CN106014488A - Gas turbine blade with longitudinal intersection rib cooling structure - Google Patents
Gas turbine blade with longitudinal intersection rib cooling structure Download PDFInfo
- Publication number
- CN106014488A CN106014488A CN201610531012.6A CN201610531012A CN106014488A CN 106014488 A CN106014488 A CN 106014488A CN 201610531012 A CN201610531012 A CN 201610531012A CN 106014488 A CN106014488 A CN 106014488A
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- China
- Prior art keywords
- baffle
- blade
- gas turbine
- rib
- turbine blade
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- Pending
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 47
- 238000013461 design Methods 0.000 abstract description 10
- 230000000694 effects Effects 0.000 abstract description 5
- 238000002156 mixing Methods 0.000 abstract description 5
- 239000007789 gas Substances 0.000 abstract 4
- 239000000112 cooling gas Substances 0.000 abstract 1
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 10
- 238000010276 construction Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- 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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas turbine blade with a longitudinal intersection rib cooling structure. The blade comprises a blade root platform and a blade body; the blade root platform is located above the blade body, a first baffle is arranged in the blade root platform, the interior of the blade root platform is divided into a first air inlet and a second air inlet through the first baffle, a second baffle is arranged at the top end of the first baffle, the second baffle is of a U-shaped structure, and a third baffle is arranged in the second baffle; the blade body comprises a front edge and a tail edge, a first gas film cooling hole is formed in the front edge, a second gas film cooling hole is formed between the front edge and the top of the tail edge, a fourth baffle is arranged on the side, close to the front edge, of the second baffle, and an impact hole is formed in the fourth baffle; and the blade is reasonable in design, and has the better cooling effect, the heat exchange efficiency is effectively improved, meanwhile, the loss caused by mixing of cooling gas and a main flow in air cooling is avoided, the impact to the blade is reduced, and the service life of the gas turbine blade is prolonged.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of gas turbine blade having and longitudinally intersecting rib cooling structure.
Background technology
Gas turbine, as a kind of important heat to power output device, obtains increasingly extensive application in fields such as aviation, boats and ships, generating and chemical industry, 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.The important channel improving gas turbine performance is to improve turbine inlet gas temperature.Along with improving constantly of turbine inlet gas temperature, its running temperature allows temperature far above metal, as in current state-of-the-art aero-gas turbine, turbine inlet gas temperature has reached 2000K, the turbine-inlet temperature of advanced heavy duty gas turbine has reached 1873K, is up to 1973K grinding heavy duty gas turbine turbine-inlet temperature.Gas turbine to be ensured can mainly have two kinds of approach, a kind of heat resistance being to improve further blade material by reliability service in high temperature environments for a long time, and another kind is to use advanced cooling technology to reduce leaf temperature.The raising 70% of turbine inlet gas temperature is owing to have employed effective air Cooling Design, and other 30% is the progress of the development due to heat proof material and processing technology.Visible, turbine 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 turbine gas turbine, and the vitals that drive rotor rotates.The blade being contained on housing 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, the negotiability of its size relationship to turbine.In high rate turbine machinery, the disconnected of any movable vane falls all to cause vibration, even causes damage, needs emergency shutdown to overhaul.Therefore, the reliability of blade is most important.
Summary of the invention
The invention aims to solve shortcoming present in prior art, and propose a kind of there is the gas turbine blade longitudinally intersecting rib cooling structure.
To achieve these goals, present invention employs following technical scheme:
nullA kind of have the gas turbine blade longitudinally intersecting rib cooling structure，Including leaf with platform and blade，Described leaf is positioned at the top of blade with platform，Described leaf is with being provided with the first baffle plate in platform，Described first baffle plate by leaf with being separated into the first air inlet and the second air inlet in platform，The top of described first baffle plate is provided with second baffle，Described second baffle is U-shaped structure，And in second baffle, it is provided with third gear plate，Described blade includes leading edge and trailing edge，Described leading edge is 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，Described second baffle is provided with fourth gear plate near the side of leading edge，Described fourth gear plate is provided with impact opening，Described second baffle is provided with Circular Cylinder group near the side of trailing edge，Described trailing edge is provided with the 3rd film cooling holes，Described fourth gear plate and second baffle、The most arranged in parallel between second baffle and third gear plate and second baffle and Circular Cylinder group have flow-disturbing rib，Described flow-disturbing rib is provided with turbulent flow generator，Run through between described flow-disturbing rib to have and longitudinally intersect rib.
Preferably, described first film cooling holes is angularly disposed in leading edge, and the first film cooling holes matches with impact opening.
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 invention has the beneficial effects as follows: reasonable in design, operation and simple in construction, utilize flow-disturbing rib and longitudinally intersect rib staggered form design, there is more preferably cooling effect, it is effectively increased heat exchange efficiency, avoid simultaneously and air cooling cools down the loss that gas causes with main flow blending, reduce the impact to blade, improve the service life of this gas turbine blade.
Accompanying drawing explanation
Fig. 1 is a kind of structural representation with the gas turbine blade longitudinally intersecting rib cooling structure that the present invention proposes.
In figure: 1 leaf is 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 flow generators, 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 the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments.
Embodiment
nullWith 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 is with being provided with the first baffle plate 16 in platform 1，First baffle plate 16 by leaf with being separated into the first air inlet 15 and the second air inlet 17 in platform 1，The top of the first baffle plate 16 is provided with second baffle 9，Second baffle 9 is U-shaped structure，And in second baffle 9, it is provided with third gear plate 8，Blade includes leading edge 4 and trailing edge 10，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，Second baffle 9 is provided with fourth gear plate 5 near the side of leading edge 4，Fourth gear plate 5 is provided with impact opening 3，Second baffle 9 is provided with Circular Cylinder group 11 near the side of trailing edge 10，Trailing edge 10 is provided with the 3rd film cooling holes 12，Fourth gear plate 5 and second baffle 9、The most arranged in parallel between 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，Run through between flow-disturbing rib 2 to have and longitudinally intersect rib 14.The invention has the beneficial effects as follows: reasonable in design, operation and simple in construction, utilize flow-disturbing rib 2 and longitudinally intersect rib 14 staggered form design, there is more preferably cooling effect, it is effectively increased heat exchange efficiency, avoid simultaneously and air cooling cools down the loss that gas causes with main flow blending, reduce the impact to blade, improve the service life of this gas turbine blade.
First film cooling holes 6 is angularly disposed in leading edge 4, and first film cooling holes 6 match with impact opening 3, Circular Cylinder group 11 is six to two ten row, and Circular Cylinder group 11 is corresponding with flow-disturbing rib 2, the bottom of fourth gear plate 5 is arcuate structure, fourth gear plate 5 is connected with leading edge 4, and Circular Cylinder group 11 is additionally provided with through hole.The invention has the beneficial effects as follows: reasonable in design, operation and simple in construction, utilize flow-disturbing rib 2 and longitudinally intersect rib 14 staggered form design, there is more preferably cooling effect, it is effectively increased heat exchange efficiency, avoid simultaneously and air cooling cools down the loss that gas causes with main flow blending, reduce the impact to blade, improve the service life of this gas turbine blade.
Example one: during work, cooling air enters blade from the first air inlet 15 and the second air inlet 17, fourth gear plate 5 and second baffle 9, the most arranged in parallel between 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, run through between flow-disturbing rib 2 to have and longitudinally intersect rib 14, utilize flow-disturbing rib 2 and longitudinally intersect rib 14 staggered form design, there is more preferably cooling effect, it is effectively increased heat exchange efficiency, avoid simultaneously and air cooling cools down the loss that gas causes with main flow blending, reduce the impact to blade, improve the service life of this gas turbine blade.
The above; it is only the present invention preferably detailed description of the invention; but protection scope of the present invention is not limited thereto; any those familiar with the art is in the technical scope that the invention discloses; according to technical scheme and inventive concept equivalent or change in addition thereof, all should contain within protection scope of the present invention.
Claims (5)
- null1. one kind has the gas turbine blade longitudinally intersecting rib cooling structure，Including leaf with platform (1) and blade，It is characterized in that，Described leaf is positioned at the top of blade with platform (1)，Described leaf is provided with the first baffle plate (16) with in platform (1)，Described first baffle plate (16) by leaf with being separated into the first air inlet (15) and the second air inlet (17) in platform (1)，The top of described first baffle plate (16) is provided with second baffle (9)，Described second baffle (9) is U-shaped structure，And in second baffle (9), it is provided with third gear plate (8)，Described blade includes leading edge (4) and trailing edge (10)，Described leading edge (4) is provided with the first film cooling holes (6)，The centre position at described leading edge (4) and trailing edge (10) top is provided with the second film cooling holes (7)，Described second baffle (9) is provided with fourth gear plate (5) near the side of leading edge (4)，Described fourth gear plate (5) is provided with impact opening (3)，Described second baffle (9) is provided with Circular Cylinder group (11) near the side of trailing edge (10)，Described trailing edge (10) is provided with the 3rd film cooling holes (12)，Described fourth gear plate (5) and second baffle (9)、The most arranged in parallel between second baffle (9) and third gear plate (8) and second baffle (9) and Circular Cylinder group (11) have flow-disturbing rib (2)，Described flow-disturbing rib (2) is provided with turbulent flow generator (13)，Run through between described flow-disturbing rib (2) to have and longitudinally 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).
- 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 be additionally provided with through hole on described Circular Cylinder group (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610531012.6A CN106014488A (en) | 2016-07-07 | 2016-07-07 | Gas turbine blade with longitudinal intersection rib cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610531012.6A CN106014488A (en) | 2016-07-07 | 2016-07-07 | Gas turbine blade with longitudinal intersection rib cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106014488A true CN106014488A (en) | 2016-10-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610531012.6A Pending CN106014488A (en) | 2016-07-07 | 2016-07-07 | Gas turbine blade with longitudinal intersection rib cooling structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN106014488A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112648018A (en) * | 2020-12-01 | 2021-04-13 | 日照黎阳工业装备有限公司 | High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5695320A (en) * | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having auxiliary turbulators |
| US20030133795A1 (en) * | 2002-01-11 | 2003-07-17 | Manning Robert Francis | Crossover cooled airfoil trailing edge |
| CN1536200A (en) * | 2003-04-08 | 2004-10-13 | ���չ�˾ | Turbo-element |
| CN102966380A (en) * | 2011-08-30 | 2013-03-13 | 通用电气公司 | Airfoil with array of cooling pins |
| CN103052765A (en) * | 2011-03-11 | 2013-04-17 | 三菱重工业株式会社 | Turbine blade and gas turbine |
| CN104791020A (en) * | 2015-04-23 | 2015-07-22 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN205876398U (en) * | 2016-07-07 | 2017-01-11 | 张雯 | Gas turbine blade with vertical crossing rib cooling structure |
-
2016
- 2016-07-07 CN CN201610531012.6A patent/CN106014488A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5695320A (en) * | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having auxiliary turbulators |
| US20030133795A1 (en) * | 2002-01-11 | 2003-07-17 | Manning Robert Francis | Crossover cooled airfoil trailing edge |
| CN1536200A (en) * | 2003-04-08 | 2004-10-13 | ���չ�˾ | Turbo-element |
| CN103052765A (en) * | 2011-03-11 | 2013-04-17 | 三菱重工业株式会社 | Turbine blade and gas turbine |
| CN102966380A (en) * | 2011-08-30 | 2013-03-13 | 通用电气公司 | Airfoil with array of cooling pins |
| CN104791020A (en) * | 2015-04-23 | 2015-07-22 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN205876398U (en) * | 2016-07-07 | 2017-01-11 | 张雯 | Gas turbine blade with vertical crossing rib cooling structure |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112648018A (en) * | 2020-12-01 | 2021-04-13 | 日照黎阳工业装备有限公司 | High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161012 |