EP2378201A2 - Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly - Google Patents
Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly Download PDFInfo
- Publication number
- EP2378201A2 EP2378201A2 EP11162106A EP11162106A EP2378201A2 EP 2378201 A2 EP2378201 A2 EP 2378201A2 EP 11162106 A EP11162106 A EP 11162106A EP 11162106 A EP11162106 A EP 11162106A EP 2378201 A2 EP2378201 A2 EP 2378201A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- liner
- combustion
- wall
- combustion liner
- liner assembly
- 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.)
- Withdrawn
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
-
- 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
- F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses
Definitions
- the present invention relates to apparatus and methods for minimizing or eliminating dilution air leakage paths in a gas turbine combustor and particularly relates to apparatus and methods for managing dilution air leakage to achieve lower emission levels.
- NO and NO 2 oxides of nitrogen
- CO carbon monoxide
- unburned hydrocarbons as well as other particulates.
- Various systems have been proposed and utilized for reducing emissions. For example, water or steam injection into the burning zone of the gas turbine combustor, catalytic clean-up of NO x and CO from the gas turbine exhaust and dry low NO x combustors have been used in the past. Compressor discharge dilution air introduced into the liner sleeve of the combustor and transition piece has also been utilized to reduce emissions.
- a combustion liner assembly for a gas turbine comprises an outer liner, the outer liner having a flange at a forward end; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; and a slip joint connected to the second inner wall, the slip joint receiving the flange of the outer liner.
- a combustion liner assembly for a gas turbine comprises an outer liner; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; an aft section connected to aft ends of the outer liner and the inner liner; and a slip joint provided between the aft section and the inner liner.
- a combustion liner assembly 2 comprises an outer liner 4 and an inner liner 6.
- a venturi 8 is provided at a forward end of the combustion liner assembly 2 and includes a venturi throat 10 which is provided between the inner liner 6 and an inner wall 12.
- a flange 14 may be integrally formed with the outer liner 4 and is received in a slip joint 16 that is connected to the inner wall 12 of the venturi 8.
- the inner liner 6 includes an inner wall 24 and turbulators 18 provided on an outer surface.
- An aft section, or gooseneck section, 20 is connected to the aft portion of the outer liner 4 and the inner liner 6.
- Radial drain or dump holes 22 are provided in the inner liner at an area adjacent to the aft section 20.
- the combustion liner assembly 2 may be welded to a liner sleeve at areas A and B corresponding to the slip joint 16 and the end of the aft section 20, respectively.
- the combustion liner assembly 2 may be circumferentially welded to the liner sleeve, rather than riveted as in prior art arrangements.
- the venturi 10 may be circumferentially welded to the inner wall 12 and the inner wall 24 of the inner liner 6.
- the thickness of the inner wall 24 and the thickness of the inner wall 24 of the inner liner 6 at the portion containing the circumferential weld may be thicker than prior art combustion liner assembly inner liners to increase the structural integrity of the venturi, as the venturi will be welded to the liner sleeve as opposed to riveted.
- the radial drain or dump holes 22 of the embodiment shown in Figs. 1 and 2 provides a radial discharge of cooling flow into the flame zone.
- the embodiments shown in Figs. 1 and 2 may also have an increased impingement cooling area combined with the turbulators 18.
- a small controlled leak may be provided into the cooling channel between the outer liner 4 and the inner liner 6 as an alternative to a bellows.
- the combustion liner assembly 2 includes the aft section, or gooseneck section 20 which comprises axial drain or dump holes 24, rather than radial drain or dump holes. It has been found that the use of radial drain or dump holes, as shown in the embodiment of Figs. 1 and 2 , may trigger high frequency combustion instability, or screech, during transfer to the premix combustion and at the turndown when the flame temperature is reduced. However, the axial drain or dump holes 24 do not trigger high frequency instability with the integral venturi of the embodiment shown in Fig. 3 .
- the venturi cooling is rerouted to have an axial discharge with the same effective area as the radial discharge of the venturi of the embodiment shown in Fig. 3 .
- a combustion liner assembly 2 comprises an outer liner 4 and an inner liner 6.
- the outer liner 4 includes a flange 14 that is received in a slip joint 16 that is connected to an inner wall 12 of a venturi 8 that comprises a venturi throat 10 that connects the inner wall 12 and a portion of the inner liners 6 having axial drain or dump holes 24.
- the combustion liner assembly 2 comprises radial drain or dump holes 22 formed in the inner liner 6.
- the dump holes 26 may be provided as holes on the face of the aft section 20, i.e. at the intersection of the cylindrical and conical portions of the aft section 20.
- a combustion liner assembly according to another embodiment comprises an outer liner 4 and an inner liner 6.
- a venturi 8 is provided at a forward section of the combustion liner assembly 2 and includes a venturi throat 10 and an inner wall 12.
- the venturi 8 also includes an inner wall 24 connected between the venturi throat 10 and the inner liner 6.
- An aft section 20 is connected to the outer liner 4 and the inner liner 6 by an aft slip joint 30.
- the combustion liner assembly 2 comprises radial drain or dump holes 22 provided in the inner liner 6.
- the aft end of the combustion liner assembly 2 comprises a bellows 28, as well as a slip joint 30 as disclosed in the previous embodiments.
- a combustion liner assembly 2 includes an outer liner 4 and an inner liner 6.
- a venturi 8 comprises a venturi throat 10 welded to an inner wall 12 and an inner wall 24 connected to the inner liner 6.
- a flange 14 of the outer liner 4 is received in a slip joint 16 at the forward end of the combustion liner assembly 2.
- An aft section 20 of the combustion liner 2 is connected to the outer liner 4 and the inner liner 6 by an aft slip joint 30.
- the slip joint 16 may be formed of, for example, an alloy of primarily nickel, such as Hastelloy®, and the flange 14 may be formed of, for example, stainless steel.
- the slip joint 16 may also be provided with a wear resistant coating.
- the slip joint 16 provides a double seal on both sides of the flange 14 and may be machined to tight tolerances. As the temperature of the combustion liner assembly 2 increases during operation of the gas turbine, the small leakage area between the flange 14 and the slip joint 16 decreases as the flange 14 expands into the slip joint 16.
- the combustion liner assemblies reduce, or eliminate, airflow losses in between the venturi wall and the liner wall so that airflow can be used and more evenly dispersed. Reduction, or elimination, of variance to air flow will allow more consistent air flow to be utilized in fuel air mixture in the head end combustion zone rather than leak air flow into direct "stream".
- the combustion liner assemblies are relatively easy to manufacture and produce a more repeatable air flow from can to can and in turn help to create better fuel air mixture pattern than current design and lower combustion emissions. These are improvements to variation and mixing fuel air better through the mixing holes than would happen through the current design.
- the combustion liner assemblies reduce, or eliminate, leaks so airflow in more noncritical areas is conserved and made more consistent, i.e. can to can variation is lowered.
- the combustion liner assemblies also increase airflow in useable areas in a more dispersed and even mixing through the mixing holes than would happen through current designs.
- the combustion liner assemblies can be replaced in the field easily.
- the existing liners can be pulled out and replaced with the combustion liner assemblies disclosed herein.
- the combustion liner assemblies may also use current production methods and machining to produce.
- the combustion liner assemblies do not change the fit, form or function of the overall liner assembly.
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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
Description
- The present invention relates to apparatus and methods for minimizing or eliminating dilution air leakage paths in a gas turbine combustor and particularly relates to apparatus and methods for managing dilution air leakage to achieve lower emission levels.
- Significant products of combustion in gas turbine emissions are oxides of nitrogen, i.e., NO and NO2 collectively called NOx, carbon monoxide CO, and unburned hydrocarbons as well as other particulates. Various systems have been proposed and utilized for reducing emissions. For example, water or steam injection into the burning zone of the gas turbine combustor, catalytic clean-up of NOx and CO from the gas turbine exhaust and dry low NOx combustors have been used in the past. Compressor discharge dilution air introduced into the liner sleeve of the combustor and transition piece has also been utilized to reduce emissions.
- According to an embodiment of the invention, a combustion liner assembly for a gas turbine comprises an outer liner, the outer liner having a flange at a forward end; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; and a slip joint connected to the second inner wall, the slip joint receiving the flange of the outer liner.
- According to another embodiment of the invention, a combustion liner assembly for a gas turbine comprises an outer liner; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; an aft section connected to aft ends of the outer liner and the inner liner; and a slip joint provided between the aft section and the inner liner.
-
-
Fig. 1 is a schematic illustration of a gas turbine combustion liner assembly according to an embodiment of the invention; -
Fig. 2 is a schematic illustration of a venturi throat of the combustion liner assembly ofFig. 1 ; -
Fig. 3 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention; -
Fig. 4 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention; -
Fig. 5 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention; -
Fig. 6 is a schematic illustration of an aft, or goose neck, section of the combustion liner assembly according to another embodiment of the invention; -
Fig. 7 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention; -
Fig. 8 is a schematic illustration of a combustion liner assembly according to another embodiment of the invention; and -
Fig. 9 is a schematic illustration of a flange of the outer liner and slip joint according to an embodiment of the invention. - Referring to
Fig. 1 , acombustion liner assembly 2 comprises anouter liner 4 and aninner liner 6. Aventuri 8 is provided at a forward end of thecombustion liner assembly 2 and includes aventuri throat 10 which is provided between theinner liner 6 and aninner wall 12. Aflange 14 may be integrally formed with theouter liner 4 and is received in aslip joint 16 that is connected to theinner wall 12 of theventuri 8. - The
inner liner 6 includes aninner wall 24 andturbulators 18 provided on an outer surface. An aft section, or gooseneck section, 20 is connected to the aft portion of theouter liner 4 and theinner liner 6. Radial drain ordump holes 22 are provided in the inner liner at an area adjacent to theaft section 20. - The
combustion liner assembly 2 may be welded to a liner sleeve at areas A and B corresponding to theslip joint 16 and the end of theaft section 20, respectively. Thecombustion liner assembly 2 may be circumferentially welded to the liner sleeve, rather than riveted as in prior art arrangements. - Referring to
Fig. 2 , theventuri 10 may be circumferentially welded to theinner wall 12 and theinner wall 24 of theinner liner 6. The thickness of theinner wall 24 and the thickness of theinner wall 24 of theinner liner 6 at the portion containing the circumferential weld may be thicker than prior art combustion liner assembly inner liners to increase the structural integrity of the venturi, as the venturi will be welded to the liner sleeve as opposed to riveted. - The radial drain or
dump holes 22 of the embodiment shown inFigs. 1 and 2 provides a radial discharge of cooling flow into the flame zone. The embodiments shown inFigs. 1 and 2 may also have an increased impingement cooling area combined with theturbulators 18. A small controlled leak may be provided into the cooling channel between theouter liner 4 and theinner liner 6 as an alternative to a bellows. - Referring to
Fig. 3 , according to another embodiment of the invention, thecombustion liner assembly 2 includes the aft section, orgooseneck section 20 which comprises axial drain ordump holes 24, rather than radial drain or dump holes. It has been found that the use of radial drain or dump holes, as shown in the embodiment ofFigs. 1 and 2 , may trigger high frequency combustion instability, or screech, during transfer to the premix combustion and at the turndown when the flame temperature is reduced. However, the axial drain ordump holes 24 do not trigger high frequency instability with the integral venturi of the embodiment shown inFig. 3 . - As shown in
Figs. 1 and 2 , the venturi cooling is rerouted to have an axial discharge with the same effective area as the radial discharge of the venturi of the embodiment shown inFig. 3 . - Referring to
Figs. 4 and5 , acombustion liner assembly 2 according to another embodiment comprises anouter liner 4 and aninner liner 6. Theouter liner 4 includes aflange 14 that is received in aslip joint 16 that is connected to aninner wall 12 of aventuri 8 that comprises aventuri throat 10 that connects theinner wall 12 and a portion of theinner liners 6 having axial drain ordump holes 24. At the aft section or,gooseneck section 20, thecombustion liner assembly 2 comprises radial drain ordump holes 22 formed in theinner liner 6. - Referring to
Fig. 6 , according to another embodiment, thedump holes 26 may be provided as holes on the face of theaft section 20, i.e. at the intersection of the cylindrical and conical portions of theaft section 20. - Referring to
Fig. 7 , a combustion liner assembly according to another embodiment comprises anouter liner 4 and aninner liner 6. Aventuri 8 is provided at a forward section of thecombustion liner assembly 2 and includes aventuri throat 10 and aninner wall 12. Theventuri 8 also includes aninner wall 24 connected between theventuri throat 10 and theinner liner 6. Anaft section 20 is connected to theouter liner 4 and theinner liner 6 by anaft slip joint 30. Thecombustion liner assembly 2 comprises radial drain ordump holes 22 provided in theinner liner 6. - The aft end of the
combustion liner assembly 2 comprises abellows 28, as well as aslip joint 30 as disclosed in the previous embodiments. - Referring to
Fig. 8 , according to another embodiment of the invention, acombustion liner assembly 2 includes anouter liner 4 and aninner liner 6. Aventuri 8 comprises aventuri throat 10 welded to aninner wall 12 and aninner wall 24 connected to theinner liner 6. Aflange 14 of theouter liner 4 is received in aslip joint 16 at the forward end of thecombustion liner assembly 2. Anaft section 20 of thecombustion liner 2 is connected to theouter liner 4 and theinner liner 6 by anaft slip joint 30. - Referring to
Fig. 9 theslip joint 16 may be formed of, for example, an alloy of primarily nickel, such as Hastelloy®, and theflange 14 may be formed of, for example, stainless steel. Theslip joint 16 may also be provided with a wear resistant coating. Theslip joint 16 provides a double seal on both sides of theflange 14 and may be machined to tight tolerances. As the temperature of thecombustion liner assembly 2 increases during operation of the gas turbine, the small leakage area between theflange 14 and theslip joint 16 decreases as theflange 14 expands into theslip joint 16. - The combustion liner assemblies reduce, or eliminate, airflow losses in between the venturi wall and the liner wall so that airflow can be used and more evenly dispersed. Reduction, or elimination, of variance to air flow will allow more consistent air flow to be utilized in fuel air mixture in the head end combustion zone rather than leak air flow into direct "stream". The combustion liner assemblies are relatively easy to manufacture and produce a more repeatable air flow from can to can and in turn help to create better fuel air mixture pattern than current design and lower combustion emissions. These are improvements to variation and mixing fuel air better through the mixing holes than would happen through the current design.
- The combustion liner assemblies reduce, or eliminate, leaks so airflow in more noncritical areas is conserved and made more consistent, i.e. can to can variation is lowered. The combustion liner assemblies also increase airflow in useable areas in a more dispersed and even mixing through the mixing holes than would happen through current designs.
- The combustion liner assemblies can be replaced in the field easily. The existing liners can be pulled out and replaced with the combustion liner assemblies disclosed herein. The combustion liner assemblies may also use current production methods and machining to produce. The combustion liner assemblies do not change the fit, form or function of the overall liner assembly.
- While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiments, it is to be understood that the invention is not to be limited to the disclosed embodiments, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
- For completeness, various aspects of the invention are now set out in the following numbered clauses:
- 1. A combustion liner assembly for a gas turbine, comprising:
- an outer liner, the outer liner having a flange at a forward end;
- an inner liner disposed within the outer liner, the inner liner having a first inner wall;
- a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; and
- a slip joint connected to the second inner wall, the slip joint receiving the flange of the outer liner.
- 2. A combustion liner assembly according to clause 1, further comprising an aft section provided at aft ends of the outer liner and the inner liner.
- 3. A combustion liner assembly according to clause 1, further comprising:
- a second slip joint connecting the aft section and the outer liner or the inner liner.
- 4. A combustion liner assembly according to clause 1, wherein the outer liner comprises a plurality of radial drain or dump holes.
- 5. A combustion liner assembly according to
clause 2, wherein the aft section comprises a plurality of radial drain or dump holes. - 6. A combustion liner assembly according to clause 5, wherein the aft section further comprises a plurality of axial drain or dump holes.
- 7. A combustion liner assembly according to
clause 2, wherein the aft section comprises a plurality of axial drain or dump holes. - 8. A combustion liner assembly according to
clause 2, wherein the aft section comprises a plurality of holes at an intersection of a cylindrical section of the aft section and a conical section of the aft section. - 9. A combustion liner assembly according to clause 1, wherein the slip joint is formed of a nickel alloy and the flange is formed of stainless steel.
- 10. A combustion liner assembly according to clause 1, wherein the slip joint comprises a wear coating.
- 11. A combustor for a gas turbine, comprising:
- a liner sleeve; and
- a combustion liner assembly according to claim 1, wherein the combustion liner assembly is welded to the liner sleeve at least at the slip joint.
- 12. A combustion liner assembly for a gas turbine, comprising:
- an outer liner;
- an inner liner disposed within the outer liner, the inner liner having a first inner wall;
- a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner;
- an aft section connected to aft ends of the outer liner and the inner liner; and
- a slip joint provided between the aft section and the inner liner.
- 13. A combustion liner assembly according to
clause 12, wherein the aft section further comprises a bellows. - 14. A combustion liner assembly according to
clause 12, wherein the outer liner comprises a plurality of radial drain or dump holes. - 15. A combustion liner assembly according to
clause 12, wherein the aft section comprises a plurality of radial drain or dump holes. - 16. A combustion liner assembly according to clause 15, wherein the aft section further comprises a plurality of axial drain or dump holes.
- 17. A combustion liner assembly according to
clause 12, wherein the aft section comprises a plurality of axial drain or dump holes. - 18. A combustion liner assembly according to
clause 12, wherein the aft section comprises a plurality of holes at an intersection of a cylindrical section of the aft section and a conical section of the aft section. - 19. A combustion liner assembly according to
clause 12, wherein the slip joint comprises a wear coating. - 20. A combustor for a gas turbine, comprising:
- a liner sleeve; and
- a combustion liner assembly according to
claim 12, wherein the combustion liner assembly is welded to the liner sleeve.
Claims (7)
- A combustion liner assembly (2) for a gas turbine, comprising:an outer liner (4), the outer liner having a flange (14) at a forward end;an inner liner (6) disposed within the outer liner, the inner liner having a first inner wall (12);a venturi (8) comprising a second inner wall (24), a venturi throat (10), and the first inner wall of the inner liner; anda slip joint (16) connected to the second inner wall, the slip joint receiving the flange of the outer liner.
- A combustion liner assembly according to claim 1, further comprising an aft section (20) provided at aft ends of the outer liner and the inner liner and a second slip joint (30) connecting the aft section and the outer liner or the inner liner.
- A combustion liner assembly according to claim 1 or claim 2, wherein the outer liner comprises a plurality of radial drain or dump holes (22).
- A combustion liner assembly according to claim 2 or claim 3, wherein the aft section comprises at least one of a plurality of radial drain or dump holes (22) and a plurality of axial drain or dump holes (24).
- A combustion liner assembly according to any one of claims 2-4, wherein the aft section comprises a plurality of holes (26) at an intersection of a cylindrical section of the aft section and a conical section of the aft section.
- A combustion liner assembly according to any one of claims 1-5, wherein the slip joint is formed of a nickel alloy and the flange is formed of stainless steel.
- A combustion liner assembly according to any one of claims 1-6, wherein the slip joint comprises a wear coating.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/759,042 US20110247340A1 (en) | 2010-04-13 | 2010-04-13 | Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2378201A2 true EP2378201A2 (en) | 2011-10-19 |
EP2378201A3 EP2378201A3 (en) | 2013-04-03 |
Family
ID=44262859
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11162106A Withdrawn EP2378201A3 (en) | 2010-04-13 | 2011-04-12 | Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly |
Country Status (4)
Country | Link |
---|---|
US (1) | US20110247340A1 (en) |
EP (1) | EP2378201A3 (en) |
CN (1) | CN102221208A (en) |
WO (1) | WO2011130001A2 (en) |
Cited By (7)
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US11255545B1 (en) | 2020-10-26 | 2022-02-22 | General Electric Company | Integrated combustion nozzle having a unified head end |
US11371702B2 (en) | 2020-08-31 | 2022-06-28 | General Electric Company | Impingement panel for a turbomachine |
US11460191B2 (en) | 2020-08-31 | 2022-10-04 | General Electric Company | Cooling insert for a turbomachine |
US11614233B2 (en) | 2020-08-31 | 2023-03-28 | General Electric Company | Impingement panel support structure and method of manufacture |
US11767766B1 (en) | 2022-07-29 | 2023-09-26 | General Electric Company | Turbomachine airfoil having impingement cooling passages |
US11994293B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus support structure and method of manufacture |
US11994292B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus for turbomachine |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20120047895A1 (en) * | 2010-08-26 | 2012-03-01 | General Electric Company | Systems and apparatus relating to combustor cooling and operation in gas turbine engines |
US8931280B2 (en) * | 2011-04-26 | 2015-01-13 | General Electric Company | Fully impingement cooled venturi with inbuilt resonator for reduced dynamics and better heat transfer capabilities |
WO2016167784A1 (en) * | 2015-04-17 | 2016-10-20 | Siemens Aktiengesellschaft | Flexible interface system for a combustor of a gas turbine engine |
JP2018520289A (en) | 2015-04-30 | 2018-07-26 | ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータNuovo Pignone Tecnologie S.R.L. | Ultra-low NOx exhaust gas turbine engine in machine drive applications |
US10139108B2 (en) * | 2015-06-08 | 2018-11-27 | Siemens Energy, Inc. | D5/D5A DF-42 integrated exit cone and splash plate |
Family Cites Families (6)
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US4920742A (en) * | 1988-05-31 | 1990-05-01 | General Electric Company | Heat shield for gas turbine engine frame |
US6921014B2 (en) * | 2002-05-07 | 2005-07-26 | General Electric Company | Method for forming a channel on the surface of a metal substrate |
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 |
US20090019854A1 (en) * | 2007-07-16 | 2009-01-22 | General Electric Company | APPARATUS/METHOD FOR COOLING COMBUSTION CHAMBER/VENTURI IN A LOW NOx COMBUSTOR |
US20110041507A1 (en) * | 2009-08-18 | 2011-02-24 | William Kirk Hessler | Integral Liner and Venturi for Eliminating Air Leakage |
-
2010
- 2010-04-13 US US12/759,042 patent/US20110247340A1/en not_active Abandoned
-
2011
- 2011-03-30 WO PCT/US2011/030449 patent/WO2011130001A2/en active Application Filing
- 2011-04-12 EP EP11162106A patent/EP2378201A3/en not_active Withdrawn
- 2011-04-13 CN CN2011101021711A patent/CN102221208A/en active Pending
Non-Patent Citations (1)
Title |
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None |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11371702B2 (en) | 2020-08-31 | 2022-06-28 | General Electric Company | Impingement panel for a turbomachine |
US11460191B2 (en) | 2020-08-31 | 2022-10-04 | General Electric Company | Cooling insert for a turbomachine |
US11614233B2 (en) | 2020-08-31 | 2023-03-28 | General Electric Company | Impingement panel support structure and method of manufacture |
US11994293B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus support structure and method of manufacture |
US11994292B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus for turbomachine |
US11255545B1 (en) | 2020-10-26 | 2022-02-22 | General Electric Company | Integrated combustion nozzle having a unified head end |
US11767766B1 (en) | 2022-07-29 | 2023-09-26 | General Electric Company | Turbomachine airfoil having impingement cooling passages |
Also Published As
Publication number | Publication date |
---|---|
CN102221208A (en) | 2011-10-19 |
WO2011130001A2 (en) | 2011-10-20 |
EP2378201A3 (en) | 2013-04-03 |
US20110247340A1 (en) | 2011-10-13 |
WO2011130001A3 (en) | 2013-05-10 |
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