US20090053054A1 - LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS - Google Patents
LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS Download PDFInfo
- Publication number
- US20090053054A1 US20090053054A1 US11/841,053 US84105307A US2009053054A1 US 20090053054 A1 US20090053054 A1 US 20090053054A1 US 84105307 A US84105307 A US 84105307A US 2009053054 A1 US2009053054 A1 US 2009053054A1
- Authority
- US
- United States
- Prior art keywords
- venturi
- liner
- weld
- annular
- aft
- 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.)
- Abandoned
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
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- 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
Definitions
- the disclosure relates generally to a venturi for a dry low nitric oxides (NOx) emissions combustor, and more particularly to a leakage reducing venturi for a dry low nitric oxides (NOx) emissions combustor.
- NOx dry low nitric oxides
- the riveted joints located at the venturi of current dry low nitric oxides (NOx) emissions combustor (DLN combustors) allow a variable air leakage into the combustion chamber.
- This air leakage has been identified as a key contributor to combustion emissions, as well as combustor-to-combustor variation. Accordingly, a leakage reducing means for associating the venturi with the liner of DLN combustors would be desirable.
- a leakage reducing venturi for a dry low nitric oxides (NOx) emissions combustor including a substantially annular outer liner, a substantially annular inner liner, a venturi channel defined by the annular inner liner and the annular outer liner, the venturi channel including a forward end and an aft end, a forward weld disposed in proximity to the forward end of the venturi channel, the forward weld being configured to connect the annular outer liner with the annular inner liner, and an aft weld disposed in proximity to the aft end of the venturi channel, the aft weld being configured to connect the annular outer liner with the annular inner liner.
- NOx dry low nitric oxides
- FIG. 1 is a simplified representation of a cross section of a combustor including an exemplary embodiment of a leakage reducing venturi
- FIG. 2 is a simplified cross section of the leakage reducing venturi of the combustor of FIG. 2 .
- a portion of a dry low nitric oxides (NOx) emissions combustor 10 (“dry low NOx” meaning less than 9 ppm NOx) for a gas turbine is illustrated.
- the combustor 10 includes generally a combustion chamber 12 , fuel nozzles 14 (some gas turbines, as illustrated here, employ multiple nozzles in each combustor), an annual premixing chamber 16 , and a leakage reducing venturi 18 (the venturi being described in greater detail below).
- a turbine compressor (which is not shown) provides airflow into the premixing chamber 16 .
- Fuel 20 is provided to the chamber 16 via the fuel nozzles 14 , which are controlled a fuel flow controller 26 . Air is introduced to the chamber 16 via one or more entry ports 28 .
- the combustion chamber 12 is generally cylindrical in shape about a combustor centerline 30 , and is enclosed by a wall 32 and a parent liner or wall 34 .
- the fuel-air mix that enters the combustion chamber 12 from the premixing chamber 16 travels in a downstream direction, as indicated by arrows 36 .
- the fuel-air mix is constricted by convergent/divergent walls 38 and 40 of the venturi 18 .
- the flow re-circulation introduced by the venturi 18 acts as a bluff body flame holder. This causes the fuel-air mix to accelerate into the combustion chamber 12 , where it will combust and create enormous amounts of heat flux on the venturi 18 .
- the leakage reducing venturi 18 includes a substantially annular outer liner 42 , a substantially annular inner liner 44 , which are integrated into the parent liner 34 of the combustor 10 .
- the outer liner 42 and inner liner 44 define a venturi channel 46 , which includes a forward end 48 and an aft end 50 .
- the venturi channel 46 is designed to ingest cooling air (compressed air) through inlets 51 that are disposed in the outer liner 44 , and in fluid communication with the venturi channel 46 . This cooling/compressed air is provided by the turbine compressor (which is not illustrated), and creates a cooling effect on the venturi 18 .
- venturi 18 is defined to include the extents of the venturi channel 46 (i.e. the forward end 48 of the channel 46 to aft end 50 of the channel 46 ) as illustrated in FIGS. 1 and 2 .
- the venturi 18 also includes a forward weld 52 and an aft weld 54 .
- the forward weld 52 is disposed at the forward end 48 of the venturi channel 46 , such that a forward extent of the channel 46 terminates at the forward weld 52 .
- the aft weld 54 is disposed at the aft end 50 of the venturi channel 46 , such that and aft extent the channel 46 terminates at the forward weld 52 .
- the forward weld 52 and aft weld 54 are disposed at opposite ends of the venturi channel 46 .
- both the forward weld 52 and aft weld 54 connect the annular outer liner 42 with the annular inner liner 44 .
- the forward weld 52 and aft weld 54 provide these connections via a welding of the inner annular liner 42 and outer annular liner 44 to a forward y-joint 60 and aft y-joint 62 respectively.
- the y-joints 60 and 62 allow for a continuous leak free path in the channel 46 , which minimizes air leakage through venturi joints, provides a cavity for impingement cooling, and allows the venturi 18 to be constructed with acceptable stresses.
- these y-joints 60 and 62 include a generally “y” like shape, which includes three prongs 70 , 72 , and 74 .
- Prongs 70 and 72 connect the joints 60 and 62 to the two walls of the channel 46 (via welds 52 and 54 ), while prong 74 connects each joint 60 and 62 to the parent liner 34 .
- Associating the venturi 18 with the parent liner 34 of the combustor 10 via these forward and aft welds 52 and 54 (and y-joints 60 and 62 ) renders any riveted venturi joints unnecessary, and minimizes air leakage variation from combustor to combustor. This welding thus reduces emissions causing leakage into the combustion chamber 12 .
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/841,053 US20090053054A1 (en) | 2007-08-20 | 2007-08-20 | LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS |
JP2008208309A JP2009047413A (ja) | 2007-08-20 | 2008-08-13 | 乾式低窒素酸化物(NOx)燃焼器用の漏れ低減ベンチュリ |
DE102008044432A DE102008044432A1 (de) | 2007-08-20 | 2008-08-14 | Leckagen reduzierende Venturidüse für trocken betriebene stickstoffarme Brennkammern |
CH01305/08A CH697802A2 (de) | 2007-08-20 | 2008-08-18 | Leckagen reduzierendes Venturi-Rohr für trockene Stickoxid-(NOx)-Niedrigemissions-Brenner. |
CNA200810211066XA CN101373069A (zh) | 2007-08-20 | 2008-08-20 | 用于干式低氮氧化物(NOx)燃烧器的减漏文丘里管 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/841,053 US20090053054A1 (en) | 2007-08-20 | 2007-08-20 | LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090053054A1 true US20090053054A1 (en) | 2009-02-26 |
Family
ID=40280466
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/841,053 Abandoned US20090053054A1 (en) | 2007-08-20 | 2007-08-20 | LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS |
Country Status (5)
Country | Link |
---|---|
US (1) | US20090053054A1 (de) |
JP (1) | JP2009047413A (de) |
CN (1) | CN101373069A (de) |
CH (1) | CH697802A2 (de) |
DE (1) | DE102008044432A1 (de) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110203287A1 (en) * | 2010-02-19 | 2011-08-25 | Ronald James Chila | Combustor liner for a turbine engine |
US20110214428A1 (en) * | 2010-03-02 | 2011-09-08 | General Electric Company | Hybrid venturi cooling system |
US20130000312A1 (en) * | 2011-06-30 | 2013-01-03 | General Electric Company | Turbomachine combustor assembly including a vortex modification system |
US20130091847A1 (en) * | 2011-10-13 | 2013-04-18 | General Electric Company | Combustor liner |
US20130180252A1 (en) * | 2012-01-18 | 2013-07-18 | General Electric Company | Combustor assembly with impingement sleeve holes and turbulators |
US10995956B2 (en) | 2016-03-29 | 2021-05-04 | Mitsubishi Power, Ltd. | Combustor and method for improving combustor performance |
US11747019B1 (en) | 2022-09-02 | 2023-09-05 | General Electric Company | Aerodynamic combustor liner design for emissions reductions |
US11788724B1 (en) | 2022-09-02 | 2023-10-17 | General Electric Company | Acoustic damper for combustor |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3326041A (en) * | 1965-04-14 | 1967-06-20 | Zink Co John | Apparatus for developing differential pressures in a conduit line |
US4413477A (en) * | 1980-12-29 | 1983-11-08 | General Electric Company | Liner assembly for gas turbine combustor |
US5319935A (en) * | 1990-10-23 | 1994-06-14 | Rolls-Royce Plc | Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection |
-
2007
- 2007-08-20 US US11/841,053 patent/US20090053054A1/en not_active Abandoned
-
2008
- 2008-08-13 JP JP2008208309A patent/JP2009047413A/ja not_active Withdrawn
- 2008-08-14 DE DE102008044432A patent/DE102008044432A1/de not_active Withdrawn
- 2008-08-18 CH CH01305/08A patent/CH697802A2/de not_active Application Discontinuation
- 2008-08-20 CN CNA200810211066XA patent/CN101373069A/zh active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3326041A (en) * | 1965-04-14 | 1967-06-20 | Zink Co John | Apparatus for developing differential pressures in a conduit line |
US4413477A (en) * | 1980-12-29 | 1983-11-08 | General Electric Company | Liner assembly for gas turbine combustor |
US5319935A (en) * | 1990-10-23 | 1994-06-14 | Rolls-Royce Plc | Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20110203287A1 (en) * | 2010-02-19 | 2011-08-25 | Ronald James Chila | Combustor liner for a turbine engine |
US8646277B2 (en) * | 2010-02-19 | 2014-02-11 | General Electric Company | Combustor liner for a turbine engine with venturi and air deflector |
US20110214428A1 (en) * | 2010-03-02 | 2011-09-08 | General Electric Company | Hybrid venturi cooling system |
US20130000312A1 (en) * | 2011-06-30 | 2013-01-03 | General Electric Company | Turbomachine combustor assembly including a vortex modification system |
US8904802B2 (en) * | 2011-06-30 | 2014-12-09 | General Electric Company | Turbomachine combustor assembly including a vortex modification system |
US20130091847A1 (en) * | 2011-10-13 | 2013-04-18 | General Electric Company | Combustor liner |
US20130180252A1 (en) * | 2012-01-18 | 2013-07-18 | General Electric Company | Combustor assembly with impingement sleeve holes and turbulators |
US10995956B2 (en) | 2016-03-29 | 2021-05-04 | Mitsubishi Power, Ltd. | Combustor and method for improving combustor performance |
US11747019B1 (en) | 2022-09-02 | 2023-09-05 | General Electric Company | Aerodynamic combustor liner design for emissions reductions |
US11788724B1 (en) | 2022-09-02 | 2023-10-17 | General Electric Company | Acoustic damper for combustor |
Also Published As
Publication number | Publication date |
---|---|
JP2009047413A (ja) | 2009-03-05 |
CH697802A2 (de) | 2009-02-27 |
DE102008044432A1 (de) | 2009-02-26 |
CN101373069A (zh) | 2009-02-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20090053054A1 (en) | LEAKAGE REDUCING VENTURI FOR DRY LOW NITRIC OXIDES (NOx) COMBUSTORS | |
JP7098283B2 (ja) | パイロット予混合ノズルおよび燃料ノズル組立体 | |
JP5199172B2 (ja) | 燃焼器ノズル | |
US20090019854A1 (en) | APPARATUS/METHOD FOR COOLING COMBUSTION CHAMBER/VENTURI IN A LOW NOx COMBUSTOR | |
JP5468812B2 (ja) | 燃焼器組立体及び、ガスタービンエンジン用の燃料ノズル | |
CA2528808C (en) | Method and apparatus for decreasing combustor acoustics | |
US10690349B2 (en) | Premixing fuel injectors and methods of use in gas turbine combustor | |
US8667800B2 (en) | Flameless combustion systems for gas turbine engines | |
WO2018003488A1 (ja) | ガスタービン燃焼器 | |
JP2009133599A (ja) | 燃焼システム内における逆火/保炎を減少させるのを可能にする方法及びシステム | |
JP5399015B2 (ja) | ガスタービンエンジン用の燃料ノズル及びそれを製作する方法 | |
CA2667047A1 (en) | Gas turbine combustor | |
JP2011141113A (ja) | 内蔵通路を備えた燃料ノズル及びその作動方法 | |
US8596071B2 (en) | Method and apparatus for assembling a gas turbine engine | |
JP2006017381A (ja) | 同軸噴流方式燃焼器 | |
US20230304666A1 (en) | Dual fuel gas turbine engine pilot nozzles | |
JP5998041B2 (ja) | ターボ機械構成要素の流れスリーブ | |
US9500369B2 (en) | Fuel nozzle and method for operating a combustor | |
WO2020116113A1 (ja) | ガスタービンの燃焼器及びこれを備えたガスタービン | |
US9670846B2 (en) | Enhanced mixing tube elements | |
JP6134510B2 (ja) | ターボ機械の燃焼器 | |
JP2012149642A (ja) | 低ダイナミックスのためのガスタービン燃料システム | |
JP2014231977A (ja) | ガスタービンエンジン |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GROOMS, NEAL WILLIAM;LEBEGUE, JEFFREY SCOTT;SIMONS, DERRICK WALTER;REEL/FRAME:019715/0884;SIGNING DATES FROM 20070814 TO 20070815 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |