CN101995021A - Integral liner and venturi for eliminating air leakage - Google Patents
Integral liner and venturi for eliminating air leakage Download PDFInfo
- Publication number
- CN101995021A CN101995021A CN2010102671341A CN201010267134A CN101995021A CN 101995021 A CN101995021 A CN 101995021A CN 2010102671341 A CN2010102671341 A CN 2010102671341A CN 201010267134 A CN201010267134 A CN 201010267134A CN 101995021 A CN101995021 A CN 101995021A
- Authority
- CN
- China
- Prior art keywords
- venturi tube
- tube section
- liner assembly
- combustion liner
- sleeve pipe
- 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
Links
Images
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
-
- 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
- F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The inventon relates to an integral liner and a venturi for eliminating air leakage. A combustion liner assembly for a gas turbine combustor includes a plurality of fuel nozzles disposed circumferentially about a central axis of the combustor, and a venturi section disposed downstream of the fuel nozzles and connected to a head end of the liner assembly. The venturi section defines an annular throat area downstream of the fuel nozzles. A liner sleeve is connected to and commences at a downstream end of the venturi section. At least a portion of the venturi section serves as a liner upstream of the liner sleeve.
Description
Technical field
The present invention relates to be used for minimize or eliminate the apparatus and method of the diluent air leakage paths of gas turbine combustor, and more specifically, the present invention relates to be used to manage diluent air and leak to realize the apparatus and method of lower emission level.
Background technology
Such as everyone knows, a large amount of combustion products in the combustion gas turbine discharging are that nitrogen oxide (promptly is generically and collectively referred to as NO and the NO of NOx
2), carbon monoxide CO and unburned hydrocarbon and other particulate.Proposed and used various systems to reduce discharging.For example, in the past, used with the combustion zone of water and steam injection gas turbine combustor, from the NOx of combustion turbine exhaust and catalysis type purification and the dry type low-NOx combustor of CO.Also used lining sleeve pipe and the discharge of the compressor in the transition piece diluent air of introducing burner to reduce emission.
Desirable will be to reduce or eliminate leakage substantially, make preserve the air stream in the more not crucial zone, and make it more consistent between jar and jar.In addition, desirable will be to reduce or eliminate leakage substantially, and making to increase air stream in the mode of more disperseing and mix uniformly by mix aperture in Free Region.
Summary of the invention
In one exemplary embodiment, a kind of combustion liner assembly that is used for gas turbine combustor comprises a plurality of fuel nozzles around the central axis that circumferentially is arranged on burner, and is arranged on the downstream of fuel nozzle and is connected to Venturi tube section on the head end of bush assembly.The Venturi tube section defines annular throat region in the downstream of fuel nozzle.The lining sleeve pipe is connected on the downstream of Venturi tube section, and starts from this downstream end.At least a portion of Venturi tube section is as the lining of the upstream of lining sleeve pipe.
In another exemplary embodiment, a kind ofly reduce the Venturi tube section of the combustion liner assembly in the combustion gas turbine and the method for the air flow losses between the lining sleeve pipe may further comprise the steps: with at least a portion of Venturi tube section lining as the upstream of lining sleeve pipe; And provide circular weld at the junction surface between Venturi tube section and lining sleeve pipe place with at the Venturi tube section and the place, the junction surface between the head end of combustion liner assembly.
In another exemplary embodiment, a kind of combustion liner assembly that is used for gas turbine combustor comprises by circular weld and is connected to Venturi tube section on the head end of bush assembly, wherein, the Venturi tube section defines annular throat region in bush assembly; And be connected on the downstream of Venturi tube section and start from the lining sleeve pipe of this downstream end, wherein, the lining sleeve pipe is connected on the downstream of Venturi tube section by circular weld.At least a portion of Venturi tube section is as the lining of the upstream of lining sleeve pipe.
Description of drawings
Fig. 1 is half the sectional view of deciding what is right and what is wrong of the combustion liner assembly around the burner center line;
Fig. 2 has shown an embodiment who has as the Venturi tube section of the part of lining;
Fig. 3 is a kind of alternative design;
Fig. 4 has shown another embodiment that uses connector;
Fig. 5 is the sectional view of another alternative; And
Fig. 6 is the sectional view of another embodiment.
List of parts
10 combustion liner assemblies
12 cover centerbodies
14 lining sleeve pipes
16 main fuel spray nozzle cup assemblies
18 Venturi tube sections
20 cener lines
22 cyclones
24 apertures along circumferentially spaced
26 neck bush/wall
28 external bushings/wall
30 radially inner side summits
32 throat region
34 inner wall section
36 outer wall sections
38 flanges
40 flanges
42 rivets
44 rivets along circumferentially spaced
46 ring-shaped air chambers
50 apertures
62 head ends
64 circular welds
66 circular welds
68 expansion joints or slip joint
681 fork-shaped sections
682 straight sections
69 apertures
70 connector parts
72 newel posts
74 fen beginning
The specific embodiment
Referring to accompanying drawing,, shown and be appointed as 10 combustion liner assembly substantially now that it comprises cover centerbody 12, lining sleeve pipe 14, main fuel spray nozzle cup assembly 16 and Venturi tube section 18 especially referring to Fig. 1.Will be appreciated that combustion liner assembly 10 around cener line 20 textural for cylindrical or annular, and a plurality of main fuel spray nozzle 16 around axis 20 each other along circumferentially spaced.Cyclone 22 is shown as the part of cover centerbody 12.Lining sleeve pipe 14 has the inlet that comprises a plurality of apertures 24 along circumferentially spaced, and aperture 24 receives from the compressor of the air chamber (not shown) between combustion liner assembly and the burning flowing sleeve/housing and discharges air.Venturi tube 18 comprises the prefabricated double-walled loop configuration that is arranged in the lining sleeve pipe 14, and comprises neck bush/wall 26 and external bushing/wall 28.Venturi tube 18 has the radially inner side summit 30 that defines throat region 32 with center cover body 12.The neck bush 26 of Venturi tube 18 and external bushing 28 comprise inner wall section 34 and outer wall section 36 respectively, and inner wall section 34 and outer wall section 36 are upstream and extend radially outward towards cup assembly 16 vertically. Wall part 34 and 36 stops in a pair of flange 38 and 40 respectively, and flange 38 and 40 curves, to extend on axial direction downstream.Flange can be fixed on the lining sleeve pipe 14 by rivet 42.In the prior art design, the external bushing 28 of Venturi tube section 18 also is fixed on the lining sleeve pipe 14 in the downstream of Venturi tube by a plurality of rivets 44 along circumferentially spaced.As illustrating best among Fig. 1, lining sleeve pipe 14 radially caves inward, and with the external bushing 28 of covering Venturi tube 18, thereby is formed for making lining sleeve pipe 14 and outer venturi pipe-in-pipe 28 to be fixed on the recessed band of going up each other in itself.
The deviation that has been found that the leakage path of the diluent air that is fed to burner has very big influence to discharging, and these deviations are results of the assembling of component tolerances and parts.For example, the main leakage path of being concerned about is between the outer tube 28 of lining sleeve pipe 14 and Venturi tube 18, in the zone of rivet 44.What will see is, the compressor that is fed to ring-shaped air chamber 46 from the outside of combustion liner by aperture 24 is discharged air and can be revealed by the riveted type connector.But,, have been found that deviation, and therefore, discharging will change to some extent through the leakage flow of riveted joint about various identical burners.Also do not identify or control those dischargings that cause by the leakage path conductance before this.
For by the aperture 50 in the outer venturi pipe-in-pipe 28 from air chamber 46 flow to inner venturi tube sleeve pipe 26 and outside diluent air the space between the venturi pipe-in-pipe 28 (difference), have other leakage path.Between (the dividing other) neck bush 34 of this other leakage path process Venturi tube 18 and the flange 38 and 40 of external bushing 36.Though these flanges 38 and 40 are engaged with each other in the past and are riveted on the lining sleeve pipe 14,, thereby cause the surface to go up the discharging of the variation of identical burner in the gap that can occur between the flange and between combustion liner and the identical combustion liner changing.
Other leakage gap has appearred between the flange 38 and 40 of the crossover of lining sleeve pipe 14 and Venturi tube 18.Shown that these gaps are different between the burner of structure in the same manner, and therefore caused the leakage flow of the discharging that changes.And importantly Venturi tube throat region 32 must remain in the preset limit (although Venturi tube can remove to safeguard and keep in repair) from the lining sleeve pipe.It is also important that after the initial manufacturing of Venturi tube and lining sleeve pipe and be applied in the various maintenance procedures of carrying out on the burner and keep throat region at the life period of burner.
Fig. 2 and 5 has shown an exemplary embodiment with monoblock type Venturi tube section and lining, and it has reduced or eliminated substantially reveals the zone and reveal loss.As shown in the figure, Venturi tube section 18 is connected on the head end 62 of bush assembly.As existing design, the flange 38,40 of wall part 34,36 is extending on axial direction downstream.But, in the embodiment shown in Figure 2, in the upstream extremity of Venturi tube section 18 is fixed to zone between the downstream of residing position and Venturi tube section 18 on the head end 62, removed lining sleeve pipe 14.The upstream extremity of circular weld 64 sealing Venturi tube sections 18 and the junction surface between the head end 62.In addition, the downstream of Venturi tube section 18 is connected on the lining sleeve pipe 14 by circular weld 66.Like this, the part of Venturi tube section 18 just is used as the lining of the upstream of the lining sleeve pipe 14 that shortens.This structure combines Venturi tube section 18 and lining sleeve pipe 14 effectively.
Fig. 3 has shown that use comprises fork-shaped section 681 and the expansion joint (expansion joint) of straight section 682 or the more complicated design of slip joint 68.In this embodiment, fork-shaped section 681 is whole with 18 one-tenth of head end 62 and Venturi tube sections.Thereby, eliminated in the leakage path that is connected to the Venturi tube section connector place on the head end.The cooling air transmits by the aperture 69 in the straight section 682.If air is revealed around slip joint 68, then it is to the not influence of performance of burner, because allowed the aperture 69 of air from outermost jacket wall to enter in the hollow Venturi tube cavity.
In Fig. 4, shown another alternative.In this embodiment, the connector component 70 that is preferably the connector component of machining is connected to Venturi tube section 18 on the head end 62.As shown, in preferred structure, connector component 70 is a Y shape, comprises newel post 72 and branch beginning 74.Divide the beginning 74 to be welded on the inner and outer wall of Venturi tube section 18, the score beginnings 74, thicker newel post 72 then was welded on the head end 62.By this connector component, removed the bigger zone of combustion liner 14.Arrow A among Fig. 4 shows the axial length that lining is removed thereon.
Fig. 6 shows another alternative.In this embodiment, the gapped and leakage path of institute between Venturi tube section 18 and the head end 62 and between Venturi tube section 18 and the lining sleeve pipe 14 is via lip ring (for example by brazing etc.) sealing.At assembly process, but the lining head-up tilt enters in the gap by capillarity to allow brazing material.
Described embodiment has reduced or eliminated the air flow losses between venturi tube wall and the jacket wall significantly.Compare with air drainage is revealed in the direct stream, eliminate air flow losses and will allow to use more consistent air to flow in the fuel air mixture in the head end combustion zone.Described simple structure uses and the similar parts and the technology that exist in existing design.Embodiment is easy to make, and will jar with jar between produce more repeatably air stream, and then will help to produce than existing and design better fuel-air mixed mode, also reduce burning and exhausting simultaneously.The air drainage that this design has has significantly reduced or eliminated in the zone between Venturi tube and the jacket wall is revealed, and making can be by mix aperture to come to use air stream than the mode of disperseing more and mixing uniformly about existing design in the zone.Member can be regulated air stream as the control point, thereby make and can use because the other air stream that the air flow losses that reduces obtains reduces discharging, and reduce jar and jar between deviation.
Though invention has been described in conjunction with the content that is considered to the most practical and preferred embodiment at present, but will be appreciated that, the invention is not restricted to disclosed embodiment, but opposite, the invention is intended to cover various modifications and equivalent arrangements in the spirit and scope that are included in appending claims.
Claims (10)
1. combustion liner assembly that is used for gas turbine combustor, described combustion liner assembly comprises:
A plurality of fuel nozzles (16) on every side along the central axis that circumferentially is arranged on described burner;
Be arranged on the downstream of described fuel nozzle and be connected to Venturi tube section (18) on the head end (62) of described bush assembly, described Venturi tube section defines annular throat region (32) in the downstream of described fuel nozzle; And
Be connected on the downstream of described Venturi tube section and start from the lining sleeve pipe (14) of described downstream end,
Wherein, at least a portion of described Venturi tube section is as the lining of the upstream of described lining sleeve pipe.
2. combustion liner assembly according to claim 1 is characterized in that, described lining sleeve pipe (14) is connected on the described downstream of described Venturi tube section (18) by circular weld (64).
3. combustion liner assembly according to claim 1 is characterized in that, described Venturi tube section (18) is connected on the described head end (62) by circular weld (66).
4. combustion liner assembly according to claim 1 is characterized in that, described combustion liner assembly further comprises described Venturi tube section (18) is connected to connector component (70) on the described head end (62).
5. combustion liner assembly according to claim 4, it is characterized in that, described Venturi tube section (18) comprises double-walled construction, described double-walled construction comprises inwall (34) and outer wall (36), and wherein, described connector component (70) is the Y shape that comprises newel post (72) and divide the beginning (74), and described minute beginning was welded on the described inwall and described outer wall of described Venturi tube section, and described newel post is welded on the described head end (62).
6. combustion liner assembly according to claim 5 is characterized in that, the described newel post (72) of described connector component (70) is thicker than the described minute beginning (74).
7. combustion liner assembly according to claim 1, it is characterized in that, the upstream extremity of described Venturi tube section (18) stops in flange (38), described flange (38) is crooked and extend vertically along downstream direction, wherein, described flange is fixed on the described head end (62) by a plurality of rivets (42), and wherein, described flange seals by circular weld.
8. combustion liner assembly according to claim 1, it is characterized in that, seal by lip ring at the gapped and leakage paths of institute between described Venturi tube section (18) and the described head end (62) and between described Venturi tube section and described lining sleeve pipe (14).
9. in combustion gas turbine, a kind of Venturi tube section (18) of combustion liner assembly and method of the air flow losses between the lining sleeve pipe (14) of reducing, described method comprises:
At least a portion of described Venturi tube section is used as the lining of the upstream of described lining sleeve pipe; And
Place, junction surface and place, the junction surface between the head end of described Venturi tube section and described combustion liner assembly between described Venturi tube section and described lining sleeve pipe provide circular weld (64,66).
10. method according to claim 9 is characterized in that, described method further comprises to be used because the extra air of the air flow losses that reduces flows, to allow that consistent more air stream is arranged in the fuel-air mixture in described head end (62).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/543,066 US20110041507A1 (en) | 2009-08-18 | 2009-08-18 | Integral Liner and Venturi for Eliminating Air Leakage |
| US12/543066 | 2009-08-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101995021A true CN101995021A (en) | 2011-03-30 |
Family
ID=43604185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010102671341A Pending CN101995021A (en) | 2009-08-18 | 2010-08-18 | Integral liner and venturi for eliminating air leakage |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20110041507A1 (en) |
| JP (1) | JP2011038766A (en) |
| CN (1) | CN101995021A (en) |
| CH (1) | CH701708A2 (en) |
| DE (1) | DE102010036887A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102313469A (en) * | 2011-09-30 | 2012-01-11 | 茂名重力石化机械制造有限公司 | Assembled and welded plate fin type air preheater |
| CN105135476A (en) * | 2015-09-17 | 2015-12-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Lining assembly |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8886334B2 (en) * | 2008-10-07 | 2014-11-11 | Mc10, Inc. | Systems, methods, and devices using stretchable or flexible electronics for medical applications |
| US9723122B2 (en) | 2009-10-01 | 2017-08-01 | Mc10, Inc. | Protective cases with integrated electronics |
| US20110218756A1 (en) * | 2009-10-01 | 2011-09-08 | Mc10, Inc. | Methods and apparatus for conformal sensing of force and/or acceleration at a person's head |
| US20110247340A1 (en) * | 2010-04-13 | 2011-10-13 | Predrag Popovic | Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly |
| US20120047895A1 (en) * | 2010-08-26 | 2012-03-01 | General Electric Company | Systems and apparatus relating to combustor cooling and operation in gas turbine engines |
| US20130091847A1 (en) * | 2011-10-13 | 2013-04-18 | General Electric Company | Combustor liner |
| CN112283747B (en) * | 2020-10-29 | 2022-08-16 | 中国航发湖南动力机械研究所 | Combustion chamber and aeroengine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4149373A (en) * | 1977-08-29 | 1979-04-17 | United Technologies Corporation | Combustion chamber stress reducing means |
| US4292801A (en) * | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
| CN101067497A (en) * | 2006-05-04 | 2007-11-07 | 通用电气公司 | A method and arrangement for expanding a primary and secondary flame in a combustor |
| CN101349425A (en) * | 2007-07-16 | 2009-01-21 | 通用电气公司 | Apparatus/method for cooling combustion chamber/venturi in a low NOx combustor |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5127221A (en) * | 1990-05-03 | 1992-07-07 | General Electric Company | Transpiration cooled throat section for low nox combustor and related process |
| US5201887A (en) * | 1991-11-26 | 1993-04-13 | United Technologies Corporation | Damper for augmentor liners |
| US5487275A (en) * | 1992-12-11 | 1996-01-30 | General Electric Co. | Tertiary fuel injection system for use in a dry low NOx combustion system |
| US6374594B1 (en) * | 2000-07-12 | 2002-04-23 | Power Systems Mfg., Llc | Silo/can-annular low emissions combustor |
| US6427446B1 (en) * | 2000-09-19 | 2002-08-06 | Power Systems Mfg., Llc | Low NOx emission combustion liner with circumferentially angled film cooling holes |
| US6651437B2 (en) * | 2001-12-21 | 2003-11-25 | General Electric Company | Combustor liner and method for making thereof |
| US6832482B2 (en) * | 2002-06-25 | 2004-12-21 | Power Systems Mfg, Llc | Pressure ram device on a gas turbine combustor |
| US6865892B2 (en) * | 2002-12-17 | 2005-03-15 | Power Systems Mfg, Llc | Combustion chamber/venturi configuration and assembly method |
| US6951109B2 (en) * | 2004-01-06 | 2005-10-04 | General Electric Company | Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly |
-
2009
- 2009-08-18 US US12/543,066 patent/US20110041507A1/en not_active Abandoned
-
2010
- 2010-08-06 DE DE102010036887A patent/DE102010036887A1/en not_active Withdrawn
- 2010-08-16 CH CH01311/10A patent/CH701708A2/en not_active Application Discontinuation
- 2010-08-16 JP JP2010181516A patent/JP2011038766A/en not_active Withdrawn
- 2010-08-18 CN CN2010102671341A patent/CN101995021A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4149373A (en) * | 1977-08-29 | 1979-04-17 | United Technologies Corporation | Combustion chamber stress reducing means |
| US4292801A (en) * | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
| CN101067497A (en) * | 2006-05-04 | 2007-11-07 | 通用电气公司 | A method and arrangement for expanding a primary and secondary flame in a combustor |
| CN101349425A (en) * | 2007-07-16 | 2009-01-21 | 通用电气公司 | Apparatus/method for cooling combustion chamber/venturi in a low NOx combustor |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102313469A (en) * | 2011-09-30 | 2012-01-11 | 茂名重力石化机械制造有限公司 | Assembled and welded plate fin type air preheater |
| CN105135476A (en) * | 2015-09-17 | 2015-12-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Lining assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2011038766A (en) | 2011-02-24 |
| CH701708A2 (en) | 2011-02-28 |
| US20110041507A1 (en) | 2011-02-24 |
| DE102010036887A1 (en) | 2011-05-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101995021A (en) | Integral liner and venturi for eliminating air leakage | |
| EP2216596B1 (en) | A fuel nozzle | |
| CN100523456C (en) | Apparatus and methods for minimizing and/or eliminating dilution air leakage in a combustion liner assembly | |
| US10502426B2 (en) | Dual fuel injectors and methods of use in gas turbine combustor | |
| US8528839B2 (en) | Combustor nozzle and method for fabricating the combustor nozzle | |
| JP5468812B2 (en) | Combustor assembly and fuel nozzle for gas turbine engine | |
| US20100205970A1 (en) | Systems, Methods, and Apparatus Providing a Secondary Fuel Nozzle Assembly | |
| US7908863B2 (en) | Fuel nozzle for a gas turbine engine and method for fabricating the same | |
| JP6514493B2 (en) | Premixer assembly for mixing combustion air and fuel | |
| JP5399015B2 (en) | Fuel nozzle for gas turbine engine and method of making the same | |
| JP2005308389A (en) | Method and device for manufacturing gas turbine engine combustor | |
| US20110247340A1 (en) | Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly | |
| US11512853B2 (en) | Fuel circuit for a fuel injector | |
| US20110239654A1 (en) | Angled seal cooling system | |
| CN103542403A (en) | Combustor arrangement, especially for a gas turbine | |
| JP2011085383A (en) | High strength crossover manifold and joining method | |
| CN109642730A (en) | Fuel and air supply the burner being incorporated in the wall of burner | |
| CN203731484U (en) | Low-cyclone nozzle of combustor | |
| US20180340689A1 (en) | Low Profile Axially Staged Fuel Injector | |
| CN103822230A (en) | Low-swirl-flow nozzle of combustion chamber | |
| CN102472494B (en) | Burner, in particular for gas turbines | |
| US11255545B1 (en) | Integrated combustion nozzle having a unified head end | |
| US20170350321A1 (en) | Bundled Tube Fuel Nozzle Assembly with Tube Extensions | |
| CN107228381A (en) | Transition duct component with slow injection structure | |
| US10260752B2 (en) | Transition duct assembly with late injection features |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20110330 |