WO2016167784A1 - Flexible interface system for a combustor of a gas turbine engine - Google Patents
Flexible interface system for a combustor of a gas turbine engine Download PDFInfo
- Publication number
- WO2016167784A1 WO2016167784A1 PCT/US2015/026274 US2015026274W WO2016167784A1 WO 2016167784 A1 WO2016167784 A1 WO 2016167784A1 US 2015026274 W US2015026274 W US 2015026274W WO 2016167784 A1 WO2016167784 A1 WO 2016167784A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- combustor
- combustor basket
- flexible
- interface system
- flexible extension
- Prior art date
Links
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
- F23R3/42—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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
Definitions
- the present invention relates in general to combustion support systems in turbine engines and, more particularly, to support systems for movement between a combustor basket, a combustor basket liner and downstream transition components.
- a combustor basket is coupled to a downstream combustor basket liner via a ramp and spring clip within a combustor.
- Transient radial relative displacement between the downstream end of the combustor basket liner and the transition inlet, combined with the runout of the combustion spring clip location, can result in the spring clips completely bottoming out. Once the spring clips have bottomed out, any additional displacement results in high stress in the combustor basket, the downstream transition, or both.
- a flexible interface system for a combustor of a gas turbine engine in which a flexible extension is configured to enable radial movement of a combustor basket liner relative to a transition downstream from the combustor basket liner while maintaining a seal and without creating excessive stress is disclosed.
- the flexible interface system may couple a combustor basket liner of a can-annular combustor basket formed from one or more outer walls defining a combustor chamber with a transition extending downstream from the combustor basket.
- the flexible extension may include one or more serpentine switchbacks which enhances flexibility of the flexible extension to accommodate and radial movement of the combustor basket liner without damaging the flexible extension or adjacent components.
- the flexible interface system for a combustor of a gas turbine engine may include one or more combustor baskets formed from one or more outer walls defining a combustor chamber with one or more combustor basket liners positioned within the combustor chamber and a transition extending
- the flexible interface system may include one or more flexible extensions extending from a combustor basket support structure to the combustor basket liner.
- the flexible extension may be configured to enable axial and radial movement of the combustor basket liner relative to a longitudinal axis of the combustor basket.
- the flexible extension may be rigidly coupled to the combustor basket, such as via support structure of the combustor basket.
- the flexible extension may be rigidly coupled to a downstream end of support structure of at least one combustor basket.
- the flexible extension may be rigidly coupled to at least one combustor basket liner.
- the flexible extension may be rigidly coupled to an upstream end of the combustor basket liner.
- the flexible extension may be formed from one or more serpentine
- the serpentine switchback may be positioned such that ridge of the serpentine switchback is positioned nonparallel to a longitudinal axis of the combustor basket.
- the serpentine switchback may be positioned such that one or more ridges of the serpentine switchback is positioned orthogonal to the longitudinal axis of the combustor basket.
- the flexible extension may be formed from a plurality of serpentine switchbacks within material forming the flexible extension.
- the flexible extension may be generally cylindrical with an upstream inlet having a larger diameter than a downstream outlet.
- the flexible extension may couple the combustor basket liner to a transition without use of one or more spring clips.
- the flexible interface system may be configured to accommodate predicted transient axial and radial relative motion between the combustor, the combustor basket liner and downstream transitions.
- the flexible interface system may also accommodate radial relative motion by expanding the flexible extension or via the sliding fit at the interface between the internal flow wall of the combustor basket liner and the transition.
- a spring clip is not necessary to provide an adequate seal between the combustor basket liner and the transition.
- the combustor liner may be rigidly attached to the transition. Eliminating the spring clip also eliminates the leakage associated with the spring clip.
- Figure 1 is a partial cross-sectional view of a gas turbine engine with a flexible interface system at a combustor.
- Figure 2 is a cross-sectional view of a combustor of the gas turbine engine shown in Figure 1 together with the flexible interface system.
- Figure 3 is a cross-sectional view of the combustor with the flexible interface system.
- Figure 4 is a cross-sectional, detail view on one side of combustor with the flexible interface system.
- a flexible interface system 10 for a combustor 12 of a gas turbine engine 14 in which a flexible extension 16 is configured to enable radial movement 20 of a combustor basket liner 22 relative to a transition 50 downstream from the combustor basket liner 22 while maintaining a seal and without creating excessive stress is disclosed.
- the flexible interface system 10 may couple a combustor basket liner 22 of a can-annular combustor basket 24 formed from one or more outer walls 28 defining a combustor chamber 30 with a transition 50 extending downstream from the combustor basket 24.
- the flexible extension 16 may include one or more serpentine switchbacks 32 which enhances flexibility of the flexible extension 16 to accommodate radial movement of the combustor basket liner 22 without damaging the flexible extension 16 or adjacent components.
- the flexible interface system 10 may include one or more combustor baskets 24 formed from one or more outer walls 28 defining the combustor chamber 30 and one or more combustor basket liners 22 positioned within the combustor chamber 30.
- a transition 50 may extend downstream from the combustor basket liner 22.
- the flexible interface system 10 may include one or more flexible extensions 16 extending from the combustor basket 24 to the combustor basket liner 22.
- the flexible extension 16 may be configured to enable radial movement of the combustor basket liner 22 relative to a longitudinal axis 46 of the combustor basket 24.
- the flexible extension 16 may be generally cylindrical with an upstream inlet 34 having a larger diameter than a downstream outlet 36.
- the flexible extension 16 may have other configurations and size relationships.
- the flexible extension 16 may be shielded by an internal flow wall 40 that extends upstream from an upstream end 48 of the combustor basket liner 22.
- the internal flow wall 40 may be slidably coupled to the upstream end 48 of the combustor basket liner 22.
- the internal flow wall 40 may have a smaller diameter than the flexible extension 16. As such, the flexible extension 16 is shielded from direct exposure to the hot gases contained within the combustor basket 24.
- the flexible extension 16 may be rigidly coupled to the combustor basket 24, such as via combustor basket support structure 39 of the combustor basket 24.
- the combustor basket support structure 39 may be formed from a combustor basket support flange that is rigidly coupled to the casing.
- the flexible extension 16 may be rigidly coupled to a downstream end 38 of support structure 39 for the combustor basket 24.
- the flexible extension 16 may also be rigidly coupled to an upstream end 48 of the combustor basket liner 22.
- the flexible extension 16 may be rigidly coupled to an outer surface 42 of the combustor basket liner 22.
- the flexible extension 16 may be formed from one or more serpentine switchbacks 32 within material forming the flexible extension 16.
- the serpentine switchback 32 may be positioned such that one or more ridges 44 of the serpentine switchback 32 are positioned nonparallel to a longitudinal axis 46 of the combustor basket 24.
- the serpentine switchback 32 may be positioned such that one or more ridges 44 of the serpentine switchback 32 is positioned orthogonal to the longitudinal axis 46 of the combustor basket 24.
- the flexible extension 16 may be formed from a plurality of serpentine switchbacks 32 within material forming the at least one flexible extension.
- the serpentine switchback 32 may extend circumferential ly around the flexible extension 16 forming rings.
- the flexible extension 16 may form a cylindrical tube.
- one or more flexible extensions 16 may couple the combustor basket liner 22 to the transition 50 without use of spring clips.
- the flexible interface system 10 may be used to seal the combustor basket 24 via the combustor basket liner 22 to the transition 50 without the use of spring clips, which improves the durability of the flexible interface system 10 by eliminating problems associated with the spring clips.
- the transition 50 may be coupled to the combustor basket liner 22 via a rigid connection with no axial movement relative to each other permitted.
- the transition 50 may be coupled to the combustor basket liner 22 via a sliding connection permitting axial movement relative to each other along the longitudinal axis 46 of the combustor basket 24.
- the flexible interface system 10 is configured to accommodate predicted transient radial relative motion between the combustor 12, the combustor basket liner 22 and downstream transitions 50.
- the flexible interface system 10 may also accommodate axial relative motions by expanding the flexible extension 16. As such, a spring clip is not necessary to provide an adequate seal between the combustor basket liner 22 and the transition 50. Eliminating the spring clip also eliminates the leakage associated with the spring clip.
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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
A flexible interface system (10) for a combustor (12) of a gas turbine engine (14) in which a flexible extension (16) is configured to enable radial movement of a combustor basket liner (22) relative to a combustor basket (24) while maintaining a seal and without creating excessive stress is disclosed. The flexible interface system (10) may couple a can-annular combustor basket (24) formed from one or more outer walls (28) defining a combustor chamber (30) with one or more combustor basket liners (22) extending downstream from the combustor basket (24). The flexible extension (16) may include one or more serpentine switchbacks (32) which enhances flexibility of the flexible extension (16) to accommodate radial movement of the combustor basket liner (22) without damaging the flexible extension (16) or adjacent components.
Description
FLEXIBLE INTERFACE SYSTEM FOR A COMBUSTOR OF
A GAS TURBINE ENGINE
FIELD OF THE INVENTION
The present invention relates in general to combustion support systems in turbine engines and, more particularly, to support systems for movement between a combustor basket, a combustor basket liner and downstream transition components.
BACKGROUND OF THE INVENTION
Typically, a combustor basket is coupled to a downstream combustor basket liner via a ramp and spring clip within a combustor. Transient radial relative displacement between the downstream end of the combustor basket liner and the transition inlet, combined with the runout of the combustion spring clip location, can result in the spring clips completely bottoming out. Once the spring clips have bottomed out, any additional displacement results in high stress in the combustor basket, the downstream transition, or both. Thus, a system capable of
accommodating movement between the downstream end of the combustor basket liner and the transition inlet without creating undue stress is desired. SUMMARY OF THE INVENTION
A flexible interface system for a combustor of a gas turbine engine in which a flexible extension is configured to enable radial movement of a combustor basket liner relative to a transition downstream from the combustor basket liner while maintaining a seal and without creating excessive stress is disclosed. The flexible interface system may couple a combustor basket liner of a can-annular combustor basket formed from one or more outer walls defining a combustor chamber with a transition extending downstream from the combustor basket. The flexible extension may include one or more serpentine switchbacks which enhances flexibility of the flexible extension to accommodate and radial movement of the combustor basket liner without damaging the flexible extension or adjacent components.
In at least one embodiment, the flexible interface system for a combustor of a gas turbine engine may include one or more combustor baskets formed from one or
more outer walls defining a combustor chamber with one or more combustor basket liners positioned within the combustor chamber and a transition extending
downstream from the combustor basket liner. The flexible interface system may include one or more flexible extensions extending from a combustor basket support structure to the combustor basket liner. The flexible extension may be configured to enable axial and radial movement of the combustor basket liner relative to a longitudinal axis of the combustor basket. By enabling some axial displacement via the flexible interface system, leakages between the combustor basket liner and the transition could be eliminated and the recirculation zone downstream of the combustor may be eliminated, thereby reducing, if not eliminating, high frequency dynamics within the combustor.
In at least one embodiment, the flexible extension may be rigidly coupled to the combustor basket, such as via support structure of the combustor basket. The flexible extension may be rigidly coupled to a downstream end of support structure of at least one combustor basket. The flexible extension may be rigidly coupled to at least one combustor basket liner. The flexible extension may be rigidly coupled to an upstream end of the combustor basket liner.
The flexible extension may be formed from one or more serpentine
switchbacks within material forming the flexible extension. The serpentine switchback may be positioned such that ridge of the serpentine switchback is positioned nonparallel to a longitudinal axis of the combustor basket. The serpentine switchback may be positioned such that one or more ridges of the serpentine switchback is positioned orthogonal to the longitudinal axis of the combustor basket. The flexible extension may be formed from a plurality of serpentine switchbacks within material forming the flexible extension. In at least one embodiment, the flexible extension may be generally cylindrical with an upstream inlet having a larger diameter than a downstream outlet.
In at least one embodiment, the flexible extension may couple the combustor basket liner to a transition without use of one or more spring clips. The flexible interface system may be configured to accommodate predicted transient axial and radial relative motion between the combustor, the combustor basket liner and downstream transitions. The flexible interface system may also accommodate radial
relative motion by expanding the flexible extension or via the sliding fit at the interface between the internal flow wall of the combustor basket liner and the transition. As such, a spring clip is not necessary to provide an adequate seal between the combustor basket liner and the transition. Instead, the combustor liner may be rigidly attached to the transition. Eliminating the spring clip also eliminates the leakage associated with the spring clip.
These and other advantages and objects will become apparent upon review of the detailed description of the invention set forth below. BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention.
Figure 1 is a partial cross-sectional view of a gas turbine engine with a flexible interface system at a combustor.
Figure 2 is a cross-sectional view of a combustor of the gas turbine engine shown in Figure 1 together with the flexible interface system.
Figure 3 is a cross-sectional view of the combustor with the flexible interface system.
Figure 4 is a cross-sectional, detail view on one side of combustor with the flexible interface system.
DETAILED DESCRIPTION OF THE INVENTION
As shown in Figures 1-4, a flexible interface system 10 for a combustor 12 of a gas turbine engine 14 in which a flexible extension 16 is configured to enable radial movement 20 of a combustor basket liner 22 relative to a transition 50 downstream from the combustor basket liner 22 while maintaining a seal and without creating excessive stress is disclosed. The flexible interface system 10 may couple a combustor basket liner 22 of a can-annular combustor basket 24 formed from one or more outer walls 28 defining a combustor chamber 30 with a transition 50 extending downstream from the combustor basket 24. The flexible extension 16 may include one or more serpentine switchbacks 32 which enhances flexibility of the flexible
extension 16 to accommodate radial movement of the combustor basket liner 22 without damaging the flexible extension 16 or adjacent components.
In at least one embodiment, the flexible interface system 10 may include one or more combustor baskets 24 formed from one or more outer walls 28 defining the combustor chamber 30 and one or more combustor basket liners 22 positioned within the combustor chamber 30. A transition 50 may extend downstream from the combustor basket liner 22. The flexible interface system 10 may include one or more flexible extensions 16 extending from the combustor basket 24 to the combustor basket liner 22. The flexible extension 16 may be configured to enable radial movement of the combustor basket liner 22 relative to a longitudinal axis 46 of the combustor basket 24. In at least one embodiment, the flexible extension 16 may be generally cylindrical with an upstream inlet 34 having a larger diameter than a downstream outlet 36. In other embodiments, the flexible extension 16 may have other configurations and size relationships. The flexible extension 16 may be shielded by an internal flow wall 40 that extends upstream from an upstream end 48 of the combustor basket liner 22. The internal flow wall 40 may be slidably coupled to the upstream end 48 of the combustor basket liner 22. The internal flow wall 40 may have a smaller diameter than the flexible extension 16. As such, the flexible extension 16 is shielded from direct exposure to the hot gases contained within the combustor basket 24.
As shown in Figures 3 and 4, the flexible extension 16 may be rigidly coupled to the combustor basket 24, such as via combustor basket support structure 39 of the combustor basket 24. In at least one embodiment, the combustor basket support structure 39 may be formed from a combustor basket support flange that is rigidly coupled to the casing. In at least one embodiment, the flexible extension 16 may be rigidly coupled to a downstream end 38 of support structure 39 for the combustor basket 24. The flexible extension 16 may also be rigidly coupled to an upstream end 48 of the combustor basket liner 22. In at least one embodiment, the flexible extension 16 may be rigidly coupled to an outer surface 42 of the combustor basket liner 22.
The flexible extension 16 may be formed from one or more serpentine switchbacks 32 within material forming the flexible extension 16. The serpentine
switchback 32 may be positioned such that one or more ridges 44 of the serpentine switchback 32 are positioned nonparallel to a longitudinal axis 46 of the combustor basket 24. The serpentine switchback 32 may be positioned such that one or more ridges 44 of the serpentine switchback 32 is positioned orthogonal to the longitudinal axis 46 of the combustor basket 24. In at least one embodiment, the flexible extension 16 may be formed from a plurality of serpentine switchbacks 32 within material forming the at least one flexible extension. The serpentine switchback 32 may extend circumferential ly around the flexible extension 16 forming rings. The flexible extension 16 may form a cylindrical tube.
In at least one embodiment, one or more flexible extensions 16 may couple the combustor basket liner 22 to the transition 50 without use of spring clips. The flexible interface system 10 may be used to seal the combustor basket 24 via the combustor basket liner 22 to the transition 50 without the use of spring clips, which improves the durability of the flexible interface system 10 by eliminating problems associated with the spring clips. In one embodiment, the transition 50 may be coupled to the combustor basket liner 22 via a rigid connection with no axial movement relative to each other permitted. In another embodiment, the transition 50 may be coupled to the combustor basket liner 22 via a sliding connection permitting axial movement relative to each other along the longitudinal axis 46 of the combustor basket 24.
The flexible interface system 10 is configured to accommodate predicted transient radial relative motion between the combustor 12, the combustor basket liner 22 and downstream transitions 50. The flexible interface system 10 may also accommodate axial relative motions by expanding the flexible extension 16. As such, a spring clip is not necessary to provide an adequate seal between the combustor basket liner 22 and the transition 50. Eliminating the spring clip also eliminates the leakage associated with the spring clip.
The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention or the following claims.
Claims
1 . A flexible interface system (10) for a combustor (12) of a gas turbine engine (14), characterized in that:
at least one combustor basket (24) formed from at least one outer wall (28) defining a combustor chamber (30);
at least one combustor basket liner (22) extending downstream from the at least one combustor basket (24); and
at least one flexible extension (16) extending from the at least one combustor basket (24) to the at least one combustor basket liner (22), wherein the at least one flexible extension (16) is configured to enable radial movement of the at least one combustor basket liner (22) relative to the at least one combustor basket (24).
2. The flexible interface system (10) of claim 1 , characterized in that the at least one flexible extension (16) is rigidly coupled to the at least one combustor basket (24).
3. The flexible interface system (10) of claim 1 , characterized in that the at least one flexible extension (16) is rigidly coupled to a downstream end (38) of the at least one combustor basket (24).
4. The flexible interface system (10) of claim 1 , characterized in that the at least one flexible extension (16) is rigidly coupled to the at least one combustor basket liner (22).
5. The flexible interface system (10) of claim 4, characterized in that the at least one flexible extension (16) is rigidly coupled to an upstream end (48) of the at least one combustor basket liner (22).
6. The flexible interface system (10) of claim 1 , characterized in that the at least one flexible extension (16) is formed from at least one serpentine switchback (32) within material forming the at least one flexible extension (16).
7. The flexible interface system (10) of claim 6, characterized in that the at least one serpentine switchback (32) is positioned such that at least one ridge (44) of the at least one serpentine switchback (32) is positioned nonparallel to a longitudinal axis (46) of the at least one combustor basket (24).
8. The flexible interface system (10) of claim 7, characterized in that the at least one serpentine switchback (32) is positioned such that at least one ridge (44) of the at least one serpentine switchback (32) is positioned orthogonal to the longitudinal axis (46) of the at least one combustor basket (24).
9. The flexible interface system (10) of claim 1 , characterized in that the at least one flexible extension (16) is formed from a plurality of serpentine switchbacks (32) within material forming the at least one flexible extension (16).
10. The flexible interface system (10) of claim 1 , characterized in that the at least one flexible extension (16) is generally cylindrical with an upstream inlet (34) having a larger diameter than a downstream outlet (36).
1 1 . The flexible interface system (10) of claim 1 , characterized in that the at least one flexible extension (16) couples the at least one combustor basket (24) to the at least one combustor basket liner (22) without use of at least one spring clip.
12
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/US2015/026274 WO2016167784A1 (en) | 2015-04-17 | 2015-04-17 | Flexible interface system for a combustor of a gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/US2015/026274 WO2016167784A1 (en) | 2015-04-17 | 2015-04-17 | Flexible interface system for a combustor of a gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2016167784A1 true WO2016167784A1 (en) | 2016-10-20 |
Family
ID=53008924
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US2015/026274 WO2016167784A1 (en) | 2015-04-17 | 2015-04-17 | Flexible interface system for a combustor of a gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| WO (1) | WO2016167784A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115298485A (en) * | 2020-03-10 | 2022-11-04 | 西门子能源全球有限两合公司 | Combustion chamber with ceramic heat shield and seal |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2748567A (en) * | 1949-10-13 | 1956-06-05 | Gen Motors Corp | Gas turbine combustion chamber with telescoping casing and liner sections |
| WO2011130001A2 (en) * | 2010-04-13 | 2011-10-20 | General Electric Company | Apparatus and method for minimzing and/or eliminating dilution air leakage in a combustion liner assembly |
| US20130232977A1 (en) * | 2012-03-08 | 2013-09-12 | General Electric Company | Fuel nozzle and a combustor for a gas turbine |
| US20140260316A1 (en) * | 2013-03-14 | 2014-09-18 | Adam J. Weaver | Gas turbine transition inlet ring adapter |
-
2015
- 2015-04-17 WO PCT/US2015/026274 patent/WO2016167784A1/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2748567A (en) * | 1949-10-13 | 1956-06-05 | Gen Motors Corp | Gas turbine combustion chamber with telescoping casing and liner sections |
| WO2011130001A2 (en) * | 2010-04-13 | 2011-10-20 | General Electric Company | Apparatus and method for minimzing and/or eliminating dilution air leakage in a combustion liner assembly |
| US20130232977A1 (en) * | 2012-03-08 | 2013-09-12 | General Electric Company | Fuel nozzle and a combustor for a gas turbine |
| US20140260316A1 (en) * | 2013-03-14 | 2014-09-18 | Adam J. Weaver | Gas turbine transition inlet ring adapter |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115298485A (en) * | 2020-03-10 | 2022-11-04 | 西门子能源全球有限两合公司 | Combustion chamber with ceramic heat shield and seal |
| CN115298485B (en) * | 2020-03-10 | 2023-10-27 | 西门子能源全球有限两合公司 | Combustion chamber with ceramic heat shield and seal |
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