EP2532961A2 - Combustor having a pressure feed - Google Patents
Combustor having a pressure feed Download PDFInfo
- Publication number
- EP2532961A2 EP2532961A2 EP12170068A EP12170068A EP2532961A2 EP 2532961 A2 EP2532961 A2 EP 2532961A2 EP 12170068 A EP12170068 A EP 12170068A EP 12170068 A EP12170068 A EP 12170068A EP 2532961 A2 EP2532961 A2 EP 2532961A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- vessel
- combustor
- annulus
- fluid
- fuel nozzles
- 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- Withdrawn
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Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- 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
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
-
- 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 combustor 10 includes an outer vessel 20, such as a compressor discharge casing (CDC), which is receptive of a first fluid 25, such as compressor discharge air output from a compressor.
- the combustor 10 further includes an annular intermediate vessel 30, an annular inner vessel 40 and a tubular assembly 50.
- the intermediate vessel 30 may be a flowsleeve of the combustor 10 and/or a transition piece and may be formed to define impingement holes 31 therein.
- the impingement holes 31 are pictured proximate to the head end, as shown in FIG. 1 , but it is understood that they may be defined further downstream at the transition piece or as an annular passage in addition to or instead of impingement holes.
- the intermediate vessel 30 is disposed within the outer vessel 20 to form an outer annulus 35 with which the first fluid 25 communicates.
- a method of assembling a combustor 10 having a pressure feed includes forming an outer annulus 35 between an outer vessel 20 and an intermediate vessel 30, forming an inner annulus 45 between the intermediate vessel 30 and an inner vessel 40 by which upstream portions 471 of fuel nozzles 47 disposed within the inner vessel 40 are to be fed, defining an internal volume 48 within the inner vessel 40 about downstream portions 472 of the fuel nozzles 47 and positioning a tubular assembly 50 by which the outer annulus 35 and the internal volume 48 are communicative.
Abstract
A combustor (10) having a pressure feed is provided and includes an outer vessel (20), an intermediate vessel (30) disposed within the outer vessel (20) to form an outer annulus (35), an inner vessel (40) disposed within the intermediate vessel (30) to form an inner annulus (45) between the intermediate and inner vessels, by which upstream portions (471) of fuel nozzles (47) disposed within the inner vessel are fed, and an internal volume (48) within the inner vessel about downstream portions (472) of the fuel nozzles (47) and a tubular assembly (50) by which the outer annulus (35) and the internal volume (48) are communicative.
Description
- The subject matter disclosed herein relates to a combustor having a pressure feed.
- For a typical combustor arrangement, a flowsleeve is inserted into an aft case that is attached to a compressor discharge case (CDC) or an integral aft case. The flowsleeve includes impingement holes formed therein. A liner is then inserted into the flowsleeve and a cap is assembled onto the flowsleeve or aft case such that fuel nozzles are operably disposed within the liner. The liner thus forms an annulus between the liner and the flowsleeve that leads to inlets of the fuel nozzles.
- With this configuration, CDC air enters the CDC from a compressor and flows through the impingement holes and into the annulus between the liner and the flowsleeve as impingement air. Additional air can be provided to the annulus from transition piece impingement cooling flows. The impingement air and the additional air then flows upstream through the annulus toward the fuel nozzle inlets where it enters the fuel nozzles so that it can be mixed with fuel for combustion operations.
- According to one aspect of the invention, a combustor having a pressure feed is provided and includes an outer vessel, an intermediate vessel disposed within the outer vessel to form an outer annulus, an inner vessel disposed within the intermediate vessel to form an inner annulus between the intermediate and inner vessels, by which upstream portions of fuel nozzles disposed within the inner vessel are fed, and an internal volume within the inner vessel about downstream portions of the fuel nozzles and a tubular assembly by which the outer annulus and the internal volume are communicative. The outer annulus is communicative with a first fluid, and second fluid is fed to upstream portions of fuel nozzles disposed within the inner vessel by the inner annulus.
- According to another aspect of the invention, a method of assembling a combustor having a pressure feed is provided and includes forming an outer annulus between an outer vessel and an intermediate vessel, forming an inner annulus between the intermediate vessel and an inner vessel by which upstream portions of fuel nozzles disposed within the inner vessel are to be fed, defining an internal volume within the inner vessel about downstream portions of the fuel nozzles and positioning a tubular assembly by which the outer annulus and the internal volume are communicative.
- These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
- Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which:
-
FIG. 1 is a perspective view of a combustor having a pressure feed; -
FIG. 2 is an enlarged side view of the combustor ofFIG. 1 ; -
FIG. 3 is a schematic illustration of a sub-assembly of the combustor ofFIG. 1 according to embodiments; and -
FIG. 4 is a side schematic view of a combustor having a pressure feed in which a transfer tube is assembled into a cap assembly for a passively fed system. - The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
- With reference to
FIGS. 1 and2 , acombustor 10 having a pressure feed is provided. Thecombustor 10 includes anouter vessel 20, such as a compressor discharge casing (CDC), which is receptive of afirst fluid 25, such as compressor discharge air output from a compressor. Thecombustor 10 further includes an annularintermediate vessel 30, an annularinner vessel 40 and atubular assembly 50. Theintermediate vessel 30 may be a flowsleeve of thecombustor 10 and/or a transition piece and may be formed to defineimpingement holes 31 therein. Theimpingement holes 31 are pictured proximate to the head end, as shown inFIG. 1 , but it is understood that they may be defined further downstream at the transition piece or as an annular passage in addition to or instead of impingement holes. Theintermediate vessel 30 is disposed within theouter vessel 20 to form anouter annulus 35 with which thefirst fluid 25 communicates. - The
inner vessel 40 may be a liner of thecombustor 10 that is disposed within theintermediate vessel 30 such that theinner vessel 40 forms aninternal volume 48 and theinner vessel 40 and theintermediate vessel 30 form aninner annulus 45. Theinner annulus 45 is defined between theintermediate vessel 30 and theinner vessel 40. By way of theinner annulus 45, asecond fluid 46, such as impingement air, is fed to upstream portions 471 (i.e., inlets) offuel nozzles 47 that are operably disposed within theinner vessel 40. Thefuel nozzles 47 may include a central fuel nozzle and a plurality of outer fuel nozzles disposed around the central fuel nozzle. Thesecond fluid 46 is provided as a portion of thefirst fluid 25 that flows from theouter annulus 35 into theinner annulus 45 via theimpingement holes 31. - The
internal volume 48 is defined within theinner vessel 40 as first and secondinternal volume sections internal volume section 482 being disposed downstream from the firstinternal volume section 481. In accordance with embodiments, the firstinternal volume section 481 may be formed as a cap internal volume that is disposed aboutdownstream portions 472 of thefuel nozzles 47. This cap internal volume is defined betweeninternal volume wall 4811 andcap face 4812. The secondinternal volume section 482 is defined downstream from thecap face 4812 and thenozzles 47 and may be formed as a combustion zone. - The
tubular assembly 50 provides for a pathway by which thefirst fluid 25 is transmittable from theouter annulus 35 to theinternal volume 48. More particularly, thetubular assembly 50 provides for a pathway by which thefirst fluid 25 is transmittable from theouter annulus 35 to the firstinternal volume section 481. - As shown in
FIG. 2 , thetubular assembly 50 may include atube 51 andseals 52 positioned around thetube 51 at theintermediate vessel 30 and theinner vessel 40 to prevent leakage of thefirst fluid 25. Thetube 51 has atubular sidewall 511 defining aninterior 512. Thetube 51 also has a closedend 513, anopen end 514 opposite the closedend 513 and anaperture 515 providing access to theinterior 512. Thetube 51 is oriented in a radial direction with respect to theouter annulus 35 and is installed in thecombustor 10 to extend from at least theouter annulus 35 to the firstinternal volume section 481. In accordance with embodiments, thetube 51 has a length whereby the closedend 513 may extend to an exterior of theouter vessel 20, theopen end 514 is disposed within the firstinternal volume section 481 and theaperture 515 is positioned within theouter annulus 35. - Also, as shown in
FIG. 2 , thetubular assembly 50 may be configured to admit a cooler air supply by way of acooler air feed 520. Such a cooler air supply may serve to mitigate combustion dynamics by providing for a variable cavity pressure. In addition, the cooler air supply may allow thecap face 4812 to operate at a relatively cool temperature and, with or without a possible addition of an inert gas, may assist in maintenance of a flame at a predefined safe distance from thecap face 4812. - The
tubular assembly 50 may further include a plurality oftubes 51. In this case, each of the plurality oftubes 51 hasseals 52 at theintermediate vessel 30 and theinner vessel 40 and is constructed as described above. The plurality oftubes 51 may be arrayed circumferentially about thecombustor 10 based on flow requirements. The plurality oftubes 51 may also be disposed at axially staggered positions based on predefined and/or determined flow requirements. - In accordance with further embodiments,
aperture 515 may be formed as a window in a circumferential portion of thetubular sidewall 511 and thetube 51 may be oriented such that theaperture 515 faces in the downstream direction. In this way, thefirst fluid 25 moving upstream toward the combustor head end can relatively easily flow into theinterior 512 via theaperture 515. - In accordance with still further embodiments and, with reference to
FIG. 3 , thetubular assembly 50 may include asub-assembly 60 by which an amount of the transmittablefirst fluid 25 is controllable. For example, as shown inFIG. 3 , thesub-assembly 60 may include a tube-in-tube assembly 61 that is operably coupled to acontroller 62. The tube-in-tube assembly 61 includes asecondary tube 611 having anaperture 612 that is disposed within thetube 51. Thecontroller 62 rotates thesecondary tube 611 within thetube 51 such that theaperture 612 becomes rotationally aligned with or mis-aligned with theaperture 515 to thereby increase or decrease the amount of the transmittablefirst fluid 25, respectively. Thus, when theaperture 612 is aligned with theaperture 515 and thetubular assembly 50 is open, as shown, about 10% of thefirst fluid 25 is transmittable to the firstinternal volume section 481 and 90% flows into theinner annulus 45 as the second fluid 46 (i.e., impingement air). By contrast, when theaperture 612 and theaperture 515 are mis-aligned and thetubular assembly 50 is closed, about 100% of thefirst fluid 25 flows into theinner annulus 45 as thesecond fluid 46. - The
tubular assembly 50 allows for a feed of, for example, pressurized air from a compressor discharge casing to a cap internal volume and may be installed after the assembly of the flowsleeve, the liner and the cap. As a result, the capinternal volume 481 may be provided with a higher cap pressure leading to increased durability for the effusion plate either by increasing the pressure drop across the plate or by introducing an impingement plate to cool the back side of the pate. During periods of high combustion dynamics, the higher pressure drop may also help to prevent hot combustion products from being forced upstream into the effusion holes and may be a tool to mitigate some dynamics. - In accordance with further aspects and, with reference to
FIG. 4 , acap assembly 100 may be provided and includes aforward case 101 and anaft case 102. Theforward case 101 includes forward portions of theintermediate vessel 30 and theinner vessel 40 with acap strut 103 supportively disposed therebetween. Theaft case 102 is integrally connected with the CDC and includes aft portions of theintermediate vessel 30 and theinner vessel 40, which form theouter annulus 35. Theinner vessel 40 forms acap cavity 105 and atransfer tube 110 is assembled into thecap assembly 100 to passively feed the first fluid 25 from theouter annulus 35 to thecap cavity 105. In accordance with embodiments, thetransfer tube 110 may be attached or welded to, for example, theforward case 101 of thecap assembly 100 at one or both ends thereof and may be further provided with aseal 111. - In accordance with still further aspects, a method of assembling a
combustor 10 having a pressure feed is provided. The method includes forming anouter annulus 35 between anouter vessel 20 and anintermediate vessel 30, forming aninner annulus 45 between theintermediate vessel 30 and aninner vessel 40 by whichupstream portions 471 offuel nozzles 47 disposed within theinner vessel 40 are to be fed, defining aninternal volume 48 within theinner vessel 40 aboutdownstream portions 472 of thefuel nozzles 47 and positioning atubular assembly 50 by which theouter annulus 35 and theinternal volume 48 are communicative. - While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims (13)
- A combustor (10) having a pressure feed, comprising:an outer vessel (20);an intermediate vessel (30) disposed within the outer vessel (20) to form an outer annulus (35) ;an inner vessel (40) disposed within the intermediate vessel (35) to form an inner annulus (45) between the intermediate and inner vessels, by which upstream portions (471) of fuel nozzles (47) disposed within the inner vessel are fed, and an internal volume (48) within the inner vessel (40) about downstream portions (472) of the fuel nozzles (47); anda tubular assembly (50) by which the outer annulus (35) and the internal volume (48) are communicative.
- The combustor (10) according to claim 1, wherein the outer vessel (20) comprises a compressor discharge casing, the intermediate vessel (30) comprises a flow sleeve having impingement holes (31) formed therein and the inner vessel 40 comprises a combustor liner.
- The combustor (10) according to claim 1 or 2, wherein compressor discharge air is deliverable to the internal volume (48) by the tubular assembly (50).
- The combustor (10) according to any of claims 1 to 3, wherein the outer vessel (20), the intermediate vessel (30) and the inner vessel (40) form a cap assembly (100) to which the tubular assembly (50) is attached and sealed.
- The combustor (10) according to any of claims 1 to 4, wherein the fuel nozzles (47) comprise a central fuel nozzle and a plurality of outer fuel nozzles.
- The combustor (10) according to any preceding claim, wherein the tubular assembly (50) comprises a tube (51) oriented in a radial direction of the outer annulus (35).
- The combustor (10) according to any of claims 1 to 5, wherein the tubular assembly (50) comprises a plurality of circumferentially arrayed tubes (51), each of the plurality of circumferentially arrayed tubes (51) being oriented in a radial direction.
- The combustor (10) according to any of claims 1 to 5, wherein the tubular assembly (50) comprises a tube-in-tube sub-assembly (60) operably coupled to a controller (62).
- The combustor (10) of any preceding claim, wherein the outer annulus (35) is communicative with a first fluid (25); and
a second fluid (46) is fed to upstream portions (471) of fuel nozzles (47) disposed within the inner vessel by the inner annulus (45). - The combustor (10) according to claim 9, wherein the first fluid (25) comprises compressor discharge air, the second fluid (46) is a portion of the first fluid (25) flowing through the impingement holes (31) as impingement air.
- The combustor according to claim 9 or 10, wherein the second fluid (46) is fed to inlets of the fuel nozzles (47) at the upstream portions (471) thereof.
- A method of assembling a combustor (10) having a pressure feed, comprising:forming an outer annulus (35) between an outer vessel (20) and an intermediate vessel (30);forming an inner annulus (35) between the intermediate vessel (30) and an inner vessel (40) by which upstream portions of fuel nozzles (47) disposed within the inner vessel (40) are to be fed;defining an internal volume (48) within the inner vessel (40) about downstream portions (472) of the fuel nozzles (47); andpositioning a tubular assembly (50) by which the outer annulus (35) and the internal volume (48) are communicative.
- The method according to claim 12, further comprising positioning a sub-assembly (60) within the tubular assembly (50) by which an amount of transmittable fluid (25) is controllable.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/154,027 US20120308947A1 (en) | 2011-06-06 | 2011-06-06 | Combustor having a pressure feed |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2532961A2 true EP2532961A2 (en) | 2012-12-12 |
Family
ID=46172723
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12170068A Withdrawn EP2532961A2 (en) | 2011-06-06 | 2012-05-30 | Combustor having a pressure feed |
Country Status (3)
Country | Link |
---|---|
US (1) | US20120308947A1 (en) |
EP (1) | EP2532961A2 (en) |
CN (1) | CN102818264A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107110505A (en) * | 2014-10-20 | 2017-08-29 | 安萨尔多能源公司 | The gas turbine unit and the method for the burner of supply gas turbine unit supplied with multithread fluid fuel |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9631815B2 (en) * | 2012-12-28 | 2017-04-25 | General Electric Company | System and method for a turbine combustor |
US9297535B2 (en) * | 2013-02-25 | 2016-03-29 | General Electric Company | Fuel/air mixing system for fuel nozzle |
US10352569B2 (en) * | 2016-11-04 | 2019-07-16 | General Electric Company | Multi-point centerbody injector mini mixing fuel nozzle assembly |
US10295190B2 (en) * | 2016-11-04 | 2019-05-21 | General Electric Company | Centerbody injector mini mixer fuel nozzle assembly |
US10393382B2 (en) * | 2016-11-04 | 2019-08-27 | General Electric Company | Multi-point injection mini mixing fuel nozzle assembly |
CN114151789B (en) * | 2022-02-09 | 2022-04-22 | 杭州宾欧新能源技术有限公司 | Burner protected by inert gas |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4255927A (en) * | 1978-06-29 | 1981-03-17 | General Electric Company | Combustion control system |
US4412414A (en) * | 1980-09-22 | 1983-11-01 | General Motors Corporation | Heavy fuel combustor |
KR930013441A (en) * | 1991-12-18 | 1993-07-21 | 아더 엠.킹 | Gas turbine combustor with multiple combustors |
US20100192582A1 (en) * | 2009-02-04 | 2010-08-05 | Robert Bland | Combustor nozzle |
US8474266B2 (en) * | 2009-07-24 | 2013-07-02 | General Electric Company | System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle |
US20120304652A1 (en) * | 2011-05-31 | 2012-12-06 | General Electric Company | Injector apparatus |
US8966907B2 (en) * | 2012-04-16 | 2015-03-03 | General Electric Company | Turbine combustor system having aerodynamic feed cap |
-
2011
- 2011-06-06 US US13/154,027 patent/US20120308947A1/en not_active Abandoned
-
2012
- 2012-05-30 EP EP12170068A patent/EP2532961A2/en not_active Withdrawn
- 2012-06-06 CN CN2012101839518A patent/CN102818264A/en active Pending
Non-Patent Citations (1)
Title |
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None |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107110505A (en) * | 2014-10-20 | 2017-08-29 | 安萨尔多能源公司 | The gas turbine unit and the method for the burner of supply gas turbine unit supplied with multithread fluid fuel |
Also Published As
Publication number | Publication date |
---|---|
US20120308947A1 (en) | 2012-12-06 |
CN102818264A (en) | 2012-12-12 |
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