CN105121963B - Removable swirler assembly for combustion liner - Google Patents
Removable swirler assembly for combustion liner Download PDFInfo
- Publication number
- CN105121963B CN105121963B CN201480023669.0A CN201480023669A CN105121963B CN 105121963 B CN105121963 B CN 105121963B CN 201480023669 A CN201480023669 A CN 201480023669A CN 105121963 B CN105121963 B CN 105121963B
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- China
- Prior art keywords
- mounting blocks
- swirler assembly
- assembly
- holes
- removable
- Prior art date
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- 238000002485 combustion reaction Methods 0.000 title abstract description 48
- 239000000446 fuel Substances 0.000 claims description 16
- 238000003466 welding Methods 0.000 claims description 7
- 239000007789 gas Substances 0.000 description 12
- 239000000567 combustion gas Substances 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 238000005266 casting Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 4
- 230000003068 static effect Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical class C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
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
- F23R3/28—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
-
- 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
-
- 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
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Testing Of Engines (AREA)
- Combustion Of Fluid Fuel (AREA)
Abstract
Disclose a kind of novel and improved swirler assembly for being used in the combustion liner of gas-turbine unit.The swirler assembly can be removed, and be determined to provide for improved assembling, repairability and cooperation in combustion liner in terms of size.Swirler assembly includes the mounting blocks of premix barrel, premixed swirl device and multiple axially spaced-aparts, for receiving the removable fastener for being used for that swirler assembly to be affixed to burner.
Description
The cross reference of related application
The U.S. Provisional Patent Application Serial No. No. 61/815 submitted on April 25th, 2013 is enjoyed in the application request,
835 priority.This application theme is related to entitled PREMIXER ASSEMBLY FOR GAS TURBINE COMBUSTOR (generations
Manage people reel number No. PSM-317/PSSF.199281) and SWIRLER ASSEMBLY AND STIFFENING MECHANISM
FOR PREMIXER ASSEMBLY OF A GAS TURBINE COMBUSTOR (attorney docket No. PSM-318/
PSSF.199282) and the commonly assigned U.S. Non-provisional Patent application of assignee same as the present application is transferred.
Technical field
The present invention relates generally to a kind of gas turbine combustor.More particularly it relates to combustion liner can
The cyclone part of removal, it has features designed to strengthen combustion by improved assembly and disassembly technology and improved cooling construction
Burner performance and the feature in member for prolonging life-span.
Background technology
In typical gas-turbine unit, the compressor of the staggeredly level with rotation and static airfoil passes through axial direction
Axle and be connected to turbine, wherein turbine also have rotation and static airfoil staggeredly level.Compressor stage reduces in terms of size,
To compress the air through it.Compressed air is then supplied to one or more burners, and it makes air mutually be mixed with fuel
Close.The incendiary source point burning mixt of neighbouring one or more burners, so as to form hot combustion gas.Hot combustion gas
Expansion driven is connected to the stage of turbine of compressor by axial axis.Discharge gas can then serve as propulsion source, to be returned by heat
Midwifery is grown up to be a useful person generation steam, or is rotated in power plant operation and be connected to the axle of generator for generating.
The combustion system of gas-turbine unit can use a variety of constructions.Combustion system for gas-turbine unit can
Multiple independent combustion chambers, the combustion system of supercharging type including single combustion chamber, around the axis interval of engine, or it is a variety of
Other combustion systems.Depending on engine geometry, performance requirement and physical operations position, accurate burner arrangement will become
Change.
One such combustion system includes being affixed to the shell of engine frame, is connected at least a portion of shell
Combustion liner, and be positioned in combustion liner or nearby for fuel (gas, liquid or the two) is ejected into burning
One or more fuel nozzles in room.Combustion system is connected with engine fluid.More specifically, shell and bushing arrangement
There is provided the air from compressor enter combustion system mode, at combustion system, its with from one or more fuel
The fuel mixing of nozzle.Fuel-air mixture is lighted by incendiary source such as spark lighter.Hot combustion gas travel across burning
Bushing, and be typically inserted through one or more transition pieces and enter in turbine.Transition piece is substantially conduit, and it has from burning
The shape of device is changed into the geometry of turbine inlet.
Combustion liner is in the center of operation of combustors.Combustion liner geometry is provided by many factors, is wrapped
Include the operating parameter, performance requirement and available geometry of engine.Although combustion liner variable geometry, burning lining
Set generally includes to be used for receive fuel nozzle, for fuel and air to be mixed and for accommodating when fuel and air are mixed
At least a portion of reaction when compound is lighted.
The combustion liner of prior art has met some performance requirements, but has also showed various deficiencies.For example, foregoing combustion
It is the main component for welding or only welding to burn bushing, so that operator or repair facility is difficult to close to the to be repaired of combustion liner
All features of reason.In addition, the existing burner design of similar structures can operate approximate 8 before renovating or replacing it, 000 is small
When.In order to improve gas-turbine unit efficiency, operator colony is desirable to the time range between extension repairing strongly, with
Just engine down time and/or repairing/check cost are reduced.
The content of the invention
According to the present invention is there is provided a kind of novelty for being used to use in the combustion liner of gas-turbine unit and improves
Swirler assembly.The swirler assembly can be removed, and be determined to provide in terms of size improving assembling, repairability and match somebody with somebody
Close in combustion liner.Multiple main swirler assemblies, which are located in combustion liner, surrounds central axis, and is sized to receive
Multiple fuel nozzles.
Embodiments in accordance with the present invention are there is provided a kind of swirler assembly for gas turbine combustor, and it includes in advance
Mixed pipe, the outer wall of the premixed swirl device being positioned in premix barrel, neighboring entry end along premix barrel are positioned and with multiple first holes
The first mounting blocks, and also along premix barrel outer wall position the second mounting blocks, the second mounting blocks with first installation block gap one
Set a distance and with perpendicular to multiple first holes one or more second holes.
There is provided the multiple spot for being used in gas turbine combustor, multi-party according to another embodiment of the invention
To fastening assembly, it includes the first mounting blocks for being affixed to body, wherein the first mounting blocks have above, it is opposite behind, it is big
Parallel side, arc outside, and multiple holes in arc outside on body.Fastening assembly also includes the second mounting blocks, should
Second mounting blocks are affixed to body and with one or more holes, wherein multiple holes in the first mounting blocks are oriented generally
One or more holes in the second mounting blocks.
According to still another embodiment of the invention there is provided the removable swirler assembly in a kind of burner, it includes
The body of generic cylindrical, prostheses, and the multiple leaves extended between prostheses and the body of generic cylindrical
Piece.Removable swirler assembly also includes the first mounting blocks for being affixed to the body of generic cylindrical, wherein first installs
Block have above, it is opposite behind, substantially parallel side, outside arc, and outside arc in multiple holes.It is removable
The swirler assembly removed also includes being affixed to body and the second mounting blocks with one or more holes, wherein removable rotation
Stream device is fastened to burner by multiple removable fasteners at the first and second mounting blocks.
The attendant advantages and feature of the present invention will be explained partly in the following description, and when checking hereafter by part
Ground is made apparent from for a person skilled in the art, or can be understood by the practice of the present invention.Now will be specific
With reference to the accompanying drawings to describe the present invention.
Brief description of the drawings
Describe the present invention in detail referring to the drawings, in the accompanying drawings：
Fig. 1 is the partial section of the gas-turbine unit of prior art, wherein the reality according to the present invention can be used
Apply the combustion system of example；
Fig. 2 is the section of the gas turbine combustor for the prior art that can be operated in Fig. 1 gas-turbine unit
Figure；
Fig. 3 is the perspective view for the combustion liner for including embodiments of the invention；
Fig. 4 is the sectional view of the combustion liner including embodiment according to embodiments of the invention；
Fig. 5 is the alternative view in the section for the Fig. 4 for including embodiments of the invention；
Fig. 6 is the sectional view of the combustion liner intercepted through swirler assembly according to embodiments of the invention；
Fig. 7 is the alternative view in the section of Fig. 6 according to embodiments of the invention；
Fig. 8 is the perspective view of the swirler assembly part of the combustion liner of Fig. 3 according to embodiments of the invention；
Fig. 9 is the combustion liner through Fig. 3 in the section including swirler assembly according to embodiments of the invention
The detailed sectional view of intake section interception；And
Figure 10 is the partial section of the swirler assembly of the combustion liner according to embodiments of the invention.
Embodiment
Subject of the present invention is specifically described herein, to meet legal requirements.However, describing itself to be not intended to limit this
The scope of patent.On the contrary, inventor has conceived, it is desirable to which the theme of protection can also be realized otherwise, with existing with other
Or WeiLai Technology includes those similar different components, Component composition, step or the step with illustrating in the literature in combination
Combination.
Referring initially to Fig. 1, the gas-turbine unit 100 of prior art is depicted in partial cross section.Gas turbine is sent out
Motivation 100 generally includes the shell 102 of encapsulating engine major part.Axle 104 axially extends along engine axis A-A,
And it is connected to compressor 106 and turbine 108.Compressor 106 receives air by entrance area 110, and air is directed across
Decrescence size rotation and static airfoil staggered row, to be passed through compressed air in air, so as to increase air
Temperature and pressure.Compressed air is then channeled through one or more combustion systems 112, here, fuel and air are mixed
It is combined and lights to form hot combustion gas.Hot combustion gas are then guided in turbine 108, and pass through cumulative size
Rotation and static airfoil staggered row, driven to make fluid expansion and the energy of burning gases to be converted into mechanical work
Axle 104.Axle 104 can also be connected to the axle of generator, for generating (not shown).
Fig. 2 discloses the section of the burner 200 of the gas-turbine unit of prior art.Therefore, the typical gas whirlpool
Taking turns burner 200 includes shell 202, lid 204, one or more fuel injectors 206 and combustion liner 208.Transition piece 210 will
Combustion liner 208 is connected to the entrance of turbine 212.
The present invention is illustrated in detail in Fig. 3-10, and is disclosed for being used in the burner of gas-turbine unit
New and improved removable swirler assembly.Referring initially to Fig. 3-7, disclose with removable swirler assembly 332
Combustion liner 300.Combustion liner 300 includes the bush body 302 of generic cylindrical, and bush body 302 has arrival end
304th, the port of export 306 or outlet side, and extend through the axis B-B of burner.Essentially cylindrical section of combustion liner 300
Face, it will be appreciated that, combustion liner 300 can change in shape, with tapered segment or change the section of diameter.Burning
Bushing 300 is generally made up of rolled metal piece, rolled metal piece seam welds, and may depend on specific burning vertically
Geometry and the cylindrical structural for forming or being extended to change.Combustion liner 300 is preferably by high temperature alloy such as Haynes 230
It is made, it is resistant to the elevated burner conditions more than approximate 1500 degrees Fahrenheit.Candidate materials can be used, such as
Hastelloy-X or Inconel.
Combustion liner 300 also includes the entrance ring cage 308 being affixed on generic cylindrical body 302.Such as institute in Fig. 3-7
The entrance ring cage 308 shown is made up of a series of heart axles 310 generally axially oriented for being connected to front ring 312, and from burning
The arrival end 304 of bushing 300 extends forward.Front ring 312 is used for a certain distance from being positioned to have from combustion liner 300 to be formed
The matched position of one group of fuel nozzle (not shown), so as to which fuel nozzle to be positioned to the appropriate axial location in burner.Enter
Choma cage 308 can be the component or casting of manufacture, and be preferably made up of stainless steel material.Referring now to Figure 10, entrance ring cage 308
Also include multiple lugs 309, lug 309 is extended radially inwardly from entrance ring cage 308, premix device assembly 330 for being connected, such as
It is discussed more fully below.Lug 309 can be separately made, and as entrance ring cage 308 a part be welded into
Choma cage 308 or casting.
Referring to Fig. 4-7, combustion liner 300 also includes premix device assembly 330.One component of premixed device 330 be one or
More removable cyclones 332.Referring now to Fig. 8-10, swirler assembly 332 is plotted as in premix device assembly 330.
Swirler assembly 332 includes premix barrel 342, and premix barrel 342 has arrival end 342A and opposite port of export 342B, and extension
Through its longitudinal axis C-C.Swirler assembly 332 also includes premixed swirl device 336, and premixed swirl device 336 is positioned at premix barrel
In 342, there are multiple moving blades 338 in this premixed swirl device 336, for eddy flow is given through the logical of premix barrel 342
Excessively stream.For the embodiment drawn in Fig. 8-10, premix barrel 342 is generally cylindrical.However, premix barrel 342 is alternative
Shape is also possible.
Swirler assembly 332 also includes two mounting blocks, for swirler assembly is connected in into gas turbine combustor
In.First mounting blocks 344 adjacent to premix barrel 342 arrival end 342A along premix barrel 342 outer wall positioning.First mounting blocks 344
With the first above 344A, opposite first flank 344B, a pair of substantially parallel sides 345, and outside 347.Outside 347
There can be the arcuate shape of the part at least along outside, so that mounting blocks 344 meet the shape of entrance ring cage 308.Outside 347
For setting the radial position of swirler assembly 332 and its contact with entrance ring cage 308, to allow the phase of swirler assembly 332
For the tighter size Control of fuel nozzle.As shown in figure 8, the first mounting blocks 344 also include multiple first holes 348, the first hole
During 348 are located at 347 outside arc, and it is oriented the longitudinal axis C-C for being essentially perpendicular to premix barrel 342.
Swirler assembly 332 also include the second mounting blocks 346, its along premix barrel 342 outer wall positioning and with first install
Block 344 is spaced axial distance.Second mounting blocks 346 have second face 346A and opposite second flank 346B, herein second
346B is processed to predefined size below, to form specific axial extent, for swirler assembly 332 is arranged on into burning
Appropriate axial location in device.In order to which swirler assembly 332 is positioned at into appropriate axial location, the second mounting blocks 346 include adding
Work moves back mouth (relief cut) 360 earnestly into second flank 346B.Second mounting blocks 346, which also have, to be essentially perpendicular to
The side in multiple first holes 348 extends up through one or more second holes 356 of the second mounting blocks 346.
For the embodiments of the invention drawn in Fig. 8-10, the second mounting blocks 346 and the first mounting blocks 344 are directly axially
Alignment.However, depending on burner geometry, the first and second mounting blocks 344 and 346 can not be axially aligned, but on
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.Difference for mounting blocks
Attachment method is possible.In one embodiment, the first mounting blocks 344 and the second mounting blocks 346 are welded to premix barrel 342.
The bead (compatible between premix barrel 342 and mounting blocks 344 and 346 material) of compatible welding material be laid in mounting blocks with
The intersection of premix barrel 342.
The alternative approach that first and second mounting blocks 344 and 346 are affixed into premix barrel 342 is by hard-welded joint
(braze joint).Hard-welded joint will be helpful to form more complete joint, because the mounting blocks contacted with premix barrel 342
Whole surface is attached to premix barrel 342.On the contrary, mounting blocks are connected by the edge that welding point only contacts premix barrel in mounting blocks
To premix barrel 342.
In another embodiment, it is integral that mounting blocks 344 and 346, which are possible to premix barrel 342,.By the He of mounting blocks 344
346 are attached in premix barrel 342 and can be realized by casting or forging.
Accurate size, interval and the amount alterable in the first mounting blocks 344 and the hole in the second mounting blocks 346, and depend on
In many factors, e.g., the mechanical and heat in burner geometry, the size of swirler assembly 332, and swirler assembly 332
Load.For the embodiments of the invention drawn in Fig. 8-10, the first mounting blocks 344 include two the first holes 348, wherein first
Hole 348, which is oriented, is essentially perpendicular to longitudinal axis C-C.Second mounting blocks 346 include one or more second holes 356, and figure
Embodiment shown in 8-10 uses single second hole 356.However, it is possible to the second more than one hole 356 be needed, to incite somebody to action
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 described above, swirler assembly 332 is designed to be able to easily remove from burner, to be preferably easy to safeguard and
Repair.Therefore, multiple removable fasteners 350 and 358 are used to swirler assembly 332 being connected in the burner.At one
In embodiment, removable fastener (such as bolt) engages pair in multiple first holes 348 and one or more second holes 356
The thread pattern answered.Thread pattern is only a kind of mode of connected removable fastener.Alternatively, one or more second
Hole 356 can be through hole (that is, non-threaded), and use neighbouring surface 346A nut.In addition, bolt/stud it is solderable/install,
To substitute on the hole 356 with nut, the surface for being subsequently placed in dome plate 334.
Swirler assembly 332 is positioned to connect with adjacent pipe 352 (also referred to as vacuum suction (hoover)) fluid
Logical, 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 are positioned to neighbouring or are slightly bonded in pipe 352.In order to ensure swirler assembly 332 is appropriate in combustion liner
Radial position and with pipe 352 formation radial gap, multiple spacers 354 surround premix barrel 342 in each outer surface positioning,
Neighbouring port of export 342B.
As described above, swirler assembly 332 is removable by multiple fasteners 350 and 358 (such as bolt or other devices)
Ground is affixed to burner.For example, and as shown in figures 6-10, main cyclone device assembly 332 is by means of through the first hole 348 and second
The fastener 350 and 358 in hole 356 is affixed to dome plate 334.By using the He of fastener 350 radially and axially oriented
358, realize more preferable positioning and tolerance control of the swirler assembly 332 relative to premix device assembly 330 and combustion liner 300
System.In addition, by the way that swirler assembly 332 is removedly affixed into premix device assembly 330, for checking and repairing premixed device group
The path of part 330 is significantly improved compared to the prior art burner with the swirler assembly for being welded to premix device assembly.
As those skilled in the art will recognize that, in addition to Reachability question, the welding of swirler assembly also causes cyclone group
The deformation of part, this so as to influence flow control.
Swirler assembly 332 is preferably made up of the material (such as a kind of stainless steel) similar with premix device assembly 330.Cyclone
Component 332 can also be manufacture component or casting with various processing parts.
Referring now to Fig. 9 and 10, swirler assembly 332 is shown as being arranged in premix device assembly 330.As described above, eddy flow
Device assembly 332 is connected in place by fastener 350 and 358, and direction is oriented fastener 350 and 358 radially and axially.Cyclone
Component 332 slips into appropriate location so that spacer 354 provides the radial gap relative to pipe 352, and the second mounting blocks 346 by
The lug 309 of entrance ring cage 308 is contacted in appropriate axial positions in moving back mouth 360 earnestly.
The present invention is described on specific embodiment, specific embodiment is intended to all be exemplary rather than in all respects
Restricted.Alternative embodiment and required operation will become clear for those skilled in the art
Chu, without departing from its scope.
It will be seen that from above, together with other advantages that system and method are obvious and intrinsic, the present invention is good suitable for obtaining
All results described above and purpose.It will be appreciated that some features and sub-portfolio are useful, and can be without reference to it
Used in the case of his feature and sub-portfolio.This is by the conception of the scope of claim and within the scope of the claims.
Claims (17)
1. a kind of swirler assembly (332) for gas turbine combustor, it includes：
Premix barrel (342), it has arrival end (342A), the opposite port of export (342B) and extend through its longitudinal axis (C-
C)；
Premixed swirl device (336), it is positioned in the premix barrel (342), and the cyclone (336), which has, to be used to give eddy flow
Give multiple moving blades (338) by stream；
First mounting blocks (344), its outer wall positioning adjacent to the arrival end (342A) along the premix barrel (342) and with many
Individual first hole (348), the multiple first hole (348), which is oriented, is essentially perpendicular to the longitudinal axis (C-C)；With
Second mounting blocks (346), its outer wall along the premix barrel (342) is positioned to have one from first mounting blocks (344)
Determine axial distance, second mounting blocks (346) have one or more second holes (356), one or more the
Two holes (356) edge extends through second mounting blocks (346) perpendicular to the direction of the multiple first hole (348).
2. swirler assembly (332) according to claim 1, it is characterised in that the premix barrel (342) is substantially justified
Taper.
3. swirler assembly (332) according to claim 1, it is characterised in that first mounting blocks (344) and second
Each in mounting blocks (346) is affixed to the premix barrel (342) by welding or hard-welded joint.
4. swirler assembly (332) according to claim 1, it is characterised in that many in first mounting blocks (344)
Individual hole (348) includes at least two holes.
5. swirler assembly (332) according to claim 1, it is characterised in that one or more the second hole
(356) to be threaded.
6. swirler assembly (332) according to claim 1, it is characterised in that second mounting blocks (346) have the
(346A) and opposite second flank (346B) before two, wherein the second flank (346B) is finish-machined to predetermined axial chi
It is very little.
7. a kind of multiple spot, multi-direction fastening assembly (350,358) for being used in gas turbine combustor, it includes：
The first mounting blocks (344) on the body for the swirler assembly being affixed in the gas turbine combustor, described first
Mounting blocks (344) have first before (344A), opposite first flank (344B), a pair of side (345), outside (347) and
Multiple holes (348) in the outside (347)；With
The second mounting blocks (346) of the body are affixed to, second mounting blocks (346) are with one be located therein or more
Multiple holes (356)；
Wherein, second mounting blocks (346) are spaced certain axial distance with first mounting blocks (344).
8. fastening assembly (350,358) according to claim 7, it is characterised in that the outside (347) is at least in bag
Enclose at the region of the multiple hole (348) for arc.
9. fastening assembly (350,358) according to claim 7, it is characterised in that first mounting blocks (344) and
Second mounting blocks (346) are affixed to the body by welding or hard-welded joint.
10. fastening assembly (350,358) according to claim 7, it is characterised in that first and second mounting blocks
(344,346) it is integral with the body.
11. fastening assembly (350,358) according to claim 7, it is characterised in that in first mounting blocks (344)
The multiple hole (348) be essentially perpendicular to one or more holes (356) in second mounting blocks (346).
12. the removable swirler assembly (332) in a kind of burner, it includes：
The body (342) of generic cylindrical；
Prostheses (336), it is positioned at the cylinder adjacent to the entrance (342A) of the body (342) of the generic cylindrical
In the body (342) of shape；
Multiple blades (338), it extends between the prostheses (336) and the body (342) of the generic cylindrical；
First mounting blocks (344), it is affixed to the body (342) of the generic cylindrical, the first mounting blocks (344) tool
Have before first (344A), it is opposite behind (344B), a pair of sides (345), and with the multiple holes (348) being located therein
Outside (347)；With
Second mounting blocks (346), it is affixed to the body (342) of the generic cylindrical, the second mounting blocks (346) tool
There are one or more holes (356) being located therein；
Wherein, the removable cyclone (332) is pacified by multiple removable fasteners (350,358) described first
The burner is fastened at both dress block (344) and the second mounting blocks (346).
13. removable swirler assembly (332) according to claim 12, it is characterised in that the multiple blade
(338) be oriented to by eddy flow give air and fuel by stream.
14. removable swirler assembly (332) according to claim 12, it is characterised in that first mounting blocks
(344) the big circumferential distance of the second mounting blocks (346) described in ratio of elongation.
15. removable swirler assembly (332) according to claim 12, it is characterised in that first mounting blocks
(344) multiple holes (348) in are essentially perpendicular to the single hole (356) in second mounting blocks (346).
16. removable swirler assembly (332) according to claim 12, it is characterised in that also including multiple fastenings
Part (350,358), the multiple fastener (350,358) is placed in multiple openings (348) of first mounting blocks (344)
In, for the cyclone (332) is affixed into the burner.
17. removable swirler assembly (332) according to claim 12, it is characterised in that first mounting blocks
(344) outside (347) is arc at least at the region in neighbouring the multiple hole (348).
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 CN105121963A (en) | 2015-12-02 |
| CN105121963B true 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) | US20140318140A1 (en) |
| JP (2) | JP2017516007A (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 |
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| 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 |
| 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 |
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| 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 |
| US6993916B2 (en) * | 2004-06-08 | 2006-02-07 | General Electric Company | Burner tube and method for mixing air and gas in a gas 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 |
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| US7513098B2 (en) * | 2005-06-29 | 2009-04-07 | Siemens Energy, Inc. | Swirler assembly and combinations of same in gas turbine engine combustors |
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| US8272224B2 (en) * | 2009-11-02 | 2012-09-25 | General Electric Company | Apparatus and methods for fuel nozzle frequency adjustment |
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2014
- 2014-04-18 US US14/256,025 patent/US20140318140A1/en not_active Abandoned
- 2014-04-18 US US14/256,022 patent/US20140318150A1/en not_active Abandoned
- 2014-04-18 US US14/256,023 patent/US20140318139A1/en not_active Abandoned
- 2014-04-24 WO PCT/EP2014/058338 patent/WO2014174012A1/en active Application Filing
- 2014-04-24 JP JP2016509465A patent/JP2017516007A/en active Pending
- 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 KR KR1020157033470A patent/KR20160023657A/en not_active Application Discontinuation
- 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
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| 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 |
| 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 |
|---|---|
| US20140318150A1 (en) | 2014-10-30 |
| US20140318140A1 (en) | 2014-10-30 |
| MX2015014400A (en) | 2016-06-21 |
| JP2017516007A (en) | 2017-06-15 |
| WO2014174012A1 (en) | 2014-10-30 |
| WO2014174009A1 (en) | 2014-10-30 |
| KR20160023657A (en) | 2016-03-03 |
| CN105121963A (en) | 2015-12-02 |
| US20140318139A1 (en) | 2014-10-30 |
| WO2014174011A1 (en) | 2014-10-30 |
| JP2016516976A (en) | 2016-06-09 |
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Address after: Baden, Switzerland Applicant after: ALSTOM TECHNOLOGY LTD Address before: Baden, Switzerland Applicant before: Alstom Technology Ltd. |
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