CN107013939A - Burner wall passage cooling system - Google Patents
Burner wall passage cooling system Download PDFInfo
- Publication number
- CN107013939A CN107013939A CN201611016285.3A CN201611016285A CN107013939A CN 107013939 A CN107013939 A CN 107013939A CN 201611016285 A CN201611016285 A CN 201611016285A CN 107013939 A CN107013939 A CN 107013939A
- Authority
- CN
- China
- Prior art keywords
- jacket wall
- combustion liner
- cooling duct
- scheme
- duct
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/005—Combined with pressure or heat exchangers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application provides the combustion liner (110) for being used together with gas-turbine unit (10).Combustion liner (110) may include completely or partially to extend to the jacket wall (140) of rear end from head end, be positioned in jacket wall and extend to multiple jacket wall cooling ducts (130) of outlet and multiple bushing return ducts from entrance.The outlet of jacket wall cooling duct (130) can be positioned near bushing return duct.
Description
The statement for the research or development supported on federal government
The present invention is to support to complete under the contract number DE-FE0023965 authorized by USDOE by U.S. government.Political affairs
Mansion has some rights in the present invention.
Technical field
The application and the patent of gained relate generally to gas-turbine unit, and more specifically, are related to burner wall
Passage cooling system, the jacket wall cooling that there is the burner wall passage cooling system jacket wall around burner to position is logical
Road, to provide wall cooling and purging or film cooling stream.
Background technology
In gas-turbine unit, hot combustion gas generally flow along hot gas path from burner through transition piece
And flow in turbine, to produce useful work.Because the burning stream of higher temperature generally results in the performance of gas-turbine unit, effect
The raising of rate and general power output, so the component of experience higher temperature burning stream must be cooled, to allow gas turbine to send out
Motivation is operated at a temperature of such a raising, without the life-span of damage or reduction.
One example of the hot gas path component that should be cooled down is combustion liner.Specifically, mixed by Fuel-air
High-temperature stream caused by burning of the thing in burner is guided through combustion liner.The existing method of cooling bushing includes difference
Film cooling technology of type etc..These cooling streams can be sent in bushing or hot gas path by entire system pressure drop.Specifically
For, air can be sent to burner from compressor or elsewhere via somewhat complicated a series of heat exchangers and pipeline.
Such a film cooling technology can be effective, but cooling stream can not then be utilized to reduce unexpected discharge.Moreover, such a cold
But stream can be expensive, because may need outside cool down before the use.
Thus expect cooling combustion liner and/or other kinds of hot gas path component improved cooling system and
Method.Such a improved cooling system and method can be exported in system and efficiency it is overall improve in the case of provide enough cold
But.
The content of the invention
The application and the patent of gained thus provide a kind of burner lining for being used to be used together with gas-turbine unit
Set.Combustion liner may include completely or partially to extend to the jacket wall of rear end from head end, be positioned in jacket wall and from entering
Mouth extends to multiple jacket wall cooling ducts of outlet and multiple bushing return ducts.The outlet of jacket wall cooling duct can be determined
Position is near bushing return duct.
The application and the patent of gained thus provide a kind of side of the component of the burner in cooling combustion turbine engine
Method.This method may include following steps：Air stream is provided to the wall of component；Make multiple cold in the wall that air flow passes through component
But passage；Air is set to be flowed to from the cooling duct in the wall of component in return duct；With air is flowed in return duct separately
One component.
The application and the patent of gained also provide a kind of component for being used together with gas-turbine unit.The component
It may include completely or partially to extend to the component wall of rear end from head end, be positioned in component wall and extend to outlet from entrance
Multiple component wall cooling ducts and multiple component return ducts.The outlet of component wall cooling duct can be positioned on component recurrent canal
Near road.
Technical scheme 1：A kind of combustion liner for being used together with gas-turbine unit, including：
Jacket wall, it completely or partially extends to rear end from head end；
Multiple jacket wall cooling ducts, it is positioned in the jacket wall；
Wherein, the multiple jacket wall cooling duct extends to outlet from entrance；With
Multiple bushing return ducts；
Wherein, the outlet of the multiple jacket wall cooling duct is positioned near the multiple bushing return duct.
Technical scheme 2：Combustion liner according to technical scheme 1, wherein, the multiple bushing return duct is with enclosing
The head end pipeline communication positioned around the head end of the jacket wall.
Technical scheme 3：Combustion liner according to technical scheme 2, wherein, the jacket wall includes and the head end
Multiple purge holes of pipeline communication.
Technical scheme 4：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct
Entrance is orientated as and the air flow communication in the flow path in flowing sleeve.
Technical scheme 5：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct bag
Include substantially square shape or substantially round shape.
Technical scheme 6：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct bag
Include the length of about 2 to 5 inches (about 5.1 to 12.7 centimetres).
Technical scheme 7：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct bag
Include the diameter of about 0.060 inch (about 1.524 millimeters) to about 0.080 inch (about 2.0 millimeters).
Technical scheme 8：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct bag
Include the inlet diameter of about 0.065 inch (about 1.65 millimeters) and the outlet of about 0.075 inch (about 1.91 millimeters)
Diameter.
Technical scheme 9：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct can
Positioned in a plurality of columns in the jacket wall.
Technical scheme 10：Combustion liner according to technical scheme 9, wherein, eight to 15 the multiple linings
Jacket wall cooling duct can be positioned on each in the multiple row in the jacket wall in.
Technical scheme 11：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct
It is casted into the jacket wall.
Technical scheme 12：Combustion liner according to technical scheme 1, wherein, the multiple jacket wall cooling duct
It is by adding manufacturing process formation.
Technical scheme 13：Combustion liner according to technical scheme 1, wherein, the jacket wall surrounds combustion chamber.
Technical scheme 14：A kind of method of component in cooling combustion turbine engine, including：
Air stream is provided to the wall of the component；
Make multiple cooling ducts in the wall that air flow passes through the component；
Air is set to be flowed to from the multiple cooling duct in the wall of the component in return duct；With
Air is set to flow to another component in the return duct.
Technical scheme 15：Cooling means according to technical scheme 14, wherein, air is flowed in the return duct
To the step of another component include air is flowed to head end pipeline in the return duct.
Technical scheme 16：A kind of component for being used together with gas-turbine unit, including：
Component wall, it completely or partially extends to rear end from head end；
Multiple component wall cooling ducts, it is positioned in the component wall；
Wherein, the multiple component wall cooling duct extends to outlet from entrance；With
Multiple component return ducts；
Wherein, the outlet of the multiple component wall cooling duct is positioned near the multiple component return duct.
Technical scheme 17：Component according to technical scheme 16, wherein, the component includes combustion liner.
Technical scheme 18：Component according to technical scheme 16, wherein, the multiple component wall cooling duct include into
Mouth and outlet, and wherein, the outlet of the multiple component wall cooling duct is positioned near the multiple component return duct.
Technical scheme 19：Component according to technical scheme 16, wherein, the multiple component return duct is with surrounding institute
State the pipeline communication of component wall positioning.
Technical scheme 20：Component according to technical scheme 16, wherein, the multiple component wall cooling duct includes big
The length of about 2 to 5 inches (about 5.1 to 12.7 centimetres).
Scheme 1：A kind of combustion liner 110 for being used together with gas-turbine unit 10, including：
Jacket wall 140, it completely or partially extends to rear end 115 from head end 105；
Multiple jacket wall cooling ducts 130, it is positioned in the jacket wall 140；
Wherein, the multiple jacket wall cooling duct 130 extends to outlet 160 from entrance 150；With
Multiple bushing return ducts 170；
Wherein, the outlet of the multiple jacket wall cooling duct 130 is positioned near the multiple bushing return duct 170.
Scheme 2：Combustion liner 110 according to scheme 1, wherein, the multiple bushing return duct 170 is with surrounding
The head end pipeline 180 that the head end 105 of the jacket wall 140 is positioned is connected.
Scheme 3：Combustion liner 110 according to scheme 2, wherein, the jacket wall 140 includes and the head end pipe
Multiple purge holes 190 that road 180 is connected.
Scheme 4：Combustion liner 110 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 enters
Mouth 150 is orientated as to be connected with the air stream 20 in the flow path 75 in flowing sleeve 70.
Scheme 5：Combustion liner 110 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 includes
Substantially square shape or substantially round shape.
Scheme 6：Combustion liner 110 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 includes
The length of about 2 to 5 inches (about 5.1 to 12.7 centimetres).
Scheme 7：Combustion liner 100 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 includes
The diameter of about 0.060 inch (about 1.524 millimeters) to about 0.080 inch (about 2.0 millimeters).
Scheme 8：Combustion liner 100 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 includes
The inlet diameter of about 0.065 inch (about 1.65 millimeters) and the outlet of about 0.075 inch (about 1.91 millimeters) are straight
Footpath.
Scheme 9：Combustion liner 100 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 can be
Positioned in a plurality of columns in the jacket wall 140.
Scheme 10：Combustion liner 110 according to scheme 9, wherein, eight to 15 the multiple jacket walls are cold
But passage 130 can be positioned on each in the multiple row in the jacket wall 140 in.
Scheme 11：Combustion liner 110 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 is
It is casted into the jacket wall.
Scheme 12：Combustion liner 110 according to scheme 1, wherein, the multiple jacket wall cooling duct 130 is
By adding manufacturing process formation.
Scheme 13：Combustion liner 110 according to scheme 1, wherein, the jacket wall 140 surrounds combustion chamber 85.
Scheme 14：A kind of method of component 110 in cooling combustion turbine engine 10, including：
Air stream 20 is provided to the wall 140 of the component 110；
Air 20 is set to flow through multiple cooling ducts 130 in the wall 140 of the component 110；
Air 20 is set to be flowed to from the multiple cooling duct 130 in the wall 140 of the component 110 in return duct 170；With
Air 20 is set to flow to another component in the return duct 170.
Scheme 15：Cooling means according to scheme 14, wherein, air 20 is flowed in the return duct 170
The step of another component, includes making air 20 flow to head end pipeline 180 in the return duct 170.
After the following detailed description that some accompanying drawings of combination and appended claims are made is read, the application and gained are special
These and other features of profit and improvement will become obvious to those skilled in the art.
Brief description of the drawings
Fig. 1 is the schematic diagram of gas-turbine unit, and it shows compressor, burner, turbine and load.
Fig. 2 is the schematic diagram for the burner that can be used together with Fig. 1 gas-turbine unit.
Fig. 3 is the perspective view of the combustion liner with wall passage cooling system that can be described herein.
Fig. 4 is the fragmentary perspective view of Fig. 3 wall passage cooling system.
Fig. 5 is the partial section view of Fig. 3 wall passage cooling system.
List of parts
10 gas-turbine units
15 compressors
20 air
25 burners
30 fuel
35 burning gases
40 turbines
45 axles
50 loads
55 cover plates
60 fuel nozzles
65 bushings
70 flowing sleeves
75 flow paths
80 entrances
85 combustion chambers
90 transition pieces
100 burners
105 head ends
110 bushings
115 rear ends
120 wall passage cooling systems
130 cooling ducts
140 jacket walls
150 entrances
160 outlets
170 return ducts
180 head end pipelines
190 purge holes.
Embodiment
With reference now to accompanying drawing (wherein through some views, similar label refers to similar element), Fig. 1 is shown can be herein
The schematic diagram of the middle gas-turbine unit 10 used.Gas-turbine unit 10 may include compressor 15.Compressor 15 compresses
The air stream 20 of entrance.Compressed air stream 20 is transported to burner 25 by compressor 15.Burner 25 by compressed air stream 20 with
Pressurized flow 30 is mixed, and lights the mixture to form burning gases stream 35.Although only showing single burner 25, combustion
Gas eddy turbine 10 may include any amount of burner 25.Burning gases stream 35 is transported to turbine 40 again.Burning gases
Stream 35 drives turbine 40, to produce mechanical work.The mechanical work produced in turbine 40 by axle 45 and external loading 50 (such as
Generator etc.) drive compressor 15.
Gas-turbine unit 10 can utilize natural gas, various types of synthesis gas liquid fuels, and/or other kinds of
Fuel and its admixture.Gas-turbine unit 10 can be by General Electric Company of Schenectady,
Any of a variety of different gas-turbine units that New York are provided, include but is not limited to such as 7 or 9 series heavy duties
Those of gas-turbine unit etc..Gas-turbine unit 10 can have many different constructions, and other types can be used
Component.Other kinds of gas-turbine unit can be also used in herein.Multiple gas-turbine units, other kinds of whirlpool
Wheel and other kinds of power generation equipment also can be used herein together.
Fig. 2 shows the example for the burner 25 that can be used together with gas-turbine unit 10 etc..In general, burner
25 may include the cover plate 55 at end at its upstream.Cover plate 55 can support multiple fuel nozzles 60 at least in part wherein.It is any
The fuel nozzle 60 of quantity or type can be used herein.Cover plate 55 provides air stream 20 and The fuel stream 30 goes to fuel nozzle 60
Path.
Burner 25 may include to configure the combustion liner 65 in flowing sleeve 70.The cloth of bushing 65 and flowing sleeve 70
It can be substantially concentric to put, and can limit annular flow path 75 therebetween.Flowing sleeve 70 may include to extend through its
Multiple flowing sleeve entrances 80.Flowing sleeve entrance 80 can provide moving air 20 from compressor 15 or elsewhere extremely
At least part of path.Flowing sleeve 70 can be by with entrance 80 or other pattern perforations.Combustion liner 65 can be in fuel nozzle 60
Downstream limit combustion chamber 85 for the burning of air stream 20 and The fuel stream 30.The rear end of burner 25 may include transition piece
90.Transition piece 90 can be positioned adjacent to turbine 40, and burning gases stream 35 can be directed into it.Burner 25 described herein
It is given for example only with burner member.Many other types of burner and burner member can be known.
Fig. 3-5 shows the part of the example for the burner 100 that can be described herein.Specifically, show that burner is served as a contrast
Set 110.Combustion liner 110 can extend to rear end 115 from head end 105.Combustion liner 110 can be substantially similar to above
Description, but add wall passage cooling system 120.Combustion liner 110 can have any suitable size, shape or structure
Make.
Wall passage cooling system 120 may include multiple cooling ducts 130.Cooling duct 130 can extend across jacket wall
140.Each in cooling duct 130 can extend to outlet 160 from entrance 150.Any amount of cooling duct 130 can be used in this
Wen Zhong.In one example, cooling duct 130 can have substantially square shape, and may have about 0.070 inch (big
About 1.778 millimeters) diameter.Alternatively, the circle of the diameter with about 0.075 inch (about 1.905 millimeters) can be used
Passage.Cooling duct 130 may have about 0.060 inch (about 1.524 millimeters) to about 0.080 inch of (about 2.0 milli
Rice) diameter.Can other shapes and size used herein.The length of cooling duct 130 can be restricted to no more than about
A few inches, i.e. be not more than about 2 to 5 inches (about 5.1 to 12.7 centimetres).It also may be used herein other length.
Cooling duct 130 can be positioned in multiple neighbouring rows by wall passage cooling system 120.In one example,
168 row cooling ducts 130 can be used.Moreover, can be each self-positioning about in the multiple row being circumferentially arranged around jacket wall 140
Eight to ten five cooling ducts 130.Alternatively, cooling duct 130 can extend any of the length of jacket wall 140 in any position
Part.Any amount of cooling duct 130 can be used herein with any suitable size, shape or construction.Cooling duct
130 may be cast as manufacturing in jacket wall 140 and/or by other kinds of routine techniques, including PSP, hard solder, processing
Deng.Alternatively, it also can whole or in part utilize and add manufacturing process etc..
The entrance 150 of cooling duct 130 can be opened, so as to exposed to air stream 20.(above-mentioned flowing sleeve 70 need not be used
Herein.) outlet 160 of cooling duct 130 can be positioned in return duct 170.Any amount of return duct 170 can be with
It is used herein with any suitable size, shape or construction.The length of cold side of the return duct 170 along jacket wall 140 is prolonged
Stretch, and can be connected with head end pipeline 180.Head end pipeline 180 can completely or partially surround the head end 105 of jacket wall 140.Head
End pipe road 180 can be connected with the grade of multiple purge holes 190 through jacket wall 140.In one example, can be used herein eight
Individual purge hole 190 may have about the diameter of 0.375 inch (about 9.525 millimeters).Any amount of purge hole 190 can be with
Any suitable size, shape are constructed used herein.Air stream 20 from return duct 170 can also be directed into it
He is local.For example, air stream 20 can be guided to premixed device, AFS control system, purge hole, nozzle or elsewhere.Moreover, different
Return duct 170 part of stream can be guided to different parts.Can other components used herein and other constructions.
When in use, a part for the air stream 20 from compressor or elsewhere can be by the lining towards combustion liner 110
Jacket wall 140 is sent out.A part for pressure drop can be used for streaming in the entrance 150 of cooling duct 130, here, stream is in its row
Enter through cooling bushing wall 140 during jacket wall 140.Cooling duct 130 increases total cooling surface product and heat transfer coefficient, to improve
The cooling effectiveness of per unit volume air.Cooling duct 130 can be restricted in terms of length, because air stream therein 20 can
Heat is rapidly absorbed from the hot side of jacket wall 140.Once given temperature difference is reduced by stream, then to routing 130
Cooling effectiveness can reduce so that the next cooling duct 130 with different air streams can continue cooling bushing wall 140.Cooling
Passage 130 can change the size (flow area) between entrance 150 and outlet 160, to make the flowing in cooling duct 130
Minimization of loss.For example, inlet diameter can be 0.065 inch (about 1.65 millimeters) and outlet diameter may be about 0.075
Inch (about 1.91 millimeters).Can other sizes used herein.Then heated air 20 can be left by outlet 160
Cooling duct 130, and can be gathered in return duct 170.Air stream 20 flows to head end pipeline 180 through return duct 170.It is empty
Air-flow 20 can then serve as the purging or leakage stream around the head end 105 of bushing 110 via purge hole 190.Alternatively, air stream
20 can be after cooling duct 130 be flowed through completely or partially for other purposes.
Using the only a part of total pressure drop so that wall passage cooling system 120 draws more and more high pressure air
It is directed at Fuel-air pre-mix zone.Therefore, burner 100 can be operated under higher pressure ratio, for the operable of improvement
Property, fuel flexibility and the reduction always discharged.Wall passage cooling system 120 also eliminates outside condenser, heat exchanger, complexity
The need for pipeline etc., for simplified and less expensive cooling system.Although being described under the background of combustion liner 110
Wall passage cooling system 120, but wall passage cooling system 120 can be with any kind of turbine component or turbine component to together with
Use.
It should be appreciated that foregoing teachings only relate to some embodiments of the present invention and gained patent.Can be by this area skill
Many modifications may be made herein and remodeling by art personnel, without departing from the present invention being limited by the following claims and their equivalents
Overall spirit and scope.
Claims (10)
1. one kind is used for the combustion liner (110) being used together with gas-turbine unit (10), including：
Jacket wall (140), it completely or partially extends to rear end (115) from head end (105)；
Multiple jacket wall cooling ducts (130), it is positioned in the jacket wall (140)；
Wherein, the multiple jacket wall cooling duct (130) extends to outlet (160) from entrance (150)；With
Multiple bushing return ducts (170)；
Wherein, to be positioned at the multiple bushing return duct (170) attached for the outlet of the multiple jacket wall cooling duct (130)
Closely.
2. combustion liner (110) according to claim 1, wherein, the multiple bushing return duct (170) is with surrounding
Head end pipeline (180) connection of head end (105) positioning of the jacket wall (140).
3. combustion liner (110) according to claim 2, wherein, the jacket wall (140) includes and the head end pipe
Multiple purge holes (190) of road (180) connection.
4. combustion liner (110) according to claim 1, wherein, the multiple jacket wall cooling duct (130) enter
Mouth (150) is orientated as to be connected with the air stream (20) in the flow path (75) in flowing sleeve (70).
5. combustion liner (110) according to claim 1, wherein, the multiple jacket wall cooling duct (130) includes
Substantially square shape or substantially round shape.
6. combustion liner (110) according to claim 1, wherein, the multiple jacket wall cooling duct (130) includes
The length of about 2 to 5 inches (about 5.1 to 12.7 centimetres).
7. combustion liner (100) according to claim 1, wherein, the multiple jacket wall cooling duct (130) includes
The diameter of about 0.060 inch (about 1.524 millimeters) to about 0.080 inch (about 2.0 millimeters).
8. combustion liner (100) according to claim 1, wherein, the multiple jacket wall cooling duct (130) includes
The inlet diameter of about 0.065 inch (about 1.65 millimeters) and the outlet of about 0.075 inch (about 1.91 millimeters) are straight
Footpath.
9. combustion liner (100) according to claim 1, wherein, the multiple jacket wall cooling duct (130) can be
Positioned in a plurality of columns on the jacket wall (140).
10. combustion liner (110) according to claim 9, wherein, eight to 15 the multiple jacket wall coolings
Passage (130) can be positioned on each in the multiple row in the jacket wall (140) in.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/944341 | 2015-11-18 | ||
| US14/944,341 US20170138595A1 (en) | 2015-11-18 | 2015-11-18 | Combustor Wall Channel Cooling System |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107013939A true CN107013939A (en) | 2017-08-04 |
Family
ID=57288309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611016285.3A Pending CN107013939A (en) | 2015-11-18 | 2016-11-18 | Burner wall passage cooling system |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20170138595A1 (en) |
| EP (1) | EP3171086A1 (en) |
| JP (1) | JP2017096267A (en) |
| CN (1) | CN107013939A (en) |
Families Citing this family (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9976487B2 (en) | 2015-12-22 | 2018-05-22 | General Electric Company | Staged fuel and air injection in combustion systems of gas turbines |
| US9938903B2 (en) | 2015-12-22 | 2018-04-10 | General Electric Company | Staged fuel and air injection in combustion systems of gas turbines |
| US9995221B2 (en) | 2015-12-22 | 2018-06-12 | General Electric Company | Staged fuel and air injection in combustion systems of gas turbines |
| US9945294B2 (en) | 2015-12-22 | 2018-04-17 | General Electric Company | Staged fuel and air injection in combustion systems of gas turbines |
| US9945562B2 (en) | 2015-12-22 | 2018-04-17 | General Electric Company | Staged fuel and air injection in combustion systems of gas turbines |
| US9989260B2 (en) | 2015-12-22 | 2018-06-05 | General Electric Company | Staged fuel and air injection in combustion systems of gas turbines |
| US11156362B2 (en) | 2016-11-28 | 2021-10-26 | General Electric Company | Combustor with axially staged fuel injection |
| US10982855B2 (en) | 2018-09-28 | 2021-04-20 | General Electric Company | Combustor cap assembly with cooling microchannels |
| US10816507B2 (en) | 2019-03-20 | 2020-10-27 | Raytheon Technologies Corporation | Apparatus and method and system for inspecting a component of a gas turbine engine |
| US11994293B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus support structure and method of manufacture |
| US11460191B2 (en) | 2020-08-31 | 2022-10-04 | General Electric Company | Cooling insert for a turbomachine |
| US11371702B2 (en) * | 2020-08-31 | 2022-06-28 | General Electric Company | Impingement panel for a turbomachine |
| US11614233B2 (en) | 2020-08-31 | 2023-03-28 | General Electric Company | Impingement panel support structure and method of manufacture |
| US11994292B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus for turbomachine |
| US11255545B1 (en) | 2020-10-26 | 2022-02-22 | General Electric Company | Integrated combustion nozzle having a unified head end |
| US11767766B1 (en) | 2022-07-29 | 2023-09-26 | General Electric Company | Turbomachine airfoil having impingement cooling passages |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5181379A (en) * | 1990-11-15 | 1993-01-26 | General Electric Company | Gas turbine engine multi-hole film cooled combustor liner and method of manufacture |
| JP3962554B2 (en) * | 2001-04-19 | 2007-08-22 | 三菱重工業株式会社 | Gas turbine combustor and gas turbine |
| JP4823186B2 (en) * | 2007-09-25 | 2011-11-24 | 三菱重工業株式会社 | Gas turbine combustor |
| US20100223931A1 (en) * | 2009-03-04 | 2010-09-09 | General Electric Company | Pattern cooled combustor liner |
| US20100272953A1 (en) * | 2009-04-28 | 2010-10-28 | Honeywell International Inc. | Cooled hybrid structure for gas turbine engine and method for the fabrication thereof |
| US8707705B2 (en) * | 2009-09-03 | 2014-04-29 | General Electric Company | Impingement cooled transition piece aft frame |
| US8720204B2 (en) * | 2011-02-09 | 2014-05-13 | Siemens Energy, Inc. | Resonator system with enhanced combustor liner cooling |
| US9234438B2 (en) * | 2012-05-04 | 2016-01-12 | Siemens Aktiengesellschaft | Turbine engine component wall having branched cooling passages |
| US20130318986A1 (en) * | 2012-06-05 | 2013-12-05 | General Electric Company | Impingement cooled combustor |
| US9212823B2 (en) * | 2012-09-06 | 2015-12-15 | General Electric Company | Systems and methods for suppressing combustion driven pressure fluctuations with a premix combustor having multiple premix times |
| US9309809B2 (en) * | 2013-01-23 | 2016-04-12 | General Electric Company | Effusion plate using additive manufacturing methods |
| US9528701B2 (en) * | 2013-03-15 | 2016-12-27 | General Electric Company | System for tuning a combustor of a gas turbine |
| GB201305432D0 (en) * | 2013-03-26 | 2013-05-08 | Rolls Royce Plc | A gas turbine engine cooling arrangement |
| US9410702B2 (en) * | 2014-02-10 | 2016-08-09 | Honeywell International Inc. | Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniques |
-
2015
- 2015-11-18 US US14/944,341 patent/US20170138595A1/en not_active Abandoned
-
2016
- 2016-11-08 JP JP2016217716A patent/JP2017096267A/en active Pending
- 2016-11-18 EP EP16199642.6A patent/EP3171086A1/en not_active Withdrawn
- 2016-11-18 CN CN201611016285.3A patent/CN107013939A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| EP3171086A1 (en) | 2017-05-24 |
| US20170138595A1 (en) | 2017-05-18 |
| JP2017096267A (en) | 2017-06-01 |
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Application publication date: 20170804 |