CN107965353A - It is a kind of that there is the jet flow groove cooling structure for improving end wall cooling effectiveness near stator blade leading edge - Google Patents
It is a kind of that there is the jet flow groove cooling structure for improving end wall cooling effectiveness near stator blade leading edge Download PDFInfo
- Publication number
- CN107965353A CN107965353A CN201711195590.8A CN201711195590A CN107965353A CN 107965353 A CN107965353 A CN 107965353A CN 201711195590 A CN201711195590 A CN 201711195590A CN 107965353 A CN107965353 A CN 107965353A
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- China
- Prior art keywords
- stator blade
- jet flow
- flow groove
- cooling
- end wall
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Classifications
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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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
- 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
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- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
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- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
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- 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
Abstract
The invention discloses a kind of jet flow groove cooling structure for having and improving end wall cooling effectiveness near stator blade leading edge, including it is installed on the cooling blast chamber (12) and jet flow groove (13) of gas turbine stator blade (1) root；Wherein, along the direction of cooling stream through gas turbine stator blade (1) root, jet flow groove (13) is connected cooling blast chamber (12) along the airintake direction spontaneous combustion room (8) of high-temperature fuel gas through the fin (4) inside stator blade and with cooling blast chamber (12) outlet.During work, the cooling blast introduced from compressor enters jet flow groove (13) by cooling blast chamber (12), finally enters the mainstream region of blade grid passage from the jet flow groove outlet (14) of stator blade root.Cooling blast end wall near stator blade leading edge under the action of toe angle whirlpool and horse shoe vortex is formed about uniformly cooling down air film, is close to end wall surface flow upstream so as to be sufficiently cooled protection to the end wall near leading edge.
Description
Technical field
The present invention relates to a kind of cooling structure, and in particular to a kind of to have end wall cooling effectiveness near raising stator blade leading edge
Jet flow groove cooling structure.
Background technology
Gas turbine is widely used in generating electricity, aviation, chemical industry and machinery move as energy conversion and the main device utilized
Power field.With the high speed development of social economy, increased dramatically for energy demand gives combustion gas whirlpool with becoming increasingly conspicuous for environmental problem
The design of wheel proposes tightened up requirement.Up to the present, it is on the one hand logical in order to solve energy shortage and problem of environmental pollution
The gas turbine thermal efficiency can be significantly improved to reduce CO by crossing raising inlet gas temperature2Discharge；On the other hand fired by improving
Burning the design of room makes fuel gas temperature be evenly distributed to reduce the fuel gas temperature in combustion centre region, so as to reduce NOxGeneration.This
Two aspects are all so that the fuel gas temperature near first stage stator blades end wall significantly improves, additionally due to stator blade leading edge nearby has complexity
And strong vortex system, therefore nearby the thermic load born of end wall constantly increases stator blade, so as to seriously affect its service life and whole
A gas turbine it is safe for operation.
In order to reduce the thermic load of end wall, used in actual gas turbine among film cooling holes, the upstream line of rabbet joint and passage
Gap cooling blast cooling protection is carried out to end wall near stator blade, but stator blade edge horse shoe vortex causes the cooling blast of upstream
Beginning wall surface is sucked away from by mainstream volume, causes the jet stream that cannot be cooled of the end wall near stator blade leading edge effectively to cover.Research shows：
Stator blade upstream boundary layer fluid produces separation at the certain position of stator blade leading edge upstream and forms horse shoe vortex.A part of cooling blast is just
Inhaled by the left and right branch volume of horse shoe vortex and depart from end wall, another part cooling fluid is limited in what horse shoe vortex or so branch was formed
In region, the coverage for cooling down stream is limited in region between horse shoe vortex or so branch.The angle whirlpool of stator blade leading edge is by mainstream
High-temperature fuel gas volume, which is inhaled, directly washes away end wall surface near stator blade leading edge, in the case where long-term direct of high-temperature fuel gas is washed away, before stator blade
Nearby end wall is easily ablated for edge, seriously affects the thermal efficiency of gas turbine and safe for operation.In order to effectively reduce stator blade
The thermic load of the neighbouring end wall of leading edge, introduces one near leading edge in conventional gas turbine and is discharged to air-dispersing fenestra and utilizes the upstream line of rabbet joint
Cooling blast can suppress horse shoe vortex to a certain degree and high-temperature fuel gas that angle scrollwork suction belt enters rushes end wall near stator blade leading edge
Brush, therefore there is certain cooling protection to act on end wall near stator blade leading edge.Fig. 1 and Fig. 2 gives a kind of band combuster
Traditional stator blade endwall structure of the gas die hole 5 of the line of rabbet joint 6 and stator blade leading edge upstream between boiler.Traditional cooling structure can
Stator blade leading edge end wall cooling effectiveness nearby is improved to a certain degree, but stator blade leading edge nearby can not still obtain high thermal load regions 10
To cooling protection.
Therefore, develop new and effective cooling structure effectively to cool down the end wall near stator blade leading edge, reduce the region
Thermic load, ensureing stator blade leading edge, nearby end wall safely and effectively works with highly important engineering application value.
The content of the invention
High thermic load is born for end wall near stator blade leading edge, and can not effectively be cooled down using conventional chilling method
Feature, the present invention provides a kind of jet flow groove cooling structure for having and improving end wall cooling effectiveness near stator blade leading edge, it is utilized
The transport effect of stator blade toe angle whirlpool and upstream horse shoe vortex significantly improves the cooling effectiveness of end wall near stator blade leading edge.The present invention
The high thermal load regions of end wall near stator blade leading edge can be inherently eliminated, improve the stator blade nearby service life of end wall and guarantor
Nearby end wall safely and effectively works barrier stator blade leading edge.
The present invention adopts the following technical scheme that to realize：
It is a kind of that there is the jet flow groove cooling structure for improving end wall cooling effectiveness near stator blade leading edge, including it is installed on combustion gas whirlpool
Take turns the cooling blast chamber and jet flow groove of stator blade root；Wherein,
Cooling blast chamber is along the direction of cooling stream through gas turbine stator blade root, and jet flow groove is along high-temperature fuel gas
Airintake direction spontaneous combustion room be connected through the fin inside stator blade and with cooling blast chamber outlet.
Further improve of the invention is that cooling blast chamber includes cylindrical upper chamber and lower chambers and company
Connect the upper and lower chamber connecting pipe of two chambers.
Further improve of the invention is that cooling blast chamber diameter D values are 40-60mm.
The present invention, which further improves, to be, jet flow groove lower surface and the high thermal load regions near stator blade leading edge of jet flow groove
Radial position it is highly identical.
The present invention, which further improves, to be, the passage edge of the jet flow groove upper surface of jet flow groove and jet flow groove lower surface composition
Cooling blast direction is linear flaring type, and jet flow groove entrance height H1Less than jet flow groove outlet height H2。
Further improve of the invention is if the stator blade of gas turbine stator blade is highly H, then there is H1＜ H2≤ 0.5%H.
The present invention, which further improves, to be, jet flow groove outlet height H2Less than the horse shoe vortex vortex core heart away from end wall height H3With
The stator blade toe angle whirlpool vortex core heart is away from end wall height H4。
Further improve of the invention is that jet flow groove outlet is arranged within the segmental arc of stator blade leading edge import roundlet, and
The small radius of circle R of stator blade leading edge import has, 0.015Lax≤R≤0.08Lax, LaxFor stator blade axial direction chord length.
The present invention has following beneficial technique effect：
A kind of jet flow groove cooling structure with end wall cooling effectiveness near raising stator blade leading edge provided by the invention, its is total
Body technique thinking is to introduce a stator blade root cooling blast groove for carrying chamber to stator blade root, the stator blade root jet flow groove
Outlet is located at stator blade root surface.Wherein jet flow groove is the portion of connection cooling stream chamber and the outlet of stator blade root cooling blast groove
Point.The cooling blast introduced from compressor enters jet flow groove jet flow groove by chamber, and finally from stator blade root, cooling blast groove goes out
Mouth enters the mainstream region of blade grid passage.Cooling blast end wall near stator blade leading edge under the action of toe angle whirlpool and horse shoe vortex
It is formed about uniformly cooling down air film, it is sufficiently cold so as to carry out the end wall near leading edge to be close to end wall surface flow upstream
But protect.
(1) cooling blast chamber.The part cooling stream of compressor section is introduced into cooling blast chamber, and two volumes are larger
Chamber is connected by a pipeline, can restrain influence of the compressor section change to the outlet of cooling blast groove.In variable working condition, cooling
Jet flow groove still can provide metastable cooling source of the gas to cooling blast groove.
(2) jet flow groove.The position and direction of jet flow groove determine that cooling blast enters the speed and flow point in mainstream region
Cloth has significant impact to cooling effect.The jet flow groove lower surface of the present invention and end wall are in same radial position height, jet flow groove
Upper and lower surface composition passage along cooling blast direction have " linear flaring type " flow area.
(3) jet flow groove exports.Jet flow groove outlet height is a very important parameter, and cooling blast is exported from jet flow groove
Interact into mainstream region with mainstream, while cooling protection is carried out to end wall near stator blade.It is quiet in order to significantly improve
The cooling effectiveness of end wall, stator blade root jet flow groove outlet height should be less than the angle whirlpool vortex core heart and upstream horse shoe vortex vortex core near leaf
The height of the heart.
Further, jet flow groove lower surface and end wall surface radial position are highly identical, and jet flow groove upper surface is along cooling blast
Direction is linear flaring type.
In conclusion provided by the invention have the jet flow groove cooling knot for improving end wall cooling effectiveness near stator blade leading edge
Structure, can reduce cooling blast and be imitated in the separation near stator blade leading edge at end wall, the cooling for significantly improving end wall near stator blade leading edge
Rate, ensureing stator blade leading edge, nearby end wall safely and effectively works.Numerical result is shown in air blowing ratio when being M=1.0, uses
The jet flow groove of stator blade root of the present invention enables to the cooling effectiveness of high thermal load regions near stator blade leading edge than under routine techniques
1.3 times are improved during only with the line of rabbet joint between the air film hole and combustion chamber and turbine of stator blade leading edge upstream.The stator blade root of the present invention
Portion's cooling blast slot structure has general applicability to strengthening the stator blade leading edge end wall cooling effect in gas turbine at present.
Brief description of the drawings
Fig. 1 is the traditional combustion chamber without root jet flow groove structure-turbine meridian plane sectional view.
Stator blade and end wall schematic diagram of Fig. 2 tradition without root jet flow groove structure.
Fig. 3 is the combustion chamber with stator blade root jet flow groove-turbine meridian plane sectional view.
Fig. 4 is stator blade and end wall schematic diagram with root jet flow groove structure.
Fig. 5 is the schematic diagram of stator blade root jet flow groove and cooling blast chamber.
Fig. 6 is stator blade root jet flow groove and stator blade top view.
Fig. 7 is the stator blade leading edge flow field schematic diagram with stator blade root jet flow groove；
Fig. 8 is the jet flow groove side view of the present invention.
In figure：1- gas turbine stator blades, 2- gas turbine movable vanes, 3- wheel rims seal, the fin inside 4- stator blades, 5- stator blades
The air film hole of leading edge upstream, the line of rabbet joint between 6- combustion chambers and turbine, 7- combustion chamber wall surface air film holes, 8- combustion chambers, 9- stator blades
End wall, nearby high thermal load regions, 11- stator blade height H, 12- cooling blast chambers, 13- jet flow grooves, 14- are penetrated 10- stator blades leading edge
Launder outlet, 15- jet flow grooves upper surface, 16- jet flow grooves lower surface, 17- upper and lower chamber connecting pipes, 18- stator blade axial direction chord lengths
Lax, the small radius of circle R of 19- stator blade leading edge imports, subtended angle α, 21- cooling blast chamber diameter D, the 22- jet flow groove of 20- jet flow grooves enters
Open height H1, upper chamber's height of 23- cooling blast chambers, the length of 24- upper and lower chamber connecting pipes, 25- upper and lower chambers company
The diameter in adapter road, the height of the lower chambers of 26- cooling blast chambers, 27- jet flow groove outlet heights H2, 28- stator blade toe angles
The whirlpool vortex core heart is away from end wall height H4, the 29- horse shoe vortex vortex core hearts are away from end wall height H3, the 30- horse shoe vortex vortex core hearts, 31- stator blade toe angles
The whirlpool vortex core heart.
Embodiment
Below in conjunction with attached drawing and technical principle, the present invention is described in further detail.The present invention concrete structure referring to
Attached drawing 3~8, mentality of designing is as follows：
It is provided by the invention that there is the jet flow groove cooling for improving end wall cooling effectiveness near stator blade leading edge referring to Fig. 3 and Fig. 4
Structure, including it is installed on the cooling blast chamber 12 and jet flow groove 13 of 1 root of gas turbine stator blade；Wherein, cooling blast chamber
12 along the directions of cooling stream through 1 root of gas turbine stator blade, airintake direction spontaneous combustion of the jet flow groove 13 along high-temperature fuel gas
Room 8 is burnt through the fin 4 inside stator blade and is connected with the outlet of cooling blast chamber 12.Wherein, gas turbine stator blade 1 and combustion
Air turbine movable vane 2 passes through 3 connection of wheel rim sealing.
Compared with stator blade of the tradition without root jet flow groove structure in Fig. 1 and Fig. 2, jet flow groove 13 of the invention is independent portion
Part, can be directly mounted at 1 root of gas turbine stator blade.The jet flow groove 13 of the present invention is remarkably improved stator blade leading edge, and nearby high fever is born
The cooling effectiveness in lotus region 10.
Referring to Fig. 5 and Fig. 6, jet flow groove of the invention outlet 14 is located at the root of gas turbine stator blade 1.Jet flow groove 13 and cold
But fluidic chambers 12 are using the separately machined rear processing method assembled.Segmental arc of the jet flow groove outlet 14 in stator blade leading edge import roundlet
Within, and the small radius of circle R 19 of stator blade leading edge import has, 0.015Lax≤R≤0.08Lax, LaxFor stator blade axial direction chord length.Cooling is penetrated
Flowing chamber 12 includes cylindrical upper chamber and lower chambers and connects the upper and lower chamber connecting pipe 17 of two chambers, cooling
Fluidic chambers diameter D21 values are 40-60mm.Wherein, reference numeral 23 represents the diameter of upper and lower chamber connecting pipe, and 24 represent
The length of upper and lower chamber connecting pipe, 25 represent the diameter of upper and lower chamber connecting pipe, and 26 represent the cavity of resorption of cooling blast chamber
The height of room.
Referring to Fig. 7, it is upward to be close to end wall surface under the action of toe angle whirlpool and horse shoe vortex for the cooling blast of jet flow groove 13
Downstream carries out cooling protection to high thermal load regions 10 near stator blade leading edge.Therefore it must assure that jet flow groove outlet height H2
27 are less than the horse shoe vortex vortex core heart away from end wall height H329 and the stator blade toe angle whirlpool vortex core heart away from end wall height H428, i.e. H2＜ H3,
H2＜ H4, wherein, reference numeral 30 represents the horse shoe vortex vortex core heart, and 31 represent the stator blade toe angle whirlpool vortex core heart.
Referring to Fig. 8, the jet flow groove 13 of stator blade root of the present invention is by jet flow groove upper surface 15 and jet flow groove lower surface 16 and side
Face forms.Jet flow groove lower surface 16 and stator blade end wall 9 are in same radial position, i.e., highly identical.The jet flow groove upper table of the present invention
The passage that face 15 and jet flow groove lower surface 16 form has the flow area of linear flaring type along cooling blast direction, therefore penetrates
Chute entrance height H122 small jet flow groove outlet height H227, i.e. H1＜ H2≤ 0.5%H, H are stator blade height.
Determine the horse shoe vortex vortex core heart away from end wall height H by numerical simulation first329 and the stator blade toe angle whirlpool vortex core heart away from
End wall height H428, the distribution with reference to cooling flow under conditions of known air blowing ratio determines jet flow groove outlet height H227；Root
According to fixed jet flow groove outlet height H227 design jet flow groove entrance height H122 so that 14 distribution of jet flow groove outlet is equal
It is even.Jet flow groove outlet 14 should be within the segmental arc of stator blade leading edge import roundlet.First according to numerical simulation, it is attached to obtain stator blade leading edge
The limiting streamline distribution of nearly External airflow field, with reference to the radian of jet flow groove outlet 14, ensures cooling stream direction and stator blade leading edge root
The limiting streamline direction of end wall unanimously determines the subtended angle α 20 of root jet flow groove.
The technical principle of the present invention is as follows：
Referring to Fig. 1 and Fig. 2, in the gas turbine, the line of rabbet joint 6 between traditional stator blade leading edge end wall combuster and turbine
Cooling protection is carried out to end wall near stator blade leading edge with the air film hole 5 of stator blade leading edge upstream.Referring to Fig. 4, research shows in stator blade
There are horse shoe vortex and toe angle whirlpool near leading edge to cause the line of rabbet joint 6 between combustion chamber and turbine and the air film hole of stator blade leading edge upstream
The cooling blast of 7 discharges departs from 9 surface of stator blade end wall, therefore result in stator blade leading edge high thermal load regions 10 nearby.Study table
It is bright：The cooling effectiveness of end wall near stator blade leading edge can be significantly increased by the disengaging for the slave end wall for reducing cooling blast.This hair
Bright stator blade root jet flow groove structure is penetrated the cooling of stator blade root jet flow groove using the horse shoe vortex near stator blade leading edge and angle whirlpool
Stream is close to this end wall and is transported to the scope of upstream bigger, so as to significantly reduce disengaging of the cooling blast from end wall, significantly increases
The cooling effectiveness of end wall near big stator blade leading edge.
During work, enter the jet flow groove of linear flaring type by cooling blast chamber 12 from the cooling air-flow that compressor introduces
13.The jet flow groove outlet 14 of the present invention should be within the segmental arc of stator blade leading edge import roundlet, and jet flow groove outlet height H227 is small
In the horse shoe vortex vortex core heart away from end wall height H329 and the stator blade toe angle whirlpool vortex core heart away from end wall height H428, therefore jet flow groove
Cooling blast is close to end wall under the action of angle whirlpool and horse shoe vortex and is upstream moved, and is being formed near stator blade leading edge at end wall uniformly
Cooling air film significantly improves the cooling effectiveness in the region.Research finds that the jet flow groove jet flow groove of linear flaring type makes cooling blast
It is distributed more uniformly in jet flow groove outlet 14, therefore end wall forms uniform cooling air film and obtains more near stator blade leading edge
High cooling effectiveness.
Cooling blast can be greatly decreased quiet in preliminary proof, stator blade root jet flow groove of the invention to numerical simulation result
Leaf leading edge nearby departs from end wall and significantly improves the cooling effectiveness of end wall near stator blade leading edge.
Claims (8)
1. a kind of have the jet flow groove cooling structure for improving end wall cooling effectiveness near stator blade leading edge, it is characterised in that including peace
Cooling blast chamber (12) and jet flow groove (13) loaded on gas turbine stator blade (1) root；Wherein,
Cooling blast chamber (12) along the direction of cooling stream through gas turbine stator blade (1) root, jet flow groove (13) along
The airintake direction spontaneous combustion room (8) of high-temperature fuel gas is exported through the fin (4) inside stator blade and with cooling blast chamber (12)
It is connected.
A kind of 2. jet flow groove cooling knot with end wall cooling effectiveness near raising stator blade leading edge according to claim 1
Structure, it is characterised in that cooling blast chamber (12) includes cylindrical upper chamber and lower chambers and connects two chambers
Upper and lower chamber connecting pipe (17).
A kind of 3. jet flow groove cooling knot with end wall cooling effectiveness near raising stator blade leading edge according to claim 2
Structure, it is characterised in that cooling blast chamber diameter D values are 40-60mm.
A kind of 4. jet flow groove cooling knot with end wall cooling effectiveness near raising stator blade leading edge according to claim 1
Structure, it is characterised in that the footpath of the jet flow groove lower surface (16) of jet flow groove (13) and high thermal load regions (10) near stator blade leading edge
It is identical to position height.
A kind of 5. jet flow groove cooling knot with end wall cooling effectiveness near raising stator blade leading edge according to claim 4
Structure, it is characterised in that the passage edge cooling of the jet flow groove upper surface (15) of jet flow groove (12) and jet flow groove lower surface (16) composition
Jet direction is linear flaring type, and jet flow groove entrance height H1(22) it is less than jet flow groove outlet height H2(27)。
A kind of 6. jet flow groove cooling knot with end wall cooling effectiveness near raising stator blade leading edge according to claim 5
Structure, it is characterised in that set the stator blade height of gas turbine stator blade (1) as H, then have H1＜ H2≤ 0.5%H.
A kind of 7. jet flow groove cooling knot with end wall cooling effectiveness near raising stator blade leading edge according to claim 4
Structure, it is characterised in that jet flow groove outlet height H2(27) it is less than the horse shoe vortex vortex core heart away from end wall height H3(29) and stator blade toe angle
The whirlpool vortex core heart is away from end wall height H4(28)。
A kind of 8. jet flow groove cooling knot with end wall cooling effectiveness near raising stator blade leading edge according to claim 4
Structure, it is characterised in that jet flow groove outlet (14) is arranged within the segmental arc of stator blade leading edge import roundlet, and stator blade leading edge import is small
Radius of circle R has, 0.015Lax≤R≤0.08Lax, LaxFor stator blade axial direction chord length.
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|---|---|---|---|
| CN201711195590.8A CN107965353A (en) | 2017-11-24 | 2017-11-24 | It is a kind of that there is the jet flow groove cooling structure for improving end wall cooling effectiveness near stator blade leading edge |
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|---|---|---|---|
| CN201711195590.8A CN107965353A (en) | 2017-11-24 | 2017-11-24 | It is a kind of that there is the jet flow groove cooling structure for improving end wall cooling effectiveness near stator blade leading edge |
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| CN201711195590.8A Pending CN107965353A (en) | 2017-11-24 | 2017-11-24 | It is a kind of that there is the jet flow groove cooling structure for improving end wall cooling effectiveness near stator blade leading edge |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110056397A (en) * | 2019-06-05 | 2019-07-26 | 上海电气燃气轮机有限公司 | Gas turbine wheel rim sealing device and gas turbine |
| CN111335967A (en) * | 2020-03-03 | 2020-06-26 | 清华大学 | Turbine static wheel disc, gas turbine and design method of end wall lateral outflow hole |
| CN112747929A (en) * | 2020-11-30 | 2021-05-04 | 南京航空航天大学 | Flow channel adjusting mechanism of cascade test bed for expanding adjusting range of cascade attack angle |
| CN113006880A (en) * | 2021-03-29 | 2021-06-22 | 南京航空航天大学 | Novel cooling device for end wall of turbine blade |
| CN113153459A (en) * | 2021-03-26 | 2021-07-23 | 西北工业大学 | Slot partition plate structure capable of improving cooling efficiency of front edge end wall of turbine stationary blade |
| CN113236373A (en) * | 2021-06-07 | 2021-08-10 | 西北工业大学 | Tesla valve-based air film hole channel structure and application thereof to turbine blade leading edge |
| CN113356932A (en) * | 2021-07-07 | 2021-09-07 | 西安交通大学 | Air film cooling composite hole structure for turbine blade and turbine blade |
| CN113933061A (en) * | 2021-09-30 | 2022-01-14 | 中国联合重型燃气轮机技术有限公司 | Stationary blade simulator and combustion chamber test device with same |
| CN113933061B (en) * | 2021-09-30 | 2024-04-19 | 中国联合重型燃气轮机技术有限公司 | Static blade simulator and combustion chamber test device with same |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110056397A (en) * | 2019-06-05 | 2019-07-26 | 上海电气燃气轮机有限公司 | Gas turbine wheel rim sealing device and gas turbine |
| CN110056397B (en) * | 2019-06-05 | 2023-11-10 | 上海电气燃气轮机有限公司 | Gas turbine rim sealing device and gas turbine |
| CN111335967A (en) * | 2020-03-03 | 2020-06-26 | 清华大学 | Turbine static wheel disc, gas turbine and design method of end wall lateral outflow hole |
| CN112747929A (en) * | 2020-11-30 | 2021-05-04 | 南京航空航天大学 | Flow channel adjusting mechanism of cascade test bed for expanding adjusting range of cascade attack angle |
| CN113153459A (en) * | 2021-03-26 | 2021-07-23 | 西北工业大学 | Slot partition plate structure capable of improving cooling efficiency of front edge end wall of turbine stationary blade |
| CN113006880A (en) * | 2021-03-29 | 2021-06-22 | 南京航空航天大学 | Novel cooling device for end wall of turbine blade |
| CN113236373A (en) * | 2021-06-07 | 2021-08-10 | 西北工业大学 | Tesla valve-based air film hole channel structure and application thereof to turbine blade leading edge |
| CN113236373B (en) * | 2021-06-07 | 2022-04-08 | 西北工业大学 | Tesla valve-based air film hole channel structure and application thereof to turbine blade leading edge |
| CN113356932A (en) * | 2021-07-07 | 2021-09-07 | 西安交通大学 | Air film cooling composite hole structure for turbine blade and turbine blade |
| CN113933061A (en) * | 2021-09-30 | 2022-01-14 | 中国联合重型燃气轮机技术有限公司 | Stationary blade simulator and combustion chamber test device with same |
| CN113933061B (en) * | 2021-09-30 | 2024-04-19 | 中国联合重型燃气轮机技术有限公司 | Static blade simulator and combustion chamber test device with same |
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