CN105121963A - Removable swirler assembly for a combustion liner - Google Patents
Removable swirler assembly for a combustion liner Download PDFInfo
- Publication number
- CN105121963A CN105121963A CN201480023669.0A CN201480023669A CN105121963A CN 105121963 A CN105121963 A CN 105121963A CN 201480023669 A CN201480023669 A CN 201480023669A CN 105121963 A CN105121963 A CN 105121963A
- Authority
- CN
- China
- Prior art keywords
- mounting blocks
- hole
- swirler assembly
- affixed
- removable
- 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.)
- Granted
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Classifications
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/002—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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
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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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
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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
- F23R2900/00017—Assembling combustion chamber liners or subparts
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49346—Rocket or jet device making
Abstract
A novel and improved swirler assembly for use in a combustion liner of a gas turbine engine is disclosed. The swirler assembly is removable and sized to provide an improved assembly, repairability, and fit-up in the combustion liner. The swirler assembly includes a premix tube, premix swirler and a plurality of axially spaced mounting blocks for receiving removable fasteners for securing the swirler assembly to the combustor.
Description
The cross reference of related application
The U.S. Provisional Patent Application sequence number No.61/815 submitted on April 25th, 2013 is enjoyed in the application's request, the priority of 835.This application theme relates to and is entitled as PREMIXERASSEMBLYFORGASTURBINECOMBUSTOR (attorney docket No.PSM-317/PSSF.199281) with SWIRLERASSEMBLYANDSTIFFENINGMECHANISMFORPREMIXERASSEMBLY OFAGASTURBINECOMBUSTOR (attorney docket No.PSM-318/PSSF.199282) and transfers the U.S. Non-provisional Patent application of the common transfer of the assignee identical with the application.
Technical field
The present invention relates generally to a kind of gas turbine combustor.More specifically, the present invention relates to the removable cyclone part of combustion liner, it has and is designed by the assembly and disassembly technology of improvement and the cooling construction of improvement and the feature in enhanced burning device performance and member for prolonging life-span.
Background technology
In typical gas-turbine unit, the compressor with the staggered level of rotation and static airfoil is connected to turbine by axial axis, and wherein turbine also has the staggered level of rotation and static airfoil.Compressor stage reduces in size, to compress the air through it.Then compressed air be supplied to one or more burner, and it makes air mix mutually with fuel.The incendiary source point burning mixt of this one or more burner contiguous, thus form hot combustion gas.The expansion driven of hot combustion gas is connected to the stage of turbine of compressor by axial axis.Then Exhaust Gas can be used as propelling source, and to pass through recuperation of heat maker generating steam, or rotation is connected to the axle of generator for generating in power plant operation.
The combustion system of gas-turbine unit can adopt multiple structure.Combustion system for gas-turbine unit can comprise single combustion chamber, combustion system around multiple independent combustion chambers of the axis at intervals of engine, supercharging type, or other combustion systems multiple.Depend on engine geometry, performance requirement and physical operations position, burner arrangement will change accurately.
This type of combustion system comprise be affixed to engine frame shell, be connected in shell at least partially in combustion liner, and to be positioned in combustion liner or neighbouring one or more fuel nozzle for fuel (gas, liquid or the two) being ejected in combustion chamber.Combustion system is communicated with engine fluid.More specifically, shell and lining are arranged provides the air from compressor to enter the mode of combustion system, at combustion system place, and itself and the fuel mix from one or more fuel nozzle.Fuel-air mixture by incendiary source as spark lighter is lighted.Hot combustion gas travels across combustion liner, and usually passes one or more transition piece and enter in turbine.Transition piece is essentially conduit, and it has the geometry becoming turbine inlet from the shape of burner.
Combustion liner is in the center of operation of combustors.Combustion liner geometry is specified by many factors, comprises the operating parameter of engine, performance requirement and available geometry.Although combustion liner variable geometry, combustion liner generally includes for receiving fuel nozzle, for fuel and air being mixed and being used for holding reaction when fuel and air mixture is lighted at least partially.
The combustion liner of prior art has met some performance requirement, but has also presented various deficiency.Such as, the assembly that previous combustion lining is main welding or only welds, thus make operator or all features to be repaired be difficult to close to combustion liner of repairing facility.In addition, similar structures existing burner design renovation or approximate 8 can be operated before replacing it, 000 hour.In order to improve gas-turbine unit efficiency, operator colony expects to extend the time range between repairing strongly, to reduce engine down time and/or repairing/check cost.
Summary of the invention
According to the present invention, provide a kind of novelty for using in the combustion liner of gas-turbine unit and the swirler assembly improved.This swirler assembly can remove, and is defined as providing the assembling of improvement, repairability and being engaged in combustion liner in size.Multiple main swirler assembly is arranged in combustion liner around central axis, and size is defined as receiving multiple fuel nozzle.
According to embodiments of the invention, provide a kind of swirler assembly for gas turbine combustor, it comprises premix barrel, the premixed swirl device be positioned in premix barrel, neighboring entry end are located along the outer wall of premix barrel and have first mounting blocks in multiple first hole, also along the second mounting blocks that the outer wall of premix barrel is located, the second mounting blocks and the first mounting blocks keep at a certain distance away and have one or more second hole perpendicular to multiple first hole.
According to another embodiment of the invention, provide the multiple spot for using in gas turbine combustor, multi-direction fastening assembly, it comprises the first mounting blocks being affixed to body, before wherein the first mounting blocks has, contrary after, substantial parallel side, outside arc, and be arranged in the multiple holes outside arc.Fastening assembly also comprises the second mounting blocks, and this second mounting blocks is affixed to body and has one or more hole, and the multiple holes wherein in the first mounting blocks are oriented one or more hole be essentially perpendicular in the second mounting blocks.
According to still another embodiment of the invention, provide the removable swirler assembly in a kind of burner, it comprises body, the prostheses of generic cylindrical, and the multiple blades extended between prostheses and the body of generic cylindrical.Removable swirler assembly also comprises the first mounting blocks of the body being affixed to generic cylindrical, before wherein the first mounting blocks has, contrary after, substantial parallel side, outside arc, and be arranged in the multiple holes outside arc.Removable swirler assembly also comprises and is affixed to body and second mounting blocks with one or more hole, and wherein removable cyclone is fastened to burner by multiple removable securing member at the first and second mounting blocks places.
Attendant advantages of the present invention and feature will partly be explained in the following description, and partly will become clear for a person skilled in the art when checking hereafter, or are understood by practice of the present invention.Present general is concrete with reference to the accompanying drawings to describe the present invention.
Accompanying drawing explanation
The present invention is described in detail referring to accompanying drawing, in the accompanying drawings:
Fig. 1 is the partial section of the gas-turbine unit of prior art, wherein can use combustion system according to an embodiment of the invention;
Fig. 2 is the sectional view of the gas turbine combustor of the prior art that can operate in the gas-turbine unit of Fig. 1;
Fig. 3 is the perspective view of the combustion liner comprising embodiments of the invention;
Fig. 4 is the sectional view of the combustion liner comprising embodiment according to an embodiment of the invention;
Fig. 5 is the alternative view in the cross section of the Fig. 4 comprising embodiments of the invention;
Fig. 6 is according to an embodiment of the invention through the sectional view of the combustion liner of swirler assembly intercepting;
Fig. 7 is the alternative view in the cross section of Fig. 6 according to an embodiment of the invention;
Fig. 8 is the perspective view of the swirler assembly part of the combustion liner of Fig. 3 according to an embodiment of the invention;
Fig. 9 is the detailed sectional view that the intake section of the combustion liner through Fig. 3 in the cross section comprising swirler assembly according to an embodiment of the invention intercepts; And
Figure 10 is the partial section of the swirler assembly of combustion liner according to an embodiment of the invention.
Detailed description of the invention
Theme of the present invention specifically describes in this article, meets legal requirements.But, the scope self being not intended to limit this patent is described.On the contrary, inventor conceives, and claimed theme can also realize with other forms, with other existing or future combine with technique comprise and combining with those the similar different components, Component composition, step or the step that illustrate in the literature.
First referring to Fig. 1, in partial cross section, the gas-turbine unit 100 of prior art is depicted.Gas-turbine unit 100 comprises the shell 102 of encapsulating engine major part substantially.Axle 104 axially extends along engine axis A-A, and is connected to compressor 106 and turbine 108.Air by entrance area 110 admission of air, and is directed across the rotation of decrescence size and the staggered row of static airfoil by compressor 106, to pass compressed air at that time at air, thus increases the temperature and pressure of air.Then compressed air be guided through one or more combustion system 112, and at this, fuel and air are mixed together and light to form hot combustion gas.Then hot combustion gas is directed in turbine 108, and through the rotation of cumulative size and the staggered row of static airfoil, to make fluid expansion and to become mechanical power to carry out driving shaft 104 power conversion of burning gases.Axle 104 also can be connected to the axle of generator, for generating (not shown).
Fig. 2 discloses the cross section of the burner 200 of the gas-turbine unit of prior art.Therefore, this exemplary gas turbine burner 200 comprises shell 202, lid 204, one or more fuel injector 206 and combustion liner 208.Combustion liner 208 is connected to the entrance of turbine 212 by transition piece 210.
The present invention illustrates in detail in Fig. 3-10, and discloses the new removable swirler assembly with improving for using in the burner of gas-turbine unit.First referring to Fig. 3-7, the combustion liner 300 with removable swirler assembly 332 is disclosed.Combustion liner 300 comprises the bush body 302 of generic cylindrical, and bush body 302 has arrival end 304, the port of export 306 or outlet side, and extends through the axis B-B of burner.Combustion liner 300 is substantially cylindrical cross-section, but it should be understood that combustion liner 300 can change in shape, has tapered segment or the section of the diameter that changes.Combustion liner 300 is made up of rolled metal sheet substantially, rolled metal sheet seam welds vertically, and can be depending on specific burning geometry and form or be extended to the cylindrical structural of change.Combustion liner 300 preferably by high temperature alloy as Haynes230 makes, it can tolerate the burner conditions of the rising exceeding approximate 1500 degrees Fahrenheits.Candidate materials can be used, as Hastelloy-X or Inconel.
Combustion liner 300 also comprises being affixed to generic cylindrical body 302 enters choma cage 308.The choma cage 308 that enters as shown in figs. 3-7 is made up of a series of axles 310 axially directed being substantially connected to front ring 312, and extends forward from the arrival end 304 of combustion liner 300.Front ring 312 is positioned to be had with a certain distance from combustion liner 300, to form the matched position being used for one group of fuel nozzle (not shown), fuel nozzle to be positioned at the suitable axial location in burner.Enter component or foundry goods that choma cage 308 can be manufacture, and be preferably made up of stainless steel material.Referring now to Figure 10, enter choma cage 308 and also comprise multiple lug 309, lug 309 extends radially inwardly from entering choma cage 308, for the premixed device assembly 330 that is connected, as discussed in more detail hereinafter.Lug 309 can be made dividually, and is welded to into choma cage 308 or foundry goods as the part entering choma cage 308.
Referring to Fig. 4-7, combustion liner 300 also comprises premixed device assembly 330.A component of premixed device 330 is one or more removable cyclone 332.Referring now to Fig. 8-10, swirler assembly 332 is plotted as in premixed device assembly 330.Swirler assembly 332 comprises premix barrel 342, and premix barrel 342 has arrival end 342A and contrary port of export 342B, and extends through its longitudinal axis C-C.Swirler assembly 332 also comprises premixed swirl device 336, and premixed swirl device 336 is positioned in premix barrel 342, has multiple moving blade 338 at this premixed swirl device 336, for eddy flow is given through premix barrel 342 by stream.For the embodiment drawn in Fig. 8-10, premix barrel 342 is substantially columniform.But the alternative shape of premix barrel 342 is also possible.
Swirler assembly 332 also comprises two mounting blocks, is connected in gas turbine combustor for by swirler assembly.The arrival end 342A of the contiguous premix barrel 342 of the first mounting blocks 344 locates along the outer wall of premix barrel 342.First mounting blocks 344 has the first above 344A, contrary first flank 344B, a pair substantial parallel side 345, and outside 347.Outside 347 can have at least along the arcuate shape of a part for outside, so that mounting blocks 344 meets the shape into choma cage 308.Outside 347 for arrange swirler assembly 332 radial position and with the contact entering choma cage 308, to allow swirler assembly 332 relative to the tighter size Control of fuel nozzle.As shown in Figure 8, the first mounting blocks 344 also comprises multiple first hole 348, hole 348, first and to be arranged in outside arc 347, and is oriented the longitudinal axis C-C being essentially perpendicular to premix barrel 342.
Swirler assembly 332 also comprises the second mounting blocks 346, and its outer wall along premix barrel 342 is located and and the first mounting blocks 344 interval axial distance.Second mounting blocks 346 has second face 346A and contrary second flank 346B, is processed to pre-sizing at this second flank 346B, to form specific axial extent, for the suitable axial location installed by swirler assembly 332 in the burner.In order to swirler assembly 332 is positioned at suitable axial location, the second mounting blocks 346 comprises being worked into and moves back mouth (reliefcut) 360 earnestly in second flank 346B.Second mounting blocks 346 also has one or more second hole 356 extending up through the second mounting blocks 346 in the side being essentially perpendicular to multiple first hole 348.
For the embodiments of the invention drawn in Fig. 8-10, the second mounting blocks 346 and the first mounting blocks 344 directly axially align.But depend on burner geometry, the first and second mounting blocks 344 and 346 can not axially align, but about clock skew (clock) circumferentially from one another.
Each in first mounting blocks 344 and the second mounting blocks 346 is affixed to premix barrel 342.Different attachment methods for mounting blocks are possible.In one embodiment, the first mounting blocks 344 and the second mounting blocks 346 are welded to premix barrel 342.The intersection of the bead of compatible welding material (in premix barrel 342 and compatible between mounting blocks 344 and the material of 346) be laid in mounting blocks and premix barrel 342.
By hard-welded joint (brazejoint) by the alternative approach that the first and second mounting blocks 344 and 346 are affixed to premix barrel 342.Hard-welded joint forms more complete joint by contributing to, because the whole surface of the mounting blocks contacted with premix barrel 342 is attached to premix barrel 342.On the contrary, mounting blocks is only affixed to premix barrel 342 in the edge of mounting blocks contact premix barrel by welding point.
In another embodiment, mounting blocks 344 and 346 is likely one with premix barrel 342.Mounting blocks 344 and 346 is attached in premix barrel 342 and realizes by casting or forging.
The size accurately in the hole in the first mounting blocks 344 and the second mounting blocks 346, interval and amount alterable, and depend on many factors, e.g., the size of burner geometry, swirler assembly 332, and machinery on swirler assembly 332 and heat load.For the embodiments of the invention drawn in Fig. 8-10, the first mounting blocks 344 comprises two the first holes 348, and wherein the first hole 348 is oriented and is essentially perpendicular to longitudinal axis C-C.Second mounting blocks 346 comprises one or more the second hole 356, and the embodiment shown in Fig. 8-10 uses single second hole 356.But, likely need the second more than one hole 356, swirler assembly 342 is affixed to burner.For the embodiment shown in Fig. 8-10, the second hole 356 is substantially parallel to axis C-C.
As mentioned above, swirler assembly 332 is designed to be able to easily remove from burner, to be convenient to maintenance and repair better.Therefore, multiple removable securing member 350 and 358 is for being connected swirler assembly 332 in the burner.In one embodiment, removable securing member (as bolt) engages the thread pattern of the correspondence in multiple first holes 348 and one or more second hole 356.Thread pattern is only be connected a kind of mode of removable securing member.Alternatively, one or more second hole 356 can be through hole (that is, without screw thread), and uses the nut of neighbouring surface 346A.In addition, bolt/stud can be welded/be installed, and to substitute the hole 356 with nut, is then placed on the surface of dome plate 334.
Swirler assembly 332 is positioned to be communicated with adjacent pipe 352 (also referred to as vacuum suction (hoover)) fluid, and the stream of fuel and air is sent to the mixed zone of combustion liner 300 by it from swirler assembly 332.That is, swirler assembly 332 is positioned to be close to or to be slightly bonded in pipe 352.Form radial gap in order to ensure the suitable radial position of swirler assembly 332 in combustion liner with pipe 352, multiple spacer 354 is located around the outer surface of each in premix barrel 342, contiguous port of export 342B.
As mentioned above, swirler assembly 332 is affixed to burner removedly by multiple securing member 350 and 358 (as bolt or other devices).Such as, and as shown in figures 6-10, main cyclone device assembly 332 is affixed to dome plate 334 by means of the securing member 350 and 358 through the first hole 348 and the second hole 356.By using radially and axially directed securing member 350 and 358, achieve swirler assembly 332 relative to the better location of premixed device assembly 330 and combustion liner 300 and allowance control.In addition, by swirler assembly 332 is affixed to premixed device assembly 330 removedly, greatly improve compared to the prior art burner with the swirler assembly being welded to premixed device assembly for the path checked and repair premixed device assembly 330.As person of skill in the art will appreciate that, except Reachability question, the welding of swirler assembly also causes the distortion of swirler assembly, this thus can affect flowing control.
Swirler assembly 332 is preferably made up of the material (as a kind of stainless steel) similar with premixed device assembly 330.Swirler assembly 332 also can be the manufacture assembly or foundry goods with various processing part.
Referring now to Fig. 9 and 10, swirler assembly 332 shows for being arranged in premixed device assembly 330.As mentioned above, swirler assembly 332 is connected in place by securing member 350 and 358, and securing member 350 and 358 is radially directed with axial direction.Swirler assembly 332 slips into appropriate location, makes spacer 354 provide radial gap relative to pipe 352, and the second mounting blocks 346 is owing to moving back mouth 360 and contact the lug 309 into choma cage 308 in suitable axial positions earnestly.
Describe the present invention about specific embodiment, specific embodiment is intended to be all exemplary and nonrestrictive in all respects.Alternative embodiment and required operation will become clear for those skilled in the art, and not depart from its scope.
From seeing above, together with other advantages that system and method is obvious and intrinsic, the present invention is well suitable for obtaining all results mentioned above and object.Will be appreciated that some characteristic sum sub-portfolio is useful, and can when not using with reference to when other characteristic sum sub-portfolios.This by the conception of scope of claim and within the scope of the claims.
Claims (19)
1., for a swirler assembly for gas turbine combustor, it comprises:
Premix barrel, its longitudinal axis that there is arrival end, the contrary port of export and extend through it;
Premixed swirl device, it is positioned in described premix barrel, and described cyclone has the multiple moving blades for being given by eddy flow by stream;
First mounting blocks, its contiguous described arrival end is located along the outer wall of described premix barrel and has multiple first hole, and described multiple first hole is oriented and is essentially perpendicular to described longitudinal axis; With
Second mounting blocks, its outer wall along described premix barrel is positioned to be had with a certain distance from described first mounting blocks, described second mounting blocks has one or more the second hole, and one or more second hole described extends through described second mounting blocks along the direction perpendicular to described multiple first hole.
2. swirler assembly according to claim 1, is characterized in that, described premix barrel is substantially conical.
3. swirler assembly according to claim 1, is characterized in that, each in described first mounting blocks and the second mounting blocks is affixed to described premix barrel.
4. swirler assembly according to claim 3, is characterized in that, described first and second mounting blocks are affixed to described premix barrel by welding or hard-welded joint.
5. swirler assembly according to claim 1, is characterized in that, the multiple holes in described first mounting blocks comprise at least two holes.
6. swirler assembly according to claim 1, is characterized in that, one or more second hole described is threaded.
7. swirler assembly according to claim 1, is characterized in that, described second mounting blocks has second face and contrary second flank, and wherein said second flank is finish-machined to predetermined axial dimension.
8., for the multiple spot used in gas turbine combustor, a multi-direction fastening assembly, it comprises:
Be affixed to the first mounting blocks of body, described first mounting blocks has first flank before first, contrary, a pair side, outside and is arranged in multiple holes of described outside; With
Be affixed to the second mounting blocks of described body, described second mounting blocks have be positioned at one of them or more hole;
Wherein, described second mounting blocks and the described first certain axial distance in mounting blocks interval.
9. fastening assembly according to claim 8, is characterized in that, described outside is at least arc surrounding the region place in described multiple hole.
10. fastening assembly according to claim 8, is characterized in that, described first mounting blocks is affixed to described body by welding or hard-welded joint.
11. fastening assemblies according to claim 8, is characterized in that, described second mounting blocks is affixed to described body by welding or hard-welded joint.
12. fastening assemblies according to claim 8, is characterized in that, described first and second mounting blocks and described body are one.
13. fastening assemblies according to claim 8, is characterized in that, the described multiple hole in described first mounting blocks is essentially perpendicular to one or more installing hole in described second mounting blocks.
Removable swirler assembly in 14. 1 kinds of burners, it comprises:
The body of generic cylindrical;
Prostheses, the entrance of the body of its contiguous described generic cylindrical is positioned in described columniform body;
Multiple blade, it extends between described prostheses and the body of described generic cylindrical;
First mounting blocks, it is affixed to the body of described generic cylindrical, before described first mounting blocks has first, contrary after, a pair side, and there is the outside in the multiple holes be positioned at wherein; With
Second mounting blocks, it is affixed to the body of described generic cylindrical, described second mounting blocks have be positioned at one of them or more hole;
Wherein, described removable cyclone is fastened to described burner by multiple removable securing member at both described first mounting blocks and the second mounting blocks place.
15. removable cyclones according to claim 14, is characterized in that, described multiple blades oriented become in case eddy flow is given air and fuel by stream.
16. removable cyclones according to claim 14, is characterized in that, the circumferential distance that described in described first mounting blocks ratio of elongation, the second mounting blocks is large.
17. removable cyclones according to claim 14, is characterized in that, the multiple holes in described first mounting blocks are essentially perpendicular to the single hole in described second mounting blocks.
18. removable cyclones according to claim 14, is characterized in that, also comprise multiple securing member, described multiple securing member is placed in multiple openings of described first mounting blocks, is affixed to described burner for by described cyclone.
19. removable cyclones according to claim 14, is characterized in that, the outside of described first mounting blocks is at least arc at the region place in contiguous described multiple hole.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US201361815835P | 2013-04-25 | 2013-04-25 | |
| US61/815835 | 2013-04-25 | ||
| US14/256022 | 2014-04-18 | ||
| US14/256,022 US20140318150A1 (en) | 2013-04-25 | 2014-04-18 | Removable swirler assembly for a combustion liner |
| PCT/EP2014/058334 WO2014174009A1 (en) | 2013-04-25 | 2014-04-24 | Removable swirler assembly for a combustion liner |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105121963A true CN105121963A (en) | 2015-12-02 |
| CN105121963B CN105121963B (en) | 2017-08-18 |
Family
ID=51788070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201480023669.0A Expired - Fee Related CN105121963B (en) | 2013-04-25 | 2014-04-24 | Removable swirler assembly for combustion liner |
Country Status (6)
| Country | Link |
|---|---|
| US (3) | US20140318139A1 (en) |
| JP (2) | JP2016516976A (en) |
| KR (1) | KR20160023657A (en) |
| CN (1) | CN105121963B (en) |
| MX (1) | MX2015014400A (en) |
| WO (3) | WO2014174012A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3081862B1 (en) * | 2015-04-13 | 2020-08-19 | Ansaldo Energia Switzerland AG | Vortex generating arrangement for a pre-mixing burner of a gas turbine and gas turbine with such vortex generating arrangement |
| CN105546582A (en) * | 2016-01-19 | 2016-05-04 | 西北工业大学 | Evaporating tube device having enhanced atomization effect |
| CN107543202B (en) * | 2017-07-25 | 2019-06-04 | 西北工业大学 | A kind of low-pollution burning chamber of gas turbine list eddy flow head construction |
| US11859819B2 (en) | 2021-10-15 | 2024-01-02 | General Electric Company | Ceramic composite combustor dome and liners |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07260137A (en) * | 1994-03-17 | 1995-10-13 | Kawasaki Heavy Ind Ltd | Method and apparatus for diagnosing combustion |
| DE69126846D1 (en) * | 1990-11-27 | 1997-08-21 | Gen Electric | Secondary premix fuel nozzle with integrated swirl device |
| US20050268618A1 (en) * | 2004-06-08 | 2005-12-08 | General Electric Company | Burner tube and method for mixing air and gas in a gas turbine engine |
| CN101424407A (en) * | 2007-10-29 | 2009-05-06 | 通用电气公司 | Mager vorgemischte dual-fuel-ringrohrbrennkammer mit radial-mehrring-stufenduse |
| CN101435585A (en) * | 2008-11-28 | 2009-05-20 | 北京大学 | Gas turbine combined type fuel evaporating and atomizing combustion apparatus |
Family Cites Families (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4216652A (en) * | 1978-06-08 | 1980-08-12 | General Motors Corporation | Integrated, replaceable combustor swirler and fuel injector |
| US6298667B1 (en) * | 2000-06-22 | 2001-10-09 | General Electric Company | Modular combustor dome |
| US6334298B1 (en) * | 2000-07-14 | 2002-01-01 | General Electric Company | Gas turbine combustor having dome-to-liner joint |
| US6415610B1 (en) * | 2000-08-18 | 2002-07-09 | Siemens Westinghouse Power Corporation | Apparatus and method for replacement of combustor basket swirlers |
| US6672073B2 (en) * | 2002-05-22 | 2004-01-06 | Siemens Westinghouse Power Corporation | System and method for supporting fuel nozzles in a gas turbine combustor utilizing a support plate |
| US7222488B2 (en) * | 2002-09-10 | 2007-05-29 | General Electric Company | Fabricated cowl for double annular combustor of a gas turbine engine |
| US6705087B1 (en) * | 2002-09-13 | 2004-03-16 | Siemens Westinghouse Power Corporation | Swirler assembly with improved vibrational response |
| US6848260B2 (en) * | 2002-09-23 | 2005-02-01 | Siemens Westinghouse Power Corporation | Premixed pilot burner for a combustion turbine engine |
| US7316117B2 (en) * | 2005-02-04 | 2008-01-08 | Siemens Power Generation, Inc. | Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations |
| US7581402B2 (en) * | 2005-02-08 | 2009-09-01 | Siemens Energy, Inc. | Turbine engine combustor with bolted swirlers |
| US7513098B2 (en) * | 2005-06-29 | 2009-04-07 | Siemens Energy, Inc. | Swirler assembly and combinations of same in gas turbine engine combustors |
| US20070028595A1 (en) * | 2005-07-25 | 2007-02-08 | Mongia Hukam C | High pressure gas turbine engine having reduced emissions |
| US8438853B2 (en) * | 2008-01-29 | 2013-05-14 | Alstom Technology Ltd. | Combustor end cap assembly |
| US8387393B2 (en) * | 2009-06-23 | 2013-03-05 | Siemens Energy, Inc. | Flashback resistant fuel injection system |
| US8272224B2 (en) * | 2009-11-02 | 2012-09-25 | General Electric Company | Apparatus and methods for fuel nozzle frequency adjustment |
-
2014
- 2014-04-18 US US14/256,023 patent/US20140318139A1/en not_active Abandoned
- 2014-04-18 US US14/256,022 patent/US20140318150A1/en not_active Abandoned
- 2014-04-18 US US14/256,025 patent/US20140318140A1/en not_active Abandoned
- 2014-04-24 WO PCT/EP2014/058338 patent/WO2014174012A1/en active Application Filing
- 2014-04-24 MX MX2015014400A patent/MX2015014400A/en unknown
- 2014-04-24 JP JP2016509463A patent/JP2016516976A/en active Pending
- 2014-04-24 WO PCT/EP2014/058334 patent/WO2014174009A1/en active Application Filing
- 2014-04-24 JP JP2016509465A patent/JP2017516007A/en active Pending
- 2014-04-24 CN CN201480023669.0A patent/CN105121963B/en not_active Expired - Fee Related
- 2014-04-24 WO PCT/EP2014/058336 patent/WO2014174011A1/en active Application Filing
- 2014-04-24 KR KR1020157033470A patent/KR20160023657A/en not_active Application Discontinuation
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE69126846D1 (en) * | 1990-11-27 | 1997-08-21 | Gen Electric | Secondary premix fuel nozzle with integrated swirl device |
| JPH07260137A (en) * | 1994-03-17 | 1995-10-13 | Kawasaki Heavy Ind Ltd | Method and apparatus for diagnosing combustion |
| US20050268618A1 (en) * | 2004-06-08 | 2005-12-08 | General Electric Company | Burner tube and method for mixing air and gas in a gas turbine engine |
| CN101424407A (en) * | 2007-10-29 | 2009-05-06 | 通用电气公司 | Mager vorgemischte dual-fuel-ringrohrbrennkammer mit radial-mehrring-stufenduse |
| CN101435585A (en) * | 2008-11-28 | 2009-05-20 | 北京大学 | Gas turbine combined type fuel evaporating and atomizing combustion apparatus |
Also Published As
| Publication number | Publication date |
|---|---|
| US20140318139A1 (en) | 2014-10-30 |
| US20140318150A1 (en) | 2014-10-30 |
| WO2014174009A1 (en) | 2014-10-30 |
| KR20160023657A (en) | 2016-03-03 |
| JP2016516976A (en) | 2016-06-09 |
| US20140318140A1 (en) | 2014-10-30 |
| MX2015014400A (en) | 2016-06-21 |
| WO2014174012A1 (en) | 2014-10-30 |
| CN105121963B (en) | 2017-08-18 |
| JP2017516007A (en) | 2017-06-15 |
| WO2014174011A1 (en) | 2014-10-30 |
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