CN102809174A - Turbomachine combustor assembly - Google Patents

Turbomachine combustor assembly Download PDF

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Publication number
CN102809174A
CN102809174A CN2012101917216A CN201210191721A CN102809174A CN 102809174 A CN102809174 A CN 102809174A CN 2012101917216 A CN2012101917216 A CN 2012101917216A CN 201210191721 A CN201210191721 A CN 201210191721A CN 102809174 A CN102809174 A CN 102809174A
Authority
CN
China
Prior art keywords
combustion chamber
lining
outer barrel
barrel member
end cap
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.)
Pending
Application number
CN2012101917216A
Other languages
Chinese (zh)
Inventor
R·J·罗尔森
D·W·奇拉
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of CN102809174A publication Critical patent/CN102809174A/en
Pending legal-status Critical Current

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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
    • F23R3/60—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
    • 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
    • F23R2900/00012—Details of sealing devices
    • 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
    • Y10T29/49346—Rocket or jet device making

Abstract

A turbomachine combustor assembly includes a combustor housing and a combustor body. The combustor body defines a combustor liner having a first end portion that extends to a second end portion through a combustion chamber. A cap assembly is mounted at the combustor housing. The cap assembly includes an endcover, a plurality of fuel nozzles supported by the end cover, and an outer barrel member. The outer barrel member extends about the plurality of fuel nozzles. A liner stop is arranged on one of the outer barrel member and the first end portion of the combustor liner. The liner stop includes a stepped lip portion that receives the other of the outer barrel member and the first end portion of the combustor liner to form substantially smooth liner to outer barrel interface. The liner stop restricts axial movement of the combustor liner relative to the outer barrel member.

Description

The turbine combustion chamber assembly
Technical field
The present invention relates to the turbine field, exactly, relate to a kind of turbine combustion chamber assembly that comprises the lining baffle plate.
Background technology
In the conventional turbine machine, first fluid, fuel for example, with one other fluid, air for example mixes being incorporated in that burning was directed into earlier in the end cap of combustion chamber in the combustion chamber before forming hot gas.First fluid gets into the combustion chamber end cap through the fuel manifold that is connected to burning chamber shell.The air that compressor is discharged gets into the burning end cap through the passage that between end cap lining and combustion chamber, extends, thus and fuel mix.The end cap lining is supported between combustion chamber and the outer cylinder housing at interval.The burning end cap generally includes several lining baffle plates, and these lining baffle plates cooperate with lining with the axially-movable of restriction end cap lining in the turbine running.
Summary of the invention
According to the one side of exemplary embodiment, the turbine combustion chamber assembly comprises: combustor outer casing, and it has first end; And the combustion chamber main body, it is arranged in the said combustor outer casing.Said combustion chamber main body is provided with combustion chamber lining, and said combustion chamber lining has and passes the first end section that the combustion chamber extends to the second end section.End cap assembly is installed in the said first end place of said combustor outer casing.Said end cap assembly comprises end cap, by a plurality of fuel nozzles of said endcap support, and the outer barrel member that between said end cap and said combustor outer casing, extends.Said outer barrel member extends around said a plurality of fuel nozzles.On in the said first end section of lining baffle arrangement barrel member and said combustion chamber lining outside said one of them.Said lining baffle plate comprises the scalariform lip portion, is used for holding another of said first end section of said outer barrel member and said combustion chamber lining, to form level and smooth substantially lining urceolus interface.Said lining baffle plate limits the axially-movable of said combustion chamber lining with respect to said outer barrel member.
Further comprise the containment member (94) that is arranged on the level and smooth lining urceolus interface (90) of said cardinal principle.
Further, said containment member (94) is located on the said scalariform lip portion (83).
Further, said containment member (94) locates in said scalariform lip portion (83) that barrel member (66) radially extends outside said.
Further, said containment member (94) comprises lip ring (99).
Further, the level and smooth lining urceolus interface (90) of said cardinal principle flows to the fluid stream of said end cap (52) through said combustion chamber lining with adjustment through configuration and setting.
Further, said scalariform lip portion (83) is through disposing and being provided with to impel laminar flow substantially to pass the level and smooth lining urceolus interface (90) of said cardinal principle.
Further, said lining baffle plate (80) is located on the said outer barrel member (66).
According to exemplary embodiment on the other hand, turbine comprises: compressor section; The turbine part, its operability is connected to said compressor section; And the combustion chamber assembly, it is communicated with said compressor section and said turbine segment fluid flow.Said combustion chamber assembly comprises: combustor outer casing, and it has first end; And the combustion chamber main body, it is arranged in the said combustor outer casing.Said combustion chamber main body is provided with combustion chamber lining, and said combustion chamber lining has and passes the first end section that the combustion chamber extends to the second end section.End cap assembly is installed in the said first end place of said combustor outer casing.Said end cap assembly comprises: end cap, by a plurality of fuel nozzles of said endcap support, and the water conservancy diversion sleeve pipe that between said end cap and said combustor outer casing, extends.Said water conservancy diversion sleeve pipe comprises the outer barrel member that extends around said a plurality of fuel nozzles.The said first end section of lining baffle arrangement barrel member and said combustion chamber lining outside said is on one of them.Said lining baffle plate comprises the scalariform lip portion, is used for holding another of said first end section of said outer barrel member and said combustion chamber lining, to form level and smooth substantially lining urceolus interface.Said lining baffle plate limits the axially-movable of said combustion chamber lining with respect to said outer barrel member.
Further comprise the containment member that is arranged on the level and smooth lining urceolus interface of said cardinal principle.
Further, said containment member is located on the said scalariform lip portion.
Further, said containment member in said scalariform lip office outside said barrel member radially extend.
Further, said containment member comprises lip ring.
Further, the level and smooth lining urceolus interface of said cardinal principle flows to the fluid stream of said end cap through said combustion chamber lining with adjustment through configuration and setting.
Further, said scalariform lip portion is through disposing and being provided with to impel laminar flow substantially to pass the level and smooth lining urceolus interface of said cardinal principle.
Further, said lining baffle plate is located on the said outer barrel member.
Another aspect according to exemplary embodiment; Disclose and a kind of end cap assembly is connected to the method for turbine combustion chamber shell, comprising: the outer barrel member that said end cap assembly is carried aligns with the combustion chamber lining that extend the combustion chamber in said combustor outer casing; With placing said outer barrel member and the said combustion chamber lining scalariform lip portion on one of them to insert another of said outer barrel member and said combustion chamber lining, with formation lining urceolus interface; And said end cap assembly is fixed to the turbine combustion chamber shell.
Further comprise the said lining urceolus interface of sealing.
Further, the said scalariform lip portion on one of being located in said outer barrel member and the said combustion chamber lining being inserted in said outer barrel member and the said combustion chamber lining another comprises compressing and is located at the seal on the said scalariform lip portion.
Further comprise and use said scalariform lip portion to limit said combustion chamber lining with respect to the axially-movable of said urceolus member.
Through following explanation and combine accompanying drawing can be well understood to more these with other advantages and characteristic.
Description of drawings
Claims among the present invention are pointed out in detail and have clearly been advocated the present invention.Through following explanation and combine accompanying drawing can be well understood to above-mentioned and other characteristics and advantage of the present invention, in the accompanying drawings:
Fig. 1 is the partial section according to the turbine of exemplary embodiment, and wherein this turbine comprises the combustion chamber assembly with lining baffle plate;
Fig. 2 is according to the fragmentary, perspective view of the end cap assembly part of the combustion chamber assembly of exemplary embodiment, is used to illustrate the lining baffle plate;
Fig. 3 is the detail perspective view of lining baffle plate shown in Figure 2; And
Fig. 4 is the partial plan layout of lining baffle plate shown in Figure 2.
Specific embodiment partial reference accompanying drawing is introduced each item embodiment of the present invention and advantage and characteristic with way of example.
The parts label list:
Label Parts Label Parts
2 Turbine 4 Compressor section
6 The turbine part 10 The combustion chamber assembly
14 Compressor air exhausting unit 16 Transition piece
20 Combustor outer casing 22 First end
30 The combustion chamber main body 34 Combustion chamber lining
37 The first end section 38 The second end section
40 The combustion chamber 50 End cap assembly
52 End cap 53 Front shell
56 The combustion chamber 60 Main body
62，63 Flange 66 Outer barrel member
67 Main element 68 The first end section
69 The second end section 80 The lining baffle plate
83 The scalariform lip portion 86 The first wall part
87 Second wall part 90 Lining urceolus interface
94 Containment member 96 Seal section
99 Lip ring
The specific embodiment
Employed term " axially " is meant the direction and the orientation of the center longitudinal axis extension that is parallel to the combustion chamber assembly substantially among the present invention.Employed term " radially " is meant the direction and the orientation of the center longitudinal axis extension that is orthogonal to said combustion chamber assembly substantially among the present invention.Among the present invention employed term " upper reaches " and " downstream " be meant the axial flow of extending with respect to the center longitudinal axis of said combustion chamber assembly to direction and orientation.
Consult Fig. 1, represent with 2 usually according to the turbine of exemplary embodiment.Turbine 2 is connected to the compressor section 4 of turbine part 6 with comprising operability.Combustion chamber assembly 10 is communicated with compressor section 4 fluids through turbine part 6.Compressor section 4 comprises compressor air exhausting unit 14, and its air that compressor is discharged is sent in the combustion chamber assembly 10.To more fully discuss like hereinafter, the part of air that compressor is discharged can be used for each parts of cooling combustion chamber assembly 10, and another part of the compressor air of discharging and fuel mix to be forming flammable mixture, thereby burning is with formation hot gas.Assembly 10 gets into turbine part 6 to said hot gas from the combustion chamber through transition piece 16.Turbine part 6 becomes the mechanical rotation ability with the thermal power transfer in the said hot gas, thereby is a plurality of systems, and for example generator, pump and homogeneous system provide power.
According to example shown property embodiment, combustion chamber assembly 10 comprises combustor outer casing 20, and it has first end 22 that extends to second end (not shown).Combustion chamber assembly 10 comprises combustion chamber main body 30, and it is arranged in the combustor outer casing 20.Said combustion chamber main body 30 is provided with combustion chamber lining 34.Said combustion chamber lining 34 comprises and passes the first end section 37 that combustion chamber 40 extends to second end section 38.Combustion chamber assembly 10 also comprises end cap assembly 50, and it is installed in first end, 22 places of said combustor outer casing 20.End cap assembly 50 comprises end cap 52 and front shell 53.
End cap 52 support arrangement circularize a plurality of fuel nozzles of array, and a fuel nozzle in said a plurality of fuel nozzles is represented with 56.Fuel nozzle 56 is from end cap 52 40 extensions towards the combustion chamber.As specifying fully hereinafter, fuel and air forwardly mix to form flammable mixture in the housing 53, and said flammable mixture leads to fuel nozzle 56.Said flammable mixture burns in combustion chamber 40 and expands, and leads to turbine part 6 through transition piece 16 subsequently.Front shell 53 comprises main body 60, and it is connected to first flange 62 of first end 22 of combustor outer casing 20 with having operability, and second flange 63 that end cap 52 is installed.Said front shell 53 comprises outer barrel member 66, and it extends around fuel nozzle 56, and partly is provided with passage (not separate marking), is used for the air that compressor is discharged is transported to end cap 52 from combustor outer casing 20.
According to an exemplary embodiment, outer barrel member 66 comprises main element 67, and it has the first end section 68 that extends to second end section 69.The first end section 37 of second end section 69 abuts combustor linings 34.In order to limit the axially-movable of combustion chamber lining 34, outer barrel member 66 comprises lining baffle plate 80.Said lining baffle plate 80 comprises the scalariform lip portion 83 at 69 places, second end section that are positioned at outer barrel member 66.Said scalariform lip portion 83 comprises the first wall part 86 and second wall part 87.First wall part 86 is radially extended from the center line (not separate marking) of main element 67 assembly 10 towards the combustion chamber.Second wall part 87 is offset from body parts 67 radially, and extend perpendicular to first wall part 86 substantially.
End cap assembly 50 is positioned on the combustor outer casing 20, and outer barrel member 66 aligns with combustion chamber lining 34.End cap assembly 50 is installed also and is fixed to combustor outer casing 20, and scalariform lip portion 83 extends in the first end section 37 of combustion chamber lining 34, to form level and smooth substantially lining urceolus interface 90.In this arranges, the axially-movable of first wall part 86 restriction combustion chamber linings 34, scalariform lip portion 83 forms seamlessly transitting between burning lining 34 and the outer barrel member 66 simultaneously.Between burning lining 34 and the outer barrel member 66 laminar flow substantially that seamlessly transits the air that impels the compressor discharge of formation along the combustion chamber main body 30 pass through from compressor section 4.Therefore, lining baffle plate 80 not only retrains or limits 34 axially-movables of burning lining, also can adjust the fluid that flows to fuel nozzle 56.
Further according to said exemplary embodiment, lining baffle plate 80 has containment member 94, and it comprises and be fixed to second wall part 87 to form a plurality of seal sections of lip ring 99 that a seal section in said a plurality of seal sections is represented with 96.Containment member 94 limit fluid stream flows towards end cap 52 through burning lining 34, overflows to avoid said fluid flow to cross lining urceolus interface 90.That is to say that when outer barrel member 66 inserted burning lining 34, first end section 37 compression seal members 84 were to form more firm sealing on lining urceolus interface 90.To this, should be appreciated that be on the outer barrel member 66 although be depicted as, scalariform lip portion 83 optionally is formed on the first end section 37 of burning lining 34.In addition, form containment member, should be appreciated that, also can use the continuous seal part although be depicted as by a plurality of seal sections.
Although the present invention only combines the embodiment of limited quantity to come to introduce in detail the present invention, should be appreciated that these embodiment that the present invention is not limited to disclosed.On the contrary, the present invention can be through revising variation, change, replacement or the equivalent arrangements not introduce before containing all but to be consistent with the spirit and scope of the present invention.In addition,, should be appreciated that each side of the present invention can only comprise some embodiment in the previous embodiment although introduced various embodiment of the present invention.Therefore, the present invention should not be regarded as the restriction that receives aforementioned specification, and it only receives the restriction of appended claims scope.

Claims (8)

1. a turbine combustion chamber assembly (10) comprising:
Combustor outer casing (20), it has first end (22);
Combustion chamber main body (60), it is arranged in the said combustor outer casing (20), and said combustion chamber main body (60) is provided with combustion chamber lining, and said combustion chamber lining has and passes the first end section (37) that combustion chamber (40) extends to second end section (38);
End cap assembly; It is installed in said first end (22) of said combustor outer casing (20); A plurality of fuel nozzles that said end cap assembly (50) comprises end cap (52), supported by said end cap (52); And the outer barrel member (66) that between said end cap (52) and said combustor outer casing (20), extends, said outer barrel member (66) extends around said a plurality of fuel nozzles; And
Lining baffle plate (80); It is arranged in said outer barrel member (66) and said combustion chamber lining first end section (37) on one of them; Said lining baffle plate (80) comprises scalariform lip portion (83); Be used for holding another of said outer barrel member (66) and said combustion chamber lining first end section (37), to form level and smooth substantially lining urceolus interface (90), the said combustion chamber lining of said lining baffle plate (80) restriction is with respect to the axially-movable of said outer barrel member (66).
2. turbine combustion chamber assembly according to claim 1 (10) further comprises: be arranged in the containment member (94) on the level and smooth lining urceolus interface (90) of said cardinal principle.
3. turbine combustion chamber assembly according to claim 2 (10), wherein said containment member (94) is located on the said scalariform lip portion (83).
4. turbine combustion chamber assembly according to claim 2 (10), wherein said containment member (94) locate in said scalariform lip portion (83) that barrel member (66) radially extends outside said.
5. turbine combustion chamber assembly according to claim 2 (10), wherein said containment member (94) comprises lip ring (99).
6. turbine combustion chamber assembly according to claim 1 (10), the level and smooth lining urceolus interface (90) of wherein said cardinal principle flows to the fluid stream of said end cap (52) through said combustion chamber lining with adjustment through configuration and setting.
7. turbine combustion chamber assembly according to claim 6 (10), wherein said scalariform lip portion (83) is through disposing and being provided with to impel laminar flow substantially to pass the level and smooth lining urceolus interface (90) of said cardinal principle.
8. turbine combustion chamber assembly according to claim 1 (10), wherein said lining baffle plate (80) is located on the said outer barrel member (66).
CN2012101917216A 2011-06-01 2012-06-01 Turbomachine combustor assembly Pending CN102809174A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/150,319 US20120304655A1 (en) 2011-06-01 2011-06-01 Turbomachine combustor assembly including a liner stop
US13/150,319 2011-06-01

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Publication Number Publication Date
CN102809174A true CN102809174A (en) 2012-12-05

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CN2012101917216A Pending CN102809174A (en) 2011-06-01 2012-06-01 Turbomachine combustor assembly

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US (1) US20120304655A1 (en)
EP (1) EP2530385A2 (en)
CN (1) CN102809174A (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9650958B2 (en) * 2014-07-17 2017-05-16 General Electric Company Combustor cap with cooling passage

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040025512A1 (en) * 2002-01-29 2004-02-12 General Electric Company Performance enhanced control of DLN gas turbines
US20040154303A1 (en) * 2003-02-10 2004-08-12 Mitchell Krista Anne Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor
CN1576698A (en) * 2003-07-02 2005-02-09 通用电气公司 Methods and apparatus for operating gas turbine engine combustors
CN101368738A (en) * 2007-08-14 2009-02-18 通用电气公司 Combustion liner stop in a gas turbine
US20100180602A1 (en) * 2009-01-16 2010-07-22 Thomas Edward Johnson Combustor assembly and cap for a turbine engine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7284378B2 (en) * 2004-06-04 2007-10-23 General Electric Company Methods and apparatus for low emission gas turbine energy generation

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040025512A1 (en) * 2002-01-29 2004-02-12 General Electric Company Performance enhanced control of DLN gas turbines
US20040154303A1 (en) * 2003-02-10 2004-08-12 Mitchell Krista Anne Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor
CN1576698A (en) * 2003-07-02 2005-02-09 通用电气公司 Methods and apparatus for operating gas turbine engine combustors
CN101368738A (en) * 2007-08-14 2009-02-18 通用电气公司 Combustion liner stop in a gas turbine
US20100180602A1 (en) * 2009-01-16 2010-07-22 Thomas Edward Johnson Combustor assembly and cap for a turbine engine

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EP2530385A2 (en) 2012-12-05
US20120304655A1 (en) 2012-12-06

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Application publication date: 20121205