US20120183911A1 - Combustor and a method for repairing a combustor - Google Patents
Combustor and a method for repairing a combustor Download PDFInfo
- Publication number
- US20120183911A1 US20120183911A1 US13/008,051 US201113008051A US2012183911A1 US 20120183911 A1 US20120183911 A1 US 20120183911A1 US 201113008051 A US201113008051 A US 201113008051A US 2012183911 A1 US2012183911 A1 US 2012183911A1
- Authority
- US
- United States
- Prior art keywords
- end cover
- insert
- combustor
- ring
- seal
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- 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
- F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
-
- 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
- F23R2900/00012—Details of sealing 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00017—Assembling combustion chamber liners or subparts
-
- 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
- F23R2900/00019—Repairing or maintaining 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
- Y10T29/49348—Burner, torch or metallurgical lance making
Definitions
- the present invention generally involves a combustor and a method for repairing a combustor.
- various embodiments of the present invention provide a system or method for modifying or repairing an end cover in the combustor.
- Combustors are known in the art for igniting fuel with air to produce combustion gases having a high temperature and pressure.
- gas turbine systems, aircraft engines, and numerous other combustion-based systems may include one or more combustors that mix a working fluid, such as air, with fuel and ignite the mixture to produce high temperature and pressure combustion gases. The combustion gases may then be used to rotate a turbine, provide thrust, or perform various other forms of work.
- Each combustor generally includes an end cover and a liner that surround and define a combustion chamber, and the working fluid may flow along the outside of the liner to remove heat from the liner before flowing into the combustion chamber through one or more nozzles.
- the nozzles may be radially arranged in or connected to the end cover, and fuel may be supplied to the nozzles through the end cover for injection into the combustion chamber.
- passages through the end cover may connect to complementary passages in the nozzles to provide fluid communication through the end cover and nozzles to the combustion chamber.
- An insert between the end cover and each nozzle may enable a single end cover design to accommodate several different passages to supply air, fuel, and/or other fluids to the fuel nozzle.
- the insert may be attached to the end cover by bolts, brazing, or weld joints, and each nozzle may then be bolted or otherwise attached to the insert and/or the end cover to complete the fluid pathway through the end cover, insert, and each nozzle.
- One embodiment of the present invention is a combustor that includes an end cover with a borehole through the end cover.
- the combustor further includes an insert in the borehole in the end cover and at least one continuous passage through the end cover and the insert.
- a ring is fixedly connected to the end cover with a seal between the ring and the insert.
- Another embodiment of the present invention is a combustor that includes an end cover and a nozzle connected to the end cover.
- the combustor further includes an insert between the end cover and the nozzle and at least one continuous passage through the end cover and the insert.
- a ring is fixedly connected to the end cover with a seal between the ring and the insert.
- the present invention also includes a method for repairing a combustor.
- the method includes fixedly connecting a ring to an end cover and installing a replacement insert in the end cover.
- the method further includes installing a seal between the ring and the replacement insert.
- FIG. 1 is a simplified cross-section view of a combustor according to one embodiment of the present invention
- FIG. 2 is an enlarged cross-section view of a portion of the end cover shown in FIG. 1 ;
- FIG. 3 is an enlarged cross-section view of the end cover shown in FIG. 2 with the insert substantially removed;
- FIG. 4 is an enlarged cross-section view of the end cover shown in FIG. 3 with a replacement insert installed in the end cover according to one embodiment of the present invention
- FIG. 5 is an enlarged cross-section view of the seal shown in FIG. 4 according to one embodiment of the present invention.
- FIG. 6 is an enlarged cross-section view of the seal shown in FIG. 4 according to an alternate embodiment of the present invention.
- FIG. 1 shows a simplified cross-section view of a combustor 10 according to one embodiment of the present invention.
- a casing 12 may surround the combustor 10 to contain the air or working fluid flowing to the combustor 10 .
- the combustor 10 may include one or more nozzles 14 radially arranged in a top cap 16 .
- An end cover 18 and a liner 20 generally surround a combustion chamber 22 located downstream of the nozzles 14 .
- a flow sleeve 24 with flow holes 26 may surround the liner 20 to define an annular passage 28 between the flow sleeve 24 and the liner 20 .
- the air or working fluid may pass through the flow holes 26 in the flow sleeve 24 to flow along the outside of the liner 20 to provide film or convective cooling to the liner 20 .
- the air or working fluid then reverses direction to flow through the one or more nozzles 14 where it mixes with fuel before igniting in the combustion chamber 22 to produce combustion gases having a high temperature and pressure.
- FIG. 2 shows an enlarged cross-section view of a portion of the end cover 18 shown in FIG. 1 before the improvements included in various embodiments of the present invention.
- the end cover 18 may include one or more boreholes 30 and continuous passages 32 that extend through the end cover 18 .
- the boreholes 30 and continuous passages 32 provide fluid communication through the end cover 18 to allow a fuel, a diluent, an inert gas, or other fluid to flow through the end cover 18 to the nozzle 14 .
- the borehole 30 may be stepped in the axial direction, resulting in varying diameters of the borehole 30 through the end cover 18 that provide convenient seating surfaces between the end cover 18 and an insert 34 .
- the insert 34 may be installed in the borehole 30 and connected to the end cover 18 by bolts or one or more braze 36 or weld joints, and the nozzle 14 may be connected to the end cover 18 and/or insert 34 downstream of the insert 34 so that the insert 34 is between the end cover 18 and the nozzle 14 .
- fluids in the borehole 30 and/or passages 32 may flow through the insert 34 to the nozzle 14
- the braze 36 or weld joints between the insert 34 and the end cover 18 may provide a suitable boundary to prevent co-mingling or mixing of the fluids in the borehole 30 and/or passages 32 .
- the weakened or damaged braze 36 or weld joints may be difficult to inspect and detect, and once detected, the spatial or geometric limitations inside the borehole 30 may make conventional repairs difficult or impractical without replacing the entire end cover 18 .
- Various embodiments of the present invention provide a system and method for modifying a new or existing end cover 18 that replaces or repairs one or more existing braze 36 or weld joints with a ring 40 .
- the ring 40 typically has a lower stiffness than the original insert 34 , resulting in lower tensile stresses between the ring 40 and the end cover 18 .
- the ring 40 may be more accessible to subsequent inspection and repairs, if necessary.
- the end cover 18 may be modified or repaired to couple the end cover 18 to the nozzle 14 without requiring a redesigned or replacement end cover 18 , producing substantial savings in repair or replacement costs.
- FIG. 3 provides an enlarged cross-section of the end cover 18 shown in FIG. 2 with the original insert 34 removed.
- the original insert 34 and any weakened or damaged braze 36 or weld joints may be substantially removed from the borehole 30 , for example by grinding or machining, leaving in place one or more rings 40 from the original insert 34 and associated braze 36 or weld joints that are still functioning.
- the original insert 34 and all associated braze 36 or weld joints may be completely removed and replaced with one or more rings 40 fixedly connected to the end cover 18 .
- Each ring 40 whether a remnant from the original insert 34 or a new piece, may comprise a hoop that is brazed or welded to the end cover 18 as before.
- each ring 40 reduces the stiffness of each ring 40 , resulting in a corresponding reduction in the tensile stress between each ring 40 and the end cover 18 .
- each ring 40 provides a convenient surface to mate with a replacement insert 42 while still preserving the continuous passages 32 through the end cover 18 and replacement insert 42 .
- FIG. 4 provides an enlarged cross-section of the end cover 18 shown in FIG. 3 with the replacement insert 42 installed in the end cover 18 according to one embodiment of the present invention.
- the replacement insert 42 costing far less than a replacement end cover 18 , may be inserted into the borehole 30 .
- a seal 44 between each ring 40 and the replacement insert 42 provides a suitable boundary to prevent co-mingling or mixing of the fluids in the borehole 30 and/or passages 32 .
- the seal 44 may comprise an annular metal ring having a generally W-shaped or C-shaped cross-section that allows the seal 44 to readily flex in response to relative movement between the replacement insert 42 and the associated ring 40 .
- the nozzle 14 may again be connected to the end cover 18 and/or replacement insert 42 downstream of the replacement insert 42 so that the replacement insert 42 is between the end cover 18 and the nozzle 14 .
- fluids in the borehole 30 and/or passages 32 may flow through the replacement insert 42 to the nozzle 14 as before, and the combination of the rings 40 and seals 44 between the replacement insert 42 and the end cover 18 provide a suitable boundary to prevent co-mingling or mixing of the fluids in the borehole 30 and/or passages 32 .
- FIGS. 5 and 6 provide enlarged cross-sections of the seals 44 shown in FIG. 4 according to various embodiments of the present invention.
- the seals 44 prevent fluid flow across the seals 44 during expansion or contraction of the adjacent surfaces.
- FIG. 5 shows that the W-shaped seal 44 between the ring 40 and the replacement insert 42 allows the ring 40 and the replacement insert 42 to expand or contract during operation without allowing fluid flow across the seal 44 .
- FIG. 6 shows that the C-shaped seal 44 may replace an existing braze or weld joint between the end cover 18 and the replacement insert 42 .
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
- Gas Burners (AREA)
- Fuel-Injection Apparatus (AREA)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/008,051 US20120183911A1 (en) | 2011-01-18 | 2011-01-18 | Combustor and a method for repairing a combustor |
JP2012005733A JP2012149880A (ja) | 2011-01-18 | 2012-01-16 | 燃焼器及び燃焼器の補修方法 |
DE102012100369A DE102012100369A1 (de) | 2011-01-18 | 2012-01-17 | Brennkammer und Verfahren zur Reparatur einer Brennkammer |
FR1250468A FR2970558A1 (fr) | 2011-01-18 | 2012-01-17 | Dispositif de combustion et procede pour reparer un dispositif de combustion |
CN201210026988XA CN102620318A (zh) | 2011-01-18 | 2012-01-18 | 燃烧器及维修燃烧器的方法 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/008,051 US20120183911A1 (en) | 2011-01-18 | 2011-01-18 | Combustor and a method for repairing a combustor |
Publications (1)
Publication Number | Publication Date |
---|---|
US20120183911A1 true US20120183911A1 (en) | 2012-07-19 |
Family
ID=46397785
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/008,051 Abandoned US20120183911A1 (en) | 2011-01-18 | 2011-01-18 | Combustor and a method for repairing a combustor |
Country Status (5)
Country | Link |
---|---|
US (1) | US20120183911A1 (zh) |
JP (1) | JP2012149880A (zh) |
CN (1) | CN102620318A (zh) |
DE (1) | DE102012100369A1 (zh) |
FR (1) | FR2970558A1 (zh) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130186093A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Process of fabricating a fuel nozzle assembly, process of fabricating a fuel nozzle ring, and a fuel nozzle ring |
US20160369760A1 (en) * | 2015-06-22 | 2016-12-22 | Doosan Heavy Industries & Construction Co., Ltd. | Fuel supply nozzle unit having sealing structure |
US20180172276A1 (en) * | 2016-12-21 | 2018-06-21 | General Electric Company | Fuel Nozzle Assembly with Flange Orifice |
US10399187B2 (en) | 2017-02-08 | 2019-09-03 | General Electric Company | System and method to locate and repair insert holes on a gas turbine component |
CN115142906A (zh) * | 2022-09-02 | 2022-10-04 | 中国航发沈阳发动机研究所 | 燃烧室火焰筒内壁后端与涡轮导向器叶片根部连接结构 |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8647037B2 (en) * | 2012-05-01 | 2014-02-11 | General Electric Company | System and method for assembling an end cover of a combustor |
Citations (27)
Publication number | Priority date | Publication date | Assignee | Title |
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US3730538A (en) * | 1970-06-26 | 1973-05-01 | Leyland Gas Turbines Ltd | Rubbing seal for a rotary regenerative heat exchanger |
US4341512A (en) * | 1980-07-31 | 1982-07-27 | Hauck Manufacturing Company | Burner |
US4384846A (en) * | 1979-10-23 | 1983-05-24 | Krupp-Koppers Gmbh | Burner |
US4891935A (en) * | 1987-10-23 | 1990-01-09 | Westinghouse Electric Corp. | Fuel nozzle assembly for a gas turbine engine |
US4930703A (en) * | 1988-12-22 | 1990-06-05 | General Electric Company | Integral fuel nozzle cover for gas turbine combustor |
US4964568A (en) * | 1989-01-17 | 1990-10-23 | The Perkin-Elmer Corporation | Shrouded thermal spray gun and method |
US5211004A (en) * | 1992-05-27 | 1993-05-18 | General Electric Company | Apparatus for reducing fuel/air concentration oscillations in gas turbine combustors |
US5247790A (en) * | 1992-09-18 | 1993-09-28 | Westinghouse Electric Corp. | Gas turbine fuel nozzle with replaceable cap |
US5253810A (en) * | 1992-03-13 | 1993-10-19 | The United States Of America As Represented By The Secretary Of The Navy | High heat, high pressure, non-corrosive injector assembly |
US5337961A (en) * | 1992-12-07 | 1994-08-16 | General Electric Company | Ceramic tip and compliant attachment interface for a gas turbine fuel nozzle |
US5491970A (en) * | 1994-06-10 | 1996-02-20 | General Electric Co. | Method for staging fuel in a turbine between diffusion and premixed operations |
US5685139A (en) * | 1996-03-29 | 1997-11-11 | General Electric Company | Diffusion-premix nozzle for a gas turbine combustor and related method |
US6112971A (en) * | 1999-05-12 | 2000-09-05 | General Electric Co. | Multi-nozzle combustion end cover vacuum brazing process |
US6199367B1 (en) * | 1996-04-26 | 2001-03-13 | General Electric Company | Air modulated carburetor with axially moveable fuel injector tip and swirler assembly responsive to fuel pressure |
US6237921B1 (en) * | 1998-09-02 | 2001-05-29 | General Electric Company | Nested bridge seal |
US6314739B1 (en) * | 2000-01-13 | 2001-11-13 | General Electric Company | Brazeless combustor dome assembly |
US20020011064A1 (en) * | 2000-01-13 | 2002-01-31 | Crocker David S. | Fuel injector with bifurcated recirculation zone |
US20050006492A1 (en) * | 2003-06-10 | 2005-01-13 | Brooks Harry R. | Modular fuel injector with di-pole magnetic circuit |
US20050005610A1 (en) * | 2003-07-10 | 2005-01-13 | Belsom Keith Cletus | Turbine combustor endcover assembly |
US6883329B1 (en) * | 2003-01-24 | 2005-04-26 | Power Systems Mfg, Llc | Method of fuel nozzle sizing and sequencing for a gas turbine combustor |
US20070151255A1 (en) * | 2006-01-04 | 2007-07-05 | General Electric Company | Combustion turbine engine and methods of assembly |
US7575416B2 (en) * | 2006-05-18 | 2009-08-18 | United Technologies Corporation | Rotor assembly for a rotary machine |
US20100066035A1 (en) * | 2008-09-16 | 2010-03-18 | General Electric Company | Reusable weld joint for syngas fuel nozzles |
US20100078408A1 (en) * | 2008-09-30 | 2010-04-01 | Hypertherm, Inc. | Nozzle with exposed vent passage |
US20110048020A1 (en) * | 2008-12-31 | 2011-03-03 | Mark Anthony Mueller | Acoustic damper |
US7941923B2 (en) * | 2005-12-08 | 2011-05-17 | General Electric Company | Drilled and integrated secondary fuel nozzle and manufacturing method |
US8104291B2 (en) * | 2008-03-27 | 2012-01-31 | General Electric Company | Combustion cap floating collar using E-seal |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US7596949B2 (en) * | 2006-02-23 | 2009-10-06 | General Electric Company | Method and apparatus for heat shielding gas turbine engines |
US20090320483A1 (en) * | 2008-06-26 | 2009-12-31 | General Electric Company | Variable Orifice Plug for Turbine Fuel Nozzle |
JP2010138778A (ja) * | 2008-12-11 | 2010-06-24 | Mitsubishi Heavy Ind Ltd | 燃料噴射弁の冷却構造 |
-
2011
- 2011-01-18 US US13/008,051 patent/US20120183911A1/en not_active Abandoned
-
2012
- 2012-01-16 JP JP2012005733A patent/JP2012149880A/ja active Pending
- 2012-01-17 DE DE102012100369A patent/DE102012100369A1/de not_active Withdrawn
- 2012-01-17 FR FR1250468A patent/FR2970558A1/fr not_active Withdrawn
- 2012-01-18 CN CN201210026988XA patent/CN102620318A/zh active Pending
Patent Citations (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3730538A (en) * | 1970-06-26 | 1973-05-01 | Leyland Gas Turbines Ltd | Rubbing seal for a rotary regenerative heat exchanger |
US4384846A (en) * | 1979-10-23 | 1983-05-24 | Krupp-Koppers Gmbh | Burner |
US4341512A (en) * | 1980-07-31 | 1982-07-27 | Hauck Manufacturing Company | Burner |
US4891935A (en) * | 1987-10-23 | 1990-01-09 | Westinghouse Electric Corp. | Fuel nozzle assembly for a gas turbine engine |
US4930703A (en) * | 1988-12-22 | 1990-06-05 | General Electric Company | Integral fuel nozzle cover for gas turbine combustor |
US4964568A (en) * | 1989-01-17 | 1990-10-23 | The Perkin-Elmer Corporation | Shrouded thermal spray gun and method |
US5253810A (en) * | 1992-03-13 | 1993-10-19 | The United States Of America As Represented By The Secretary Of The Navy | High heat, high pressure, non-corrosive injector assembly |
US5211004A (en) * | 1992-05-27 | 1993-05-18 | General Electric Company | Apparatus for reducing fuel/air concentration oscillations in gas turbine combustors |
US5247790A (en) * | 1992-09-18 | 1993-09-28 | Westinghouse Electric Corp. | Gas turbine fuel nozzle with replaceable cap |
US5337961A (en) * | 1992-12-07 | 1994-08-16 | General Electric Company | Ceramic tip and compliant attachment interface for a gas turbine fuel nozzle |
US5491970A (en) * | 1994-06-10 | 1996-02-20 | General Electric Co. | Method for staging fuel in a turbine between diffusion and premixed operations |
US5685139A (en) * | 1996-03-29 | 1997-11-11 | General Electric Company | Diffusion-premix nozzle for a gas turbine combustor and related method |
US6199367B1 (en) * | 1996-04-26 | 2001-03-13 | General Electric Company | Air modulated carburetor with axially moveable fuel injector tip and swirler assembly responsive to fuel pressure |
US6237921B1 (en) * | 1998-09-02 | 2001-05-29 | General Electric Company | Nested bridge seal |
US6112971A (en) * | 1999-05-12 | 2000-09-05 | General Electric Co. | Multi-nozzle combustion end cover vacuum brazing process |
US6314739B1 (en) * | 2000-01-13 | 2001-11-13 | General Electric Company | Brazeless combustor dome assembly |
US20020011064A1 (en) * | 2000-01-13 | 2002-01-31 | Crocker David S. | Fuel injector with bifurcated recirculation zone |
US6883329B1 (en) * | 2003-01-24 | 2005-04-26 | Power Systems Mfg, Llc | Method of fuel nozzle sizing and sequencing for a gas turbine combustor |
US20050006492A1 (en) * | 2003-06-10 | 2005-01-13 | Brooks Harry R. | Modular fuel injector with di-pole magnetic circuit |
US20050005610A1 (en) * | 2003-07-10 | 2005-01-13 | Belsom Keith Cletus | Turbine combustor endcover assembly |
US7941923B2 (en) * | 2005-12-08 | 2011-05-17 | General Electric Company | Drilled and integrated secondary fuel nozzle and manufacturing method |
US20070151255A1 (en) * | 2006-01-04 | 2007-07-05 | General Electric Company | Combustion turbine engine and methods of assembly |
US8122721B2 (en) * | 2006-01-04 | 2012-02-28 | General Electric Company | Combustion turbine engine and methods of assembly |
US7575416B2 (en) * | 2006-05-18 | 2009-08-18 | United Technologies Corporation | Rotor assembly for a rotary machine |
US8104291B2 (en) * | 2008-03-27 | 2012-01-31 | General Electric Company | Combustion cap floating collar using E-seal |
US20100066035A1 (en) * | 2008-09-16 | 2010-03-18 | General Electric Company | Reusable weld joint for syngas fuel nozzles |
US20100078408A1 (en) * | 2008-09-30 | 2010-04-01 | Hypertherm, Inc. | Nozzle with exposed vent passage |
US20110048020A1 (en) * | 2008-12-31 | 2011-03-03 | Mark Anthony Mueller | Acoustic damper |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130186093A1 (en) * | 2012-01-20 | 2013-07-25 | General Electric Company | Process of fabricating a fuel nozzle assembly, process of fabricating a fuel nozzle ring, and a fuel nozzle ring |
US9404655B2 (en) * | 2012-01-20 | 2016-08-02 | General Electric Company | Process of fabricating a fuel nozzle assembly |
US20160369760A1 (en) * | 2015-06-22 | 2016-12-22 | Doosan Heavy Industries & Construction Co., Ltd. | Fuel supply nozzle unit having sealing structure |
EP3109554A1 (en) * | 2015-06-22 | 2016-12-28 | Doosan Heavy Industries & Construction Co. Ltd. | Fuel supply nozzle unit having sealing structure |
US10605215B2 (en) * | 2015-06-22 | 2020-03-31 | DOOSAN Heavy Industries Construction Co., LTD | Fuel supply nozzle unit having sealing structure |
US11549475B2 (en) | 2015-06-22 | 2023-01-10 | Doosan Enerbility Co., Ltd. | Fuel supply nozzle unit having sealing structure |
US20180172276A1 (en) * | 2016-12-21 | 2018-06-21 | General Electric Company | Fuel Nozzle Assembly with Flange Orifice |
US10788215B2 (en) * | 2016-12-21 | 2020-09-29 | General Electric Company | Fuel nozzle assembly with flange orifice |
US10399187B2 (en) | 2017-02-08 | 2019-09-03 | General Electric Company | System and method to locate and repair insert holes on a gas turbine component |
CN115142906A (zh) * | 2022-09-02 | 2022-10-04 | 中国航发沈阳发动机研究所 | 燃烧室火焰筒内壁后端与涡轮导向器叶片根部连接结构 |
Also Published As
Publication number | Publication date |
---|---|
FR2970558A1 (fr) | 2012-07-20 |
JP2012149880A (ja) | 2012-08-09 |
DE102012100369A1 (de) | 2012-07-19 |
CN102620318A (zh) | 2012-08-01 |
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