CN109139128A - A kind of marine gas turbine high-pressure turbine guide vane cooling structure - Google Patents
A kind of marine gas turbine high-pressure turbine guide vane cooling structure Download PDFInfo
- Publication number
- CN109139128A CN109139128A CN201811230895.2A CN201811230895A CN109139128A CN 109139128 A CN109139128 A CN 109139128A CN 201811230895 A CN201811230895 A CN 201811230895A CN 109139128 A CN109139128 A CN 109139128A
- Authority
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- China
- Prior art keywords
- blade
- guide vane
- gas turbine
- cooling structure
- back cavity
- Prior art date
- 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.)
- Pending
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 38
- 239000011888 foil Substances 0.000 claims abstract description 12
- 238000005243 fluidization Methods 0.000 claims description 2
- 238000004080 punching Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 14
- 239000000567 combustion gas Substances 0.000 description 7
- 239000000463 material Substances 0.000 description 6
- 238000012546 transfer Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 238000011161 development Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 230000008646 thermal stress Effects 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A kind of marine gas turbine high-pressure turbine guide vane cooling structure, it is related to a kind of guide vane of high pressure turbine, and in particular to a kind of marine gas turbine high-pressure turbine guide vane cooling structure.The present invention is shorter for the high-pressure turbine guide vane service life for solving the problems, such as existing marine gas turbine.The present invention includes blade supramarginal plate, vane foil and blade inframarginal, blade supramarginal plate, vane foil, blade inframarginal are sequentially connected integrally, vane foil outer surface is made of suction surface and pressure face, suction surface and pressure face juncture area are blade inlet edge and blade trailing edge respectively, blade interior is equipped with ante-chamber and back cavity, blade inframarginal lower surface is equipped with ante-chamber entrance and back cavity entrance, and ante-chamber entrance is connected to ante-chamber, and back cavity entrance is connected to back cavity.The invention belongs to marine gas turbine apparatus fields.
Description
Technical field
The present invention relates to a kind of guide vane of high pressure turbine, and in particular to a kind of marine gas turbine high-pressure turbine guide vane is cold
But structure belongs to marine gas turbine apparatus field.
Background technique
Marine gas turbine is complicated and accurate high-tech product, and work is rotten in high temperature, high pressure, high revolving speed and high smog
Under the adverse circumstances of erosion.Its development is related to thermodynamics, hydrodynamics, thermal conduction study, Combustion, structural strength, Machine Design, material
Multiple ambits such as material learns, manufacturing technology and control science, the design process of blade experienced it is one-dimensional, two-dimentional, three
Structure design is tieed up, is a multidisciplinary synthesis, complicated system engineering.
From the aspect of gas turbine heating power circulation, improving turbine entrance temperature temperature is to improve engine thermal engine efficiency and function
The basic place of rate.With gas turbine performance require it is higher and higher, turbine inlet fuel gas temperature is also higher and higher.From turbine
The temperature spread of the Analysis on development of inlet gas temperature and blade material, blade material tolerable temperature and turbine inlet is increasingly
Greatly.Obviously in order to reach the technical indicator of heavy duty gas turbine, rely solely on material development be it is inadequate, rationally introduce cold
But system is the key that solve the problems, such as.Efficient cooling technology can extend the service life of heating part, using more economical
For material to reduce cost, these significant advantages make the design of cooling system occupy act foot in high performance gas-turbine engine development
The status of weight.
Guide vane of high pressure turbine is directly exposed to combustor exit, due to by gas turbine rapid starting/stopping, variable working condition
And the influence of the factors such as combustor exit unevenness, operating condition are the most complicated.It is continuous with turbine inlet temperature (TIT)
It improves, one side combustor exit maximum radial and circumferential asymmetry evenness can also be increase accordingly, this will lead to blade thermic load and mentions
High, thermal stress increases.On the other hand, the continuous improvement required turbine efficiency, it is continuous that this results in blade trailing edge area thickness
Thinning, the outer coefficient of heat transfer is big, is that turbo blade is most difficult to cooling one of region.Therefore turborotor trailing edge region is carried out
High-efficient cooling structure design is one of critical issue of gas turbine design.
Summary of the invention
The present invention is to solve the problems, such as that the high-pressure turbine guide vane service life of existing marine gas turbine is shorter, Jin Erti
A kind of marine gas turbine high-pressure turbine guide vane cooling structure out.
The technical solution adopted by the present invention to solve the above problem is as follows: the present invention include blade supramarginal plate, vane foil and
Blade inframarginal, blade supramarginal plate, vane foil, blade inframarginal are sequentially connected integrally, and vane foil outer surface is by suction
Face and pressure face composition, suction surface and pressure face juncture area are blade inlet edge and blade trailing edge respectively, before blade interior is equipped with
Chamber and back cavity, blade inframarginal lower surface are equipped with ante-chamber entrance and back cavity entrance, and ante-chamber entrance is connected to ante-chamber, back cavity entrance and
Back cavity connection.
Further, impingement sleeve is fitted in back cavity.
Further, the side of impingement sleeve towards pressure face is provided with row's impingement sleeve pressure face impact opening；Impact sleeve
Cylinder is provided with row's impingement sleeve suction surface impact opening towards the side of suction surface.
Further, blade trailing edge region is equipped with multiple turbulence columns, one end of turbulence columns and pressure face from blade root to leaf top
Connection, the other end of turbulence columns are connect with suction surface.
Further, the cross-sectional shape of turbulence columns can be round or ellipse, and the size of single-column can not phase
Deng.
Further, the axial distance between two neighboring turbulence columns and radial distance are unequal.
The beneficial effects of the present invention are: turbulence columns one end of the invention is connected with blade trailing edge pressure face, one end and suction
Face is connected.On the one hand, the intensity of trailing edge structures can be improved in the suction surface of turbulence columns connection blade and pressure face.On the other hand,
Wake flow caused by every turbulence columns can increase the turbulivity of free flow, while the wake flow of upstream column can also influence downstream column
Flowing and heat transfer property, enhance blade trailing edge region heat transfer intensity, thus reduce blade temperature.Such processability of product structure
Also relatively good, it is a kind of effective blade trailing edge enhanced heat exchange cooling structure.The present invention is not increasing total cooling air delivery
In the case of, more efficient reasonable cooling can be carried out to blade trailing edge region, strengthen the heat exchange of blade trailing edge, reduce blade
Maximum temperature and mean temperature, to improve the service life of blade.
Detailed description of the invention
Fig. 1 is three dimensional structure diagram of the invention；
Fig. 2 is schematic diagram in A-A direction in Fig. 1；
Fig. 3 is schematic perspective view of the invention.
Specific embodiment
Specific embodiment 1: illustrating present embodiment, a kind of combustion gas peculiar to vessel described in present embodiment in conjunction with Fig. 1 to Fig. 3
Turbine high-pressure turbine guide vane cooling structure, it includes blade supramarginal plate 1, vane foil 2 and blade inframarginal 3, blade supramarginal plate
1, vane foil 2, blade inframarginal 3 are sequentially connected integrally, and 2 outer surface of vane foil is by suction surface 11 and 12 groups of pressure face
At suction surface 11 and 12 juncture area of pressure face are blade inlet edge 8 and blade trailing edge 10 respectively, and blade interior is equipped with 6 He of ante-chamber
Back cavity 7,3 lower surface of blade inframarginal are equipped with ante-chamber entrance 4 and back cavity entrance 5, and ante-chamber entrance 4 is connected to ante-chamber 6, back cavity entrance
5 are connected to back cavity 7.Cooling air is extracted out from compressor, and the ante-chamber of blade inframarginal is transported to along the specific lumen of gas turbine
Entrance 4 and back cavity entrance 5.
Specific embodiment 2: illustrating present embodiment, a kind of combustion gas peculiar to vessel described in present embodiment in conjunction with Fig. 1 to Fig. 3
Impingement sleeve 13 is fitted in the back cavity 7 of turbine high-pressure turbine guide vane cooling structure.Other compositions and connection relationship and specific reality
It is identical to apply mode one.
Specific embodiment 3: illustrating present embodiment, a kind of combustion gas peculiar to vessel described in present embodiment in conjunction with Fig. 1 to Fig. 3
The side of impingement sleeve 13 towards the pressure face 12 of turbine high-pressure turbine guide vane cooling structure is provided with row's impingement sleeve pressure face
Impact opening 14；The side of impingement sleeve 13 towards suction surface 11 is provided with row's impingement sleeve suction surface impact opening 15.Other compositions
And connection relationship is same as the specific embodiment one.
Specific embodiment 4: illustrating present embodiment, a kind of combustion gas peculiar to vessel described in present embodiment in conjunction with Fig. 1 to Fig. 3
10 region of blade trailing edge of turbine high-pressure turbine guide vane cooling structure is equipped with multiple turbulence columns 16, turbulence columns 16 from blade root to leaf top
One end connect with pressure face 12, the other end of turbulence columns 16 is connect with suction surface 11.Other compositions and connection relationship and specific
Embodiment one is identical.
Specific embodiment 5: illustrating present embodiment, a kind of combustion gas peculiar to vessel described in present embodiment in conjunction with Fig. 1 to Fig. 3
The cross-sectional shape of the turbulence columns 16 of turbine high-pressure turbine guide vane cooling structure can be round or ellipse.It is other composition and
Connection relationship is identical as specific embodiment four.
Specific embodiment 6: illustrating present embodiment, a kind of combustion gas peculiar to vessel described in present embodiment in conjunction with Fig. 1 to Fig. 3
Axial distance and radial distance between the two neighboring turbulence columns 16 of turbine high-pressure turbine guide vane cooling structure is unequal.Its
It is formed and connection relationship is identical as specific embodiment four.
Working principle
Ante-chamber 6 is entered using the cooling blade inlet edge region of gaseous film control structure, one cooling air from cooling duct entrance 4
Blade ante-chamber, after this strand of cooling air enters ante-chamber, a part of gas through impact aperture, impact leading edge inner wall impact it is cold
But.Another strand of cooling air is directly sprayed by air film hole, forms film overcast edge in front of the blade, obstructs hot combustion gas to solid wall surface
Heating.
Back cavity 7 using the cooling middle part of blade of impingement sleeve+turbulence columns mode and blade trailing edge region, one cooling air from
Cooling duct entrance 5 enters back cavity.An impingement sleeve 13 is arranged in blade back cavity, on the impingement sleeve pressure face and
At least respectively there is row's aperture in the high direction of suction surface lateral edge leaf.After this strand of cooling air enters back cavity, through pressure face on impingement sleeve
Side aperture 14 and 15 accelerating jetting of suction surface aperture enhance convection current cooling effect to blade pressure surface and suction surface inner wall, can
With effectively cooling blade high-temperature area, entire blade regional temperature is made to be unlikely to too high.
After cooling air is fully cooled blade region, blade trailing edge region is flowed to, trailing edge region is carried out by turbulence columns
It is cooling.Around the cross sectional shape of fluidization tower, size and axially and radially spacing, can be carried out according to blade conjugate heat transfer calculated result
Corresponding adjustment.Wake flow caused by every turbulence columns can increase the turbulivity of free flow, while the wake flow of upstream column can also be with
Flowing and the heat transfer property for influencing downstream column, enhance the heat transfer intensity in blade trailing edge region, thus reduce the temperature of blade.Together
When, the intensity of trailing edge structures can be improved in the suction surface and pressure face of turbulence columns connection blade, enhances reliability；
The above described is only a preferred embodiment of the present invention, be not intended to limit the present invention in any form, though
So the present invention has been disclosed as a preferred embodiment, and however, it is not intended to limit the invention, any technology people for being familiar with this profession
Member, without departing from the scope of the present invention, when the technology contents using the disclosure above are modified or are modified
For the equivalent embodiment of equivalent variations, but without departing from the technical solutions of the present invention, according to the technical essence of the invention,
Within the spirit and principles in the present invention, any simple modifications, equivalent substitutions and improvements to the above embodiments etc., still
Belong within the protection scope of technical solution of the present invention.
Claims (6)
1. a kind of marine gas turbine high-pressure turbine guide vane cooling structure, it include blade supramarginal plate (1), vane foil (2) and
Blade inframarginal (3), blade supramarginal plate (1), vane foil (2), blade inframarginal (3) are sequentially connected integrally, and feature exists
In: vane foil (2) outer surface is made of suction surface (11) and pressure face (12), suction surface (11) and pressure face (12) junctional area
Domain is blade inlet edge (8) and blade trailing edge (10) respectively, and blade interior is equipped with ante-chamber (6) and back cavity (7), blade inframarginal (3)
Lower surface is equipped with ante-chamber entrance (4) and back cavity entrance (5), and ante-chamber entrance (4) is connected to ante-chamber (6), back cavity entrance (5) and back cavity
(7) it is connected to.
2. a kind of marine gas turbine high-pressure turbine guide vane cooling structure according to claim 1, it is characterised in that: back cavity
(7) impingement sleeve (13) are fitted in.
3. a kind of marine gas turbine high-pressure turbine guide vane cooling structure according to claim 1 or claim 2, it is characterised in that: punching
The side for hitting sleeve (13) towards pressure face (12) is provided with row's impingement sleeve pressure face impact opening (14)；Impingement sleeve (13) court
Row's impingement sleeve suction surface impact opening (15) is provided with to the side of suction surface (11).
4. a kind of marine gas turbine high-pressure turbine guide vane cooling structure according to claim 1, it is characterised in that: blade tail
Edge (10) region is equipped with multiple turbulence columns (16) from blade root to leaf top, and one end of turbulence columns (16) connect with pressure face (12), disturbs
The other end of fluidization tower (16) is connect with suction surface (11).
5. a kind of marine gas turbine high-pressure turbine guide vane cooling structure according to claim 4, it is characterised in that: turbulence columns
(16) cross-sectional shape can be round or ellipse, and the size of single-column can be unequal.
6. a kind of marine gas turbine high-pressure turbine guide vane cooling structure according to claim 4, it is characterised in that: adjacent two
Axial distance and radial distance between a turbulence columns (16) is unequal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811230895.2A CN109139128A (en) | 2018-10-22 | 2018-10-22 | A kind of marine gas turbine high-pressure turbine guide vane cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811230895.2A CN109139128A (en) | 2018-10-22 | 2018-10-22 | A kind of marine gas turbine high-pressure turbine guide vane cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109139128A true CN109139128A (en) | 2019-01-04 |
Family
ID=64809262
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811230895.2A Pending CN109139128A (en) | 2018-10-22 | 2018-10-22 | A kind of marine gas turbine high-pressure turbine guide vane cooling structure |
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| CN (1) | CN109139128A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112459850A (en) * | 2020-10-27 | 2021-03-09 | 中船重工龙江广瀚燃气轮机有限公司 | Gas turbine active control pneumatic cooling system |
| CN114087027A (en) * | 2021-11-23 | 2022-02-25 | 浙江燃创透平机械股份有限公司 | Gas turbine stationary blade with flow guide pipe |
| CN114370305A (en) * | 2022-01-25 | 2022-04-19 | 杭州汽轮动力集团有限公司 | Gas turbine stationary blade composite cooling structure |
| CN115075891A (en) * | 2022-05-29 | 2022-09-20 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane trailing edge structure with pressure side exhaust |
| WO2024017385A1 (en) * | 2022-07-22 | 2024-01-25 | 中国航发商用航空发动机有限责任公司 | Movable blade of high-pressure turbine |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112459850A (en) * | 2020-10-27 | 2021-03-09 | 中船重工龙江广瀚燃气轮机有限公司 | Gas turbine active control pneumatic cooling system |
| CN114087027A (en) * | 2021-11-23 | 2022-02-25 | 浙江燃创透平机械股份有限公司 | Gas turbine stationary blade with flow guide pipe |
| CN114087027B (en) * | 2021-11-23 | 2024-02-27 | 浙江燃创透平机械有限公司 | Gas turbine stationary blade with honeycomb duct |
| CN114370305A (en) * | 2022-01-25 | 2022-04-19 | 杭州汽轮动力集团有限公司 | Gas turbine stationary blade composite cooling structure |
| CN114370305B (en) * | 2022-01-25 | 2024-02-20 | 杭州汽轮控股有限公司 | Composite cooling structure for turbine stator blades of gas turbine |
| CN115075891A (en) * | 2022-05-29 | 2022-09-20 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine guide vane trailing edge structure with pressure side exhaust |
| WO2024017385A1 (en) * | 2022-07-22 | 2024-01-25 | 中国航发商用航空发动机有限责任公司 | Movable blade of high-pressure turbine |
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