CN107701247A - A kind of gas turbine guider inner ring impinging cooling structure, gas turbine - Google Patents
A kind of gas turbine guider inner ring impinging cooling structure, gas turbine Download PDFInfo
- Publication number
- CN107701247A CN107701247A CN201710981810.3A CN201710981810A CN107701247A CN 107701247 A CN107701247 A CN 107701247A CN 201710981810 A CN201710981810 A CN 201710981810A CN 107701247 A CN107701247 A CN 107701247A
- Authority
- CN
- China
- Prior art keywords
- inner ring
- cooling
- gas turbine
- guider
- impinging cooling
- 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.)
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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
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Abstract
The present invention relates to a kind of gas turbine guider inner ring impinging cooling structure, including impinging cooling casket plate, gas turbine guider and combustor exit wall, the inner ring combustion gas side wall of combustor exit wall and gas turbine guider overlaps and in lap-joint formed with gap, impinging cooling casket plate, combustor exit wall and guider inner ring wall surround cold air chamber, guider inner ring cold air side wall is provided with impinging cooling boss, and multiple rows of impact cold air hole is distributed with the face of cylinder of impinging cooling casket plate；High pressure cold through the boss in the impinging cooling guider inner ring of impinging cooling hole, after flowed out through gap, cooling air film is formed in guider inner ring combustion gas side wall, so as to reach the efficient cooling to guider inner ring, it is therefore prevented that the risk that high-temperature fuel gas corrodes.Promote the use of, play the role of to the Performance And Reliability for improving engine positive in modern gas turbines.
Description
Technical field
The present invention relates to high-temperature component of gas turbine turbine field, in particular, is related to a kind of gas turbine guider
Inner ring impinging cooling structure, it is possible to achieve the efficient cooling to nozzle ring inner ring, reduce thermal stress, improve the longevity of engine
Life and reliability.
Background technology
In order to improve the performance of gas turbine, temperature improves constantly before high-pressure turbine.The whirlpool of advanced aviation turbofan engine
Wheel inlet gas temperature has reached 1800K~2050K, considerably beyond the allowable temperature of existing high temperature alloy.It is high to ensure
Press the safe operation of turbine, it is necessary to implement effective cooling to reduce the tube wall temperature of high-pressure turbine guider.
Generally, gap be present between aeroengine combustor buring room and high-pressure turbine, to prevent high-temperature fuel gas from passing through the gap
Invasion, high temperature corrosion is produced to internal structure, one high-voltage secondary air-flow can be introduced it is obturaged.Meanwhile high-voltage secondary
Cooling air-flow can be cooled down by the structure to circuit wall inside and outside high-pressure turbine guider.But combustion chamber and high pressure
Gap between nozzle ring is due to that the manifold formula that goes out of cold air is limited by both cooperations, no caused by installation coordinates
Metal wall can be attached well, it is impossible to which inner and outer ring casing is cooled down well.Therefore, reasonably design seal structure and cooling
Structure has important influence to the service life and engine overall performance of protecting high-pressure turbine.Conventional engine is guarantor
Demonstrate,prove the safe operation of engine, generally realized by increasing air conditioning quantity and obturage and effectively cool down, but increase air conditioning quantity will necessarily
Reduce the overall performance of engine.In order to further improve the performance of engine and competitiveness, there is an urgent need to a kind of new structure
On the premise of the efficient cooling for realizing turbine leading edge, cooling air dosage is reduced.
The content of the invention
For shortcoming and defect present in above-mentioned prior art, the present invention is intended to provide a kind of be used for modern gas turbines
The arrangement of high-temperature component, especially gas turbine guider inner ring cooling, by designing a kind of new cooling structure, changes
Become traditional type of cooling, improve the cooling effect of gas turbine guider inner metal wall, improve engine performance and
Reliability.
To realize the target, the technical solution adopted by the present invention is：
A kind of gas turbine guider inner ring impinging cooling structure, including gas turbine guider and combustor exit wall
Face, the inner ring combustion gas side wall overlap joint of the combustor exit wall and the gas turbine guider and lap-joint formed with
Gap, it is characterised in that
The cooling structure also includes the impinging cooling casket plate of an overall cylindrical surface structure in a ring, the impinging cooling casket
Plate upstream links together with Combustion outlet wall, and downstream and the inner ring installation section of gas turbine guider link together, and
The inner ring cold air side wall of the impinging cooling casket plate and the cooled guide device is spaced apart, so as to the impinging cooling
Casket plate, combustor exit wall and gas turbine guider inner ring wall surround a cold air chamber；
It is circumferentially distributed in the inner ring cold air side wall of the gas turbine guider to have some and guider blade profile shape
Essentially identical boss, multiple rows of impact cold air hole, the impact cold air hole is distributed with the face of cylinder of the impinging cooling casket plate
Export direction it is relative with the boss；
The high pressure cold of air system impacts the cooled guide device through the impinging cooling hole on the impinging cooling casket plate
Inner ring cold air side wall on boss, the cold air after impinging cooling settles out in the cold air chamber, after through described
Gap is flowed out, and cooling air film is formed in the inner ring combustion gas side wall of the gas turbine guider.
Preferably, the upstream of the impinging cooling casket plate is fixed on combustion chamber wall surface by the form on flange or inclined-plane
On, downstream is provided with installation side, is fixed in by installing side on gas turbine guider inner ring installation section.
Preferably, the impinging cooling casket plate is linked together with combustor exit wall by way of welding, is prevented
Cold air is revealed from lap-joint.
Selectable, the impinging cooling casket plate is overlapped on one with combustor exit wall by the fit system of interference
Rise, there are certain flatness and depth of parallelism requirement in the two surface coordinated, prevents cold air from being revealed from lap-joint.
Preferably, the thickness of the impinging cooling casket plate subtracts in 0.8mm or so as far as possible on the basis of proof strength requirement
Light weight, improve engine performance.
Preferably, impinging cooling hole periodic distribution is on impinging cooling casket plate, combustion described in the face of impinging cooling hole
Air turbine guider inner ring boss.
Preferably, impinging cooling hole each cycle is distributed along below boss edge, boss leading edge, pressure upper thread and
Trailing edge distribution is closeer, is distributed in suction upper thread diluter.
Preferably, the impinging cooling bore portion is distributed in the high lower section of gas turbine guide channel thermic load.
Preferably, the diameter in the impinging cooling hole is in 0.6mm or so, to realize preferable cooling effect.
Preferably, the distance of the impinging cooling casket plate and the gas turbine guider inner ring wall 2mm to 8mm it
Between, it is relevant with air conditioning quantity and impinging cooling bore dia, ensure preferable impinging cooling effect.
Preferably, the combustor exit wall is overlapped on the gas turbine guider combustion gas side wall, cooling air-flow
Downstream wall is directly cooled down by gap between the two.
Preferably, the impinging cooling casket plate is bolted one with gas turbine guider inner ring installation section
Rise.
Present invention also offers a kind of impinging cooling casket plate, is rushed suitable for the above-mentioned gas turbine guider inner ring of the present invention
Hit cooling structure.
Present invention also offers a kind of gas turbine for including above-mentioned gas turbine guider inner ring impinging cooling structure.
In the impinging cooling casket harden structure of the present invention and combustor exit wall and gas turbine guider in combination
Ring structure improves the cooling effect of gas turbine inner ring, compared with existing form, has the advantage that：1. cooling air-flow passes through
Impinging cooling casket plate impinging cooling gas turbine guider inner ring, compared to traditional heat convection, improves cooling effectiveness, so as to
The temperature of metal wall is reduced, reduces thermal stress.2. the cooling structure is simple, dismounting is easily installed, it is convenient to cooling requirement
Implement impinging cooling in different regions.3. the risk of high-temperature fuel gas and the direct contact position of internal structure is obstructed, even if there is combustion gas
Invasion, the impinging cooling casket plate can play the danger that barrier high-temperature fuel gas directly contacts with internal structure.
Brief description of the drawings
Fig. 1 is the gas turbine guider inner ring impinging cooling structural representation of the present invention；
Fig. 2 is the impinging cooling casket plate sectional view of the present invention.
Embodiment
With reference to embodiment, the present invention is described in further detail, and following instance is explanation of the invention and this
Invention is not limited to following instance.
As shown in figure 1, the present invention is used for the structure of gas turbine guider inner ring impinging cooling, including impinging cooling casket plate
1st, gas turbine guider 2 and combustor exit wall 3.The upstream of impinging cooling casket plate 1 is provided with flange 101, can pass through welding
Mode be fixed on combustor exit 301, can also using interference fit by the way of overlap.When using interference fit
When, it need to ensure to coordinate flange 101 and combustor exit wall to have certain planarity requirements, and the depth of parallelism that both coordinate will
Ask, to prevent cold air from being revealed at this.The downstream of impinging cooling casket plate 1 is provided with installation side 102, installs side 102 and gas turbine
Guider inner ring installation section 202 is bolted together.Be provided with impinging cooling hole 103 on impinging cooling casket plate 1, for pair
The boss 203 being arranged in guider inner ring cold air side wall implements impinging cooling.Impinging cooling boss 203 by guider inside
Cooling Design causes, and in blade profile shape, therefore arrangement of the impinging cooling hole 103 on impinging cooling casket plate is also into blade profile shape point
Cloth.Impinging cooling casket plate 1, gas turbine guider inner ring 2 and combustor exit wall 3 surround a cold air chamber 4.Combustion chamber
Outlet wall 301 is overlapped on the combustion gas side of gas turbine guider inner ring 201, forms gap between the two, also can be in combustion gas whirlpool
Boss circumferentially is set in wheel guider inner ring 201, increases the size in gap.
The flow direction of cold air and combustion gas is designated in Fig. 1, the high pressure cold of air system is by impinging cooling casket plate 1
The impinging cooling guider inner ring boss 203 of impinging cooling hole 103, reduce the temperature of guider inner ring.It is cold after impinging cooling
Gas settles out in cold air chamber 4.Then, cold air is by the gap between combustor exit wall 301 and guider inner ring
Outflow, gaseous film control is carried out to guider inner ring combustion gas side wall, further reduces metallic surface temperature, so as to reach to being oriented to
The efficient cooling of device inner ring.Simultaneously as the barrier of impinging cooling casket plate, also will not be to inside even if there is high-temperature fuel gas invasion
Structure produces high temperature corrosion.
In summary, the present invention uses a kind of new impact cooling structure, changes the cooling side of nozzle ring inner ring
Formula, improve the cooling of guider inner ring, it is therefore prevented that the risk that high-temperature fuel gas corrodes.Promoted the use of in modern gas turbines,
Play the role of to the Performance And Reliability for improving engine positive.
Furthermore, it is necessary to illustrate, the specific embodiment described in this specification, the shape of its parts and components, it is named
Title etc. can be different.The equivalent or simple change that all construction, feature and principles according to described in inventional idea of the present invention are done, is wrapped
Include in the protection domain of patent of the present invention.Those skilled in the art can be to described specific implementation
Example is made various modifications or supplement or substituted using similar mode, structure without departing from the present invention or surmounts this
Scope as defined in the claims, protection scope of the present invention all should be belonged to.
Claims (9)
1. a kind of gas turbine guider inner ring impinging cooling structure, including gas turbine guider and combustor exit wall,
The inner ring combustion gas side wall of the combustor exit wall and the gas turbine guider is overlapped and formed in lap-joint seamed
Gap, it is characterised in that
The cooling structure also includes the impinging cooling casket plate of an overall cylindrical surface structure in a ring, the impinging cooling casket plate
Upstream is tightly connected with the combustor exit wall, downstream and the inner ring installation section connection of the gas turbine guider, and
The inner ring cold air side wall of the impinging cooling casket plate and the cooled guide device is spaced apart, so as to the impinging cooling
Casket plate, combustor exit wall and gas turbine guider inner ring wall surround a cold air chamber；
In the inner ring cold air side wall of the gas turbine guider it is circumferentially distributed have it is some basic with guider blade profile shape
Identical boss, multiple rows of impact cold air hole is distributed with the face of cylinder of the impinging cooling casket plate, and the impact cold air hole goes out
Mouth direction is relative with the boss.
2. the cooling structure according to the claims, it is characterised in that the upstream of the impinging cooling casket plate is by turning over
The form on side or inclined-plane is fixed on the combustor exit wall, downstream be provided with installation side, by it is described installation side by its
It is fixed on the inner ring installation section of the gas turbine guider.
3. the cooling structure according to the claims, it is characterised in that impinging cooling casket plate upstream flange passes through
The form sealing of welding is fixed on combustor exit wall.
4. the cooling structure according to the claims, it is characterised in that impinging cooling casket plate upstream flange passes through
The mode of interference is together with combustor exit wall lap hermetically.
5. according to the cooling structure described in the claims 4, it is characterised in that the impinging cooling casket plate upstream flange and combustion
The flatness of room outlet wall and the depth of parallelism of both cooperations are burnt, cold air should be caused not let out in the lap-joint of the two
Dew.
6. the cooling structure according to the claims, it is characterised in that the impinging cooling hole is periodically distributed in
On the impinging cooling casket plate, impinging cooling is carried out to the boss of the gas turbine guider inner ring.
7. the cooling structure according to the claims, it is characterised in that the impinging cooling hole is along the gas turbine
The circle of outer rim distribution one or two circles of guider inner ring boss, can implement effective cooling, reducing heat should to guider root
Power.
8. the cooling structure according to the claims, it is characterised in that the impinging cooling hole is in the gas turbine
Leading edge, trailing edge and the pressure EDS maps comparatively dense of guider inner ring boss, suction surface is more sparse, can also be uniformly distributed, mainly
According to the design of guider inner ring thermic load.
9. the cooling structure according to the claims, it is characterised in that also there is part in the impinging cooling hole according to need
It is opened in the high region of guide channel thermic load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710981810.3A CN107701247B (en) | 2017-10-20 | 2017-10-20 | Gas turbine guider inner ring impingement cooling structure and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710981810.3A CN107701247B (en) | 2017-10-20 | 2017-10-20 | Gas turbine guider inner ring impingement cooling structure and gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107701247A true CN107701247A (en) | 2018-02-16 |
| CN107701247B CN107701247B (en) | 2021-03-09 |
Family
ID=61182865
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710981810.3A Active CN107701247B (en) | 2017-10-20 | 2017-10-20 | Gas turbine guider inner ring impingement cooling structure and gas turbine |
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| Country | Link |
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| CN (1) | CN107701247B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5358374A (en) * | 1993-07-21 | 1994-10-25 | General Electric Company | Turbine nozzle backflow inhibitor |
| CN205876397U (en) * | 2016-07-29 | 2017-01-11 | 中国科学院工程热物理研究所 | Turbine disc cavity configuration with obturage and cool off guide plate |
| CN107060896A (en) * | 2017-05-08 | 2017-08-18 | 中国航发湖南动力机械研究所 | Turbine guider link construction and the gas-turbine unit with it |
| CN107143385A (en) * | 2017-06-26 | 2017-09-08 | 中国科学院工程热物理研究所 | A kind of gas turbine guider leading edge installs side structure and the gas turbine with it |
-
2017
- 2017-10-20 CN CN201710981810.3A patent/CN107701247B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5358374A (en) * | 1993-07-21 | 1994-10-25 | General Electric Company | Turbine nozzle backflow inhibitor |
| CN205876397U (en) * | 2016-07-29 | 2017-01-11 | 中国科学院工程热物理研究所 | Turbine disc cavity configuration with obturage and cool off guide plate |
| CN107060896A (en) * | 2017-05-08 | 2017-08-18 | 中国航发湖南动力机械研究所 | Turbine guider link construction and the gas-turbine unit with it |
| CN107143385A (en) * | 2017-06-26 | 2017-09-08 | 中国科学院工程热物理研究所 | A kind of gas turbine guider leading edge installs side structure and the gas turbine with it |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113006880B (en) * | 2021-03-29 | 2022-02-22 | 南京航空航天大学 | Cooling device for end wall of turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107701247B (en) | 2021-03-09 |
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