US20060230763A1 - Combustor and cap assemblies for combustors in a gas turbine - Google Patents
Combustor and cap assemblies for combustors in a gas turbine Download PDFInfo
- Publication number
- US20060230763A1 US20060230763A1 US11/104,549 US10454905A US2006230763A1 US 20060230763 A1 US20060230763 A1 US 20060230763A1 US 10454905 A US10454905 A US 10454905A US 2006230763 A1 US2006230763 A1 US 2006230763A1
- Authority
- US
- United States
- Prior art keywords
- cap assembly
- spring fingers
- ring
- combustor
- 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
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
-
- 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
- F23R3/10—Air inlet arrangements for primary air
-
- 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
Definitions
- the present invention relates to combustors and cap assemblies for combustors having increased service life and particularly relates to combustors and cap assemblies therefor for converting combustors and cap assemblies having a predetermined life cycle to combustors and cap assemblies having extended life cycles.
- a plurality of combustors are typically arranged in an annular array about the axis of the turbine.
- eighteen combustors are circumferentially spaced about the turbine axis.
- Each combustor combines fuel and compressor discharge air into an fuel/air mixture which is then combusted with the resulting gases expanded through the blades of the turbine whereby work is extracted from the turbine.
- Combustors including cap assemblies are typically rated for a predetermined number of hours of operation before requiring service. For example, a cap assembly may be rated for 8,000 hours of operation before requiring servicing New versions of the cap assembly, however, are capable of extended hours of operation, e.g. 24,000 hours. This has led to an excess supply of cap assembly hardware having the lower rated hours of operation. These excess cap assemblies thus constitutes stranded assets since the lower rated cap assemblies would not be utilized in upgraded or providing new cap assemblies in new turbines. Accordingly, there has been a need to convert the lower rated cap assemblies which are otherwise stranded assets to the higher rated cap assemblies with extended hours of service whereby the lower rated cap assemblies can be utilized for turbine upgrades or provided in new turbines.
- a cap assembly for a turbine combustor comprising: a plurality of burner tubes; a fuel nozzle in each burner tube; and seals between the burner tubes and the fuel nozzles, each seal including a ring having a high velocity oxygen fuel coating on a surface thereof.
- a combustor comprising: a combustor liner; a cap assembly in part received within an end of the liner; a seal between the cap assembly part and said liner including pair of generally annular rings with each said ring having a plurality of spring fingers at circumferentially spaced locations thereabout, said rings being concentrically disposed relative to one another with the spring fingers of one ring circumferentially offset from the spring fingers of another ring enabling the spring fingers of each ring to register with gaps between the spring fingers of said another ring.
- a cap assembly for a turbine combustor comprising: a plurality of burner tubes; a fuel nozzle in each burner tube; an outer body sleeve surrounding said plurality of burner tubes and having a plurality of openings sized and located to protect against onset of a mode of combustion dynamics.
- FIG. 1 is a cross-sectional view of a combustor containing a cap assembly upgraded in accordance with a preferred embodiment of the present invention
- FIG. 2 is an enlarged end elevational view of the cap assembly for the combustor of FIG. 1 ;
- FIG. 3 is a cross-sectional view through an axis of the cap assembly
- FIG. 4 is a fragmentary enlarged view of a seal between the burner tubes and fuel nozzles within the cap assembly
- FIG. 5 is an elevational view of a seal between the cap assembly and combustor liner in accordance with the prior art
- FIG. 6 is a similar view of a seal between the cap assembly and liner in accordance with a preferred embodiment of the present invention.
- FIG. 7 is a cross-sectional view of the seal of FIG. 6 taken about on line 7 - 7 in FIG. 6 ;
- FIG. 8 is a fragmentary enlarged end view in an axial direction of the seal of FIG. 6 ;
- FIG. 9 is an enlarged fragmentary cross-sectional view of a flange of the cap assembly fitting into the forward casing of the combustor;
- FIG. 10 is an axial view of the outer casing of the cap assembly.
- FIG. 11 is a side elevational view thereof.
- Combustor 10 for a gas turbine.
- Combustor 10 includes a cap assembly generally designated 12 at a forward end of the combustor.
- combustor 10 includes a flow sleeve 14 , a combustor liner 16 and a transition piece 18 .
- the cap assembly 12 includes a plurality of burner tubes 20 which form an annular array of tubes about the axis of the combustor and about a central fuel nozzle 22 .
- Each burner tube 20 also houses a fuel nozzle 24 illustrated in FIG. 1 .
- compressor discharge air is supplied to the burner tubes and fuel nozzle for mixing with fuel to enable combustion, the combustion gases flowing through the transition piece 18 into the turbine to extract work from the gases.
- the burner tubes 20 typically have piston seals 28 for sealing about the burner tubes and to the fuel nozzle which is received within the burner tubes.
- Prior burner tube piston seals constituted a limiting factor in the service life of the cap assembly of the combustor.
- a high velocity oxygen fuel coating 30 is provided on each piston seal 28 to extend the service life of the piston seal.
- the material of the seal per se is conventional and may comprise HAST-X and the coating is identified FSX-414. The coating may be applied to a thickness of approximately 7-9 mils whereby superior wear properties are provided to the piston seal 28 .
- an outer cap body assembly seal for sealing the cap assembly to the liner in a manner which will extend the life of the outer cap body assembly seal.
- prior seals typically included a single annular seal, generally designated 32 , having a plurality of segments 34 extending from a seal base 36 secured to the outer housing of the cap assembly. The segments 34 are thus cantilevered from the base 36 with gaps 38 therebetween. Service life for this seal constituted a limiting factor for the overall service life of the cap assembly.
- an outer cap body assembly seal in the form of a pair of concentric rings is provided. Particularly, and referring to FIGS.
- the seal assembly generally designated 39 , includes a pair of concentric outer and inner rings 40 and 42 respectively.
- Each ring included a base 44 and 46 respectively secured to one another and to the outer casing of the cap assembly.
- Each ring includes a plurality of fingers 48 , 50 respectively with gaps 52 and 54 respectively between the fingers.
- the concentrically arranged rings 40 and 42 are circumferentially offset relative to one another.
- the spring fingers of one ring circumferentially offset from the spring fingers of the other seal ring enable the spring fingers of each ring to register with the gaps between the spring fingers of the other seal ring.
- the offset double seal ring as illustrated in FIG. 3 , is secured to the outer casing 60 ( FIG.
- the seal rings are convex and cantilevered in a forward direction and are biased against the interior surface of the liner 16 ( FIG. 1 ) to provide a seal between the liner and the outer cap body assembly.
- the service life of the seal between the outer cap body assembly and the liner has been extended correspondingly to the uprated service life of new cap assemblies.
- a flange is provided on the cap assembly and the flange has a chamfer.
- FIGS. 10 and 11 there is illustrated an outer casing 60 for the cap assembly.
- the outer casing has limited service life due to its response to certain combustion dynamics within the combustor. That is, vibratory action of the casing may occur at frequencies deleterious to extended service life. Therefore to extend the service life of the casing, a plurality of holes or openings 62 are provided at predetermined locations about the casing. For example, as illustrated in FIGS. 10 and 11 , the holes 62 are provided in pairs in quadrants of the casing. By providing these holes, the vibratory response of the casing to combustion dynamics is substantially minimized or eliminated thereby extending the service life of the casing.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The cap assembly of a turbine combustor includes a plurality of burner tubes sealed against fuel nozzles extending in the tubes. These piston seals are coated with a high velocity oxygen fuel coating to extend their service life. The outer cap body assembly includes concentric seal rings each with cantilevered convex fingers circumferentially offset from one another to seal between the cap assembly casing and the inner liner. The cap assembly casing is provided with a plurality of holes at predetermined locations about the casing to minimize or eliminate response to combustion dynamics.
Description
- The present invention relates to combustors and cap assemblies for combustors having increased service life and particularly relates to combustors and cap assemblies therefor for converting combustors and cap assemblies having a predetermined life cycle to combustors and cap assemblies having extended life cycles.
- In gas turbines, a plurality of combustors are typically arranged in an annular array about the axis of the turbine. For example, in one known turbine, eighteen combustors are circumferentially spaced about the turbine axis. Each combustor combines fuel and compressor discharge air into an fuel/air mixture which is then combusted with the resulting gases expanded through the blades of the turbine whereby work is extracted from the turbine.
- Combustors including cap assemblies are typically rated for a predetermined number of hours of operation before requiring service. For example, a cap assembly may be rated for 8,000 hours of operation before requiring servicing New versions of the cap assembly, however, are capable of extended hours of operation, e.g. 24,000 hours. This has led to an excess supply of cap assembly hardware having the lower rated hours of operation. These excess cap assemblies thus constitutes stranded assets since the lower rated cap assemblies would not be utilized in upgraded or providing new cap assemblies in new turbines. Accordingly, there has been a need to convert the lower rated cap assemblies which are otherwise stranded assets to the higher rated cap assemblies with extended hours of service whereby the lower rated cap assemblies can be utilized for turbine upgrades or provided in new turbines.
- In a preferred embodiment of the present invention there is provided a cap assembly for a turbine combustor comprising: a plurality of burner tubes; a fuel nozzle in each burner tube; and seals between the burner tubes and the fuel nozzles, each seal including a ring having a high velocity oxygen fuel coating on a surface thereof.
- In a further preferred embodiment of the present invention there is provided a combustor comprising: a combustor liner; a cap assembly in part received within an end of the liner; a seal between the cap assembly part and said liner including pair of generally annular rings with each said ring having a plurality of spring fingers at circumferentially spaced locations thereabout, said rings being concentrically disposed relative to one another with the spring fingers of one ring circumferentially offset from the spring fingers of another ring enabling the spring fingers of each ring to register with gaps between the spring fingers of said another ring.
- In another preferred embodiment of the present invention there is provided a cap assembly for a turbine combustor comprising: a plurality of burner tubes; a fuel nozzle in each burner tube; an outer body sleeve surrounding said plurality of burner tubes and having a plurality of openings sized and located to protect against onset of a mode of combustion dynamics.
-
FIG. 1 is a cross-sectional view of a combustor containing a cap assembly upgraded in accordance with a preferred embodiment of the present invention; -
FIG. 2 is an enlarged end elevational view of the cap assembly for the combustor ofFIG. 1 ; -
FIG. 3 is a cross-sectional view through an axis of the cap assembly; -
FIG. 4 is a fragmentary enlarged view of a seal between the burner tubes and fuel nozzles within the cap assembly; -
FIG. 5 is an elevational view of a seal between the cap assembly and combustor liner in accordance with the prior art; -
FIG. 6 is a similar view of a seal between the cap assembly and liner in accordance with a preferred embodiment of the present invention; -
FIG. 7 is a cross-sectional view of the seal ofFIG. 6 taken about on line 7-7 inFIG. 6 ; -
FIG. 8 is a fragmentary enlarged end view in an axial direction of the seal ofFIG. 6 ; -
FIG. 9 is an enlarged fragmentary cross-sectional view of a flange of the cap assembly fitting into the forward casing of the combustor; -
FIG. 10 is an axial view of the outer casing of the cap assembly; and -
FIG. 11 is a side elevational view thereof. - Referring now to the drawings, particularly to
FIG. 1 , there is illustrated a combustor generally designated 10 for a gas turbine.Combustor 10 includes a cap assembly generally designated 12 at a forward end of the combustor. As is conventional,combustor 10 includes aflow sleeve 14, acombustor liner 16 and atransition piece 18. Additionally, thecap assembly 12 includes a plurality ofburner tubes 20 which form an annular array of tubes about the axis of the combustor and about acentral fuel nozzle 22. Eachburner tube 20 also houses afuel nozzle 24 illustrated inFIG. 1 . Typically, compressor discharge air is supplied to the burner tubes and fuel nozzle for mixing with fuel to enable combustion, the combustion gases flowing through thetransition piece 18 into the turbine to extract work from the gases. - The
burner tubes 20 typically havepiston seals 28 for sealing about the burner tubes and to the fuel nozzle which is received within the burner tubes. Prior burner tube piston seals constituted a limiting factor in the service life of the cap assembly of the combustor. In accordance with a preferred embodiment of the present invention, to extend the service life of the cap assembly in this aspect of the invention, a high velocityoxygen fuel coating 30 is provided on eachpiston seal 28 to extend the service life of the piston seal. The material of the seal per se is conventional and may comprise HAST-X and the coating is identified FSX-414. The coating may be applied to a thickness of approximately 7-9 mils whereby superior wear properties are provided to thepiston seal 28. - Referring now to
FIGS. 3 and 5 -8, there is provided an outer cap body assembly seal for sealing the cap assembly to the liner in a manner which will extend the life of the outer cap body assembly seal. Referring toFIG. 5 , prior seals typically included a single annular seal, generally designated 32, having a plurality ofsegments 34 extending from aseal base 36 secured to the outer housing of the cap assembly. Thesegments 34 are thus cantilevered from thebase 36 withgaps 38 therebetween. Service life for this seal constituted a limiting factor for the overall service life of the cap assembly. To extend the service life of the cap assembly, an outer cap body assembly seal in the form of a pair of concentric rings is provided. Particularly, and referring toFIGS. 6-8 , the seal assembly, generally designated 39, includes a pair of concentric outer andinner rings base rings FIG. 3 , is secured to the outer casing 60 (FIG. 1 ) of the outer cap body assembly and extends in a forward direction from its securement to the outer cap body casing. Thus, the seal rings are convex and cantilevered in a forward direction and are biased against the interior surface of the liner 16 (FIG. 1 ) to provide a seal between the liner and the outer cap body assembly. As a consequence, the service life of the seal between the outer cap body assembly and the liner has been extended correspondingly to the uprated service life of new cap assemblies. - Referring to
FIG. 9 , a flange is provided on the cap assembly and the flange has a chamfer. - Referring now to
FIGS. 10 and 11 , there is illustrated anouter casing 60 for the cap assembly. It has been found that in certain turbines, the outer casing has limited service life due to its response to certain combustion dynamics within the combustor. That is, vibratory action of the casing may occur at frequencies deleterious to extended service life. Therefore to extend the service life of the casing, a plurality of holes oropenings 62 are provided at predetermined locations about the casing. For example, as illustrated inFIGS. 10 and 11 , theholes 62 are provided in pairs in quadrants of the casing. By providing these holes, the vibratory response of the casing to combustion dynamics is substantially minimized or eliminated thereby extending the service life of the casing. - While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (8)
1. A cap assembly for a turbine combustor comprising:
a plurality of burner tubes;
a fuel nozzle in each burner tube; and
seals between the burner tubes and the fuel nozzles, each seal including a ring having a high velocity oxygen fuel coating on a surface thereof.
2. A cap assembly according to claim 1 wherein said seal is formed of HAST-X.
3. A combustor comprising:
a combustor liner;
a cap assembly in part received within an end of the liner; and
a seal between the cap assembly and said liner including pair of generally annular rings, each said ring having a plurality of spring fingers at circumferentially spaced locations thereabout, said rings being concentrically disposed relative to one another with the spring fingers of one ring circumferentially offset from the spring fingers of another ring enabling the spring fingers of each ring to register with gaps between the spring fingers of said another ring.
4. A combustor according to claim 3 wherein each ring has a margin along an edge thereof with the spring fingers cantilevered from said edge.
5. A combustor according to claim 4 wherein the spring fingers are arcuate with each spring finger following the arcuate contour of registering portions of a pair of spring fingers of said another ring.
6. A combustor according to claim 5 wherein the spring fingers are secured to a casing of the cap assembly, said spring fingers of an outermost ring having radially outward cantilevered convex portions for sealing about an inner surface of the liner.
7. A combustor according to claim 6 wherein said radially outward convex portions have a high velocity oxygen fuel coating.
8. A cap assembly for a turbine combustor comprising:
a plurality of burner tubes;
a fuel nozzle in each burner tube;
an outer body sleeve surrounding said plurality of burner tubes and having a plurality of openings sized and located to protect against onset of a mode of combustion dynamics.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US11/104,549 US20060230763A1 (en) | 2005-04-13 | 2005-04-13 | Combustor and cap assemblies for combustors in a gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US11/104,549 US20060230763A1 (en) | 2005-04-13 | 2005-04-13 | Combustor and cap assemblies for combustors in a gas turbine |
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US20060230763A1 true US20060230763A1 (en) | 2006-10-19 |
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US11/104,549 Abandoned US20060230763A1 (en) | 2005-04-13 | 2005-04-13 | Combustor and cap assemblies for combustors in a gas turbine |
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Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090293489A1 (en) * | 2008-06-03 | 2009-12-03 | Tuthill Richard S | Combustor liner cap assembly |
US20100005804A1 (en) * | 2008-07-11 | 2010-01-14 | General Electric Company | Combustor structure |
US20100050640A1 (en) * | 2008-08-29 | 2010-03-04 | General Electric Company | Thermally compliant combustion cap device and system |
US20100263384A1 (en) * | 2009-04-17 | 2010-10-21 | Ronald James Chila | Combustor cap with shaped effusion cooling holes |
US20120291440A1 (en) * | 2011-05-20 | 2012-11-22 | Frank Moehrle | Gas turbine combustion cap assembly |
US20120304657A1 (en) * | 2011-06-06 | 2012-12-06 | General Electric Company | Lock leaf hula seal |
US20130081397A1 (en) * | 2011-10-04 | 2013-04-04 | Brandon Taylor Overby | Forward casing with a circumferential sloped surface and a combustor assembly including same |
US20140033717A1 (en) * | 2012-08-03 | 2014-02-06 | General Electric Company | Combustor cap assembly |
EP2239507A3 (en) * | 2009-03-30 | 2014-08-13 | General Electric Company | Fuel nozzle spring support |
US20140260319A1 (en) * | 2013-03-18 | 2014-09-18 | General Electric Company | Combustor support assembly for mounting a combustion module of a gas turbine |
US9803868B2 (en) | 2011-05-20 | 2017-10-31 | Siemens Energy, Inc. | Thermally compliant support for a combustion system |
US11255432B2 (en) | 2019-04-05 | 2022-02-22 | Raytheon Technologies Corporation | Low friction, wear resistant piston seal |
US20220341373A1 (en) * | 2019-09-05 | 2022-10-27 | Safran Ceramics | Ejection cone having a flexible aerodynamic attachment |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5274991A (en) * | 1992-03-30 | 1994-01-04 | General Electric Company | Dry low NOx multi-nozzle combustion liner cap assembly |
US5987879A (en) * | 1996-01-17 | 1999-11-23 | Mitsubishi Jukogyo Kabushiki Kaisha | Spring seal device for combustor |
US6438959B1 (en) * | 2000-12-28 | 2002-08-27 | General Electric Company | Combustion cap with integral air diffuser and related method |
US20040251639A1 (en) * | 2003-06-12 | 2004-12-16 | Siemens Westinghouse Power Corporation | Turbine spring clip seal |
US20050062237A1 (en) * | 2002-09-26 | 2005-03-24 | Siemens Westinghouse Power Corporation | Turbine spring clip seal |
US7007482B2 (en) * | 2004-05-28 | 2006-03-07 | Power Systems Mfg., Llc | Combustion liner seal with heat transfer augmentation |
US7126329B2 (en) * | 2004-01-21 | 2006-10-24 | General Electric Company | Methods for preparing and testing a thermal-spray coated substrate |
US7269957B2 (en) * | 2004-05-28 | 2007-09-18 | Martling Vincent C | Combustion liner having improved cooling and sealing |
-
2005
- 2005-04-13 US US11/104,549 patent/US20060230763A1/en not_active Abandoned
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5274991A (en) * | 1992-03-30 | 1994-01-04 | General Electric Company | Dry low NOx multi-nozzle combustion liner cap assembly |
US5987879A (en) * | 1996-01-17 | 1999-11-23 | Mitsubishi Jukogyo Kabushiki Kaisha | Spring seal device for combustor |
US6438959B1 (en) * | 2000-12-28 | 2002-08-27 | General Electric Company | Combustion cap with integral air diffuser and related method |
US20050062237A1 (en) * | 2002-09-26 | 2005-03-24 | Siemens Westinghouse Power Corporation | Turbine spring clip seal |
US20040251639A1 (en) * | 2003-06-12 | 2004-12-16 | Siemens Westinghouse Power Corporation | Turbine spring clip seal |
US7126329B2 (en) * | 2004-01-21 | 2006-10-24 | General Electric Company | Methods for preparing and testing a thermal-spray coated substrate |
US7007482B2 (en) * | 2004-05-28 | 2006-03-07 | Power Systems Mfg., Llc | Combustion liner seal with heat transfer augmentation |
US7269957B2 (en) * | 2004-05-28 | 2007-09-18 | Martling Vincent C | Combustion liner having improved cooling and sealing |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2131110A3 (en) * | 2008-06-03 | 2013-02-27 | United Technologies Corporation | Combustor liner cap assembly |
US8091370B2 (en) | 2008-06-03 | 2012-01-10 | United Technologies Corporation | Combustor liner cap assembly |
US20090293489A1 (en) * | 2008-06-03 | 2009-12-03 | Tuthill Richard S | Combustor liner cap assembly |
US20100005804A1 (en) * | 2008-07-11 | 2010-01-14 | General Electric Company | Combustor structure |
US20100050640A1 (en) * | 2008-08-29 | 2010-03-04 | General Electric Company | Thermally compliant combustion cap device and system |
EP2239507A3 (en) * | 2009-03-30 | 2014-08-13 | General Electric Company | Fuel nozzle spring support |
US20100263384A1 (en) * | 2009-04-17 | 2010-10-21 | Ronald James Chila | Combustor cap with shaped effusion cooling holes |
US20120291440A1 (en) * | 2011-05-20 | 2012-11-22 | Frank Moehrle | Gas turbine combustion cap assembly |
US9388988B2 (en) * | 2011-05-20 | 2016-07-12 | Siemens Energy, Inc. | Gas turbine combustion cap assembly |
US9803868B2 (en) | 2011-05-20 | 2017-10-31 | Siemens Energy, Inc. | Thermally compliant support for a combustion system |
US20120304657A1 (en) * | 2011-06-06 | 2012-12-06 | General Electric Company | Lock leaf hula seal |
US20130081397A1 (en) * | 2011-10-04 | 2013-04-04 | Brandon Taylor Overby | Forward casing with a circumferential sloped surface and a combustor assembly including same |
US20140033717A1 (en) * | 2012-08-03 | 2014-02-06 | General Electric Company | Combustor cap assembly |
US9003803B2 (en) * | 2012-08-03 | 2015-04-14 | General Electric Company | Combustor cap assembly |
US20140260319A1 (en) * | 2013-03-18 | 2014-09-18 | General Electric Company | Combustor support assembly for mounting a combustion module of a gas turbine |
US9400114B2 (en) * | 2013-03-18 | 2016-07-26 | General Electric Company | Combustor support assembly for mounting a combustion module of a gas turbine |
US11255432B2 (en) | 2019-04-05 | 2022-02-22 | Raytheon Technologies Corporation | Low friction, wear resistant piston seal |
US11976732B2 (en) | 2019-04-05 | 2024-05-07 | Rtx Corporation | Low friction, wear resistant piston seal |
US20220341373A1 (en) * | 2019-09-05 | 2022-10-27 | Safran Ceramics | Ejection cone having a flexible aerodynamic attachment |
US11821387B2 (en) * | 2019-09-05 | 2023-11-21 | Safran Ceramics | Ejection cone having a flexible aerodynamic attachment |
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Legal Events
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AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:JOHNSON, JERE A.;BAILEY, MARK;BERRY, ROBERT R.;AND OTHERS;REEL/FRAME:016473/0312;SIGNING DATES FROM 20050311 TO 20050412 |
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STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |