | 2016-07-07 | Gas turbine blade with vertical crossing rib cooling structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205876398U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014488A (en) * | 2016-07-07 | 2016-10-12 | 周丽玲 | Gas turbine blade with longitudinal intersection rib cooling structure |
| CN109386309A (en) * | 2017-08-03 | 2019-02-26 | 通用电气公司 | Engine component with non-homogeneous herringbone pin |
| CN111648830A (en) * | 2020-05-14 | 2020-09-11 | 西安交通大学 | Internal cooling ribbed channel for rear part of turbine moving blade |
| CN113605992A (en) * | 2021-08-26 | 2021-11-05 | 华能国际电力股份有限公司 | Gas turbine cooling blade with internal micro-channels |
-
2016
- 2016-07-07 CN CN201620711394.6U patent/CN205876398U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014488A (en) * | 2016-07-07 | 2016-10-12 | 周丽玲 | Gas turbine blade with longitudinal intersection rib cooling structure |
| CN109386309A (en) * | 2017-08-03 | 2019-02-26 | 通用电气公司 | Engine component with non-homogeneous herringbone pin |
| CN109386309B (en) * | 2017-08-03 | 2021-12-24 | 通用电气公司 | Engine component with non-uniform chevron pin |
| CN111648830A (en) * | 2020-05-14 | 2020-09-11 | 西安交通大学 | Internal cooling ribbed channel for rear part of turbine moving blade |
| CN111648830B (en) * | 2020-05-14 | 2021-04-20 | 西安交通大学 | Internal cooling ribbed channel for rear part of turbine moving blade |
| CN113605992A (en) * | 2021-08-26 | 2021-11-05 | 华能国际电力股份有限公司 | Gas turbine cooling blade with internal micro-channels |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170111 Termination date: 20180707 |