CN103032901A - Forward casing with a circumferential sloped surface and a combustor assembly including same - Google Patents

Forward casing with a circumferential sloped surface and a combustor assembly including same Download PDF

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Publication number
CN103032901A
CN103032901A CN2012103671244A CN201210367124A CN103032901A CN 103032901 A CN103032901 A CN 103032901A CN 2012103671244 A CN2012103671244 A CN 2012103671244A CN 201210367124 A CN201210367124 A CN 201210367124A CN 103032901 A CN103032901 A CN 103032901A
Authority
CN
China
Prior art keywords
procapsid
circumferential
burner assembly
angled surfaces
fuel
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
CN2012103671244A
Other languages
Chinese (zh)
Inventor
B.T.奥弗比
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 CN103032901A publication Critical patent/CN103032901A/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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

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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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

A forward casing (300) used in a combustor assembly for a turbine engine includes a circumferential sloped surface (368) which reduces the total interior volume within the forward casing (300). The circumferential sloped surface (368) can be flat or concave shaped.

Description

Procapsid and the burner assembly that comprises this procapsid with circumferential angled surfaces
Technical field
The present invention relates generally to the procapsid and the burner assembly that comprises this procapsid with circumferential angled surfaces.
Background technology
The burner assembly mixing compressed air and the fuel that are used for turbogenerator, and then air-fuel mixture is lighted to produce the expansion burning gases that drive turbine.The partial sectional view of burner assembly shown in Figure 1.
As shown in Figure 1, burner assembly comprises back casing 130, and back casing 130 has the combustion liner 110 that is installed on wherein.Flow sleeve 120 also is installed in the back casing 130.
Procapsid 160 is attached to the front end of back casing 130.Rear flange 167 on the procapsid 160 is used for procapsid 160 is attached to back casing 130.Then, end cap 170 is attached to the front end of procapsid 160 via front flange 165.
Cap assembly 140 is installed on the rear side of procapsid 160.A plurality of cylindricality installation elements 142 in the cap assembly 140 are admitted corresponding fuel nozzle 150, and fuel nozzle 150 is transported to fuel in the compressed air stream.
As by shown in the arrow that occurs among Fig. 1, compressed air passes and is formed at the annular space between combustion liner 110 and the flow sleeve 120 and is introduced in the burner assembly.This annular space extends past end cap 140 and in the inside of procapsid 160.Also as by shown in the arrow among Fig. 11, introduce compressed air in the procapsid 160 then turn to 180 degree so that it can be flowed through fuel nozzle 150, be transported in the compressed air stream at this fuel.Then fuel-air mixture is transported in the inside 106 of combustion liner 110, and at this, it is lighted and is formed for driving the expanding gas of turbine.
Also as shown in Figure 1, circumferential fuel service duct 162 is located at the exterior circumferential of procapsid 160.A plurality of fuel nozzles 164 that radially extend extend internally from the inwall of procapsid 160.Fuel nozzle 164 operatively is connected to circumferential fuel passage 162, so that the fuel in the circumferential fuel passage 162 can be transported in the compressed air that flows through the fuel nozzle 164 that radially extends.
The geometry of the internal volume of procapsid 160 can cause resonance to appear in the compressed air.The resonance that yet is known as " dynamically " do not expect, and may damage the member of burner assembly, and the gross efficiency that reduces turbogenerator.A kind of mode that reduces or eliminates the resonance that produces in procapsid is the inside that reduces in the procapsid 160.
Fig. 2 illustrates and above is combined similarly another burner assembly of burner assembly that Fig. 1 describes.Yet in the embodiment shown in Figure 2, insert 180 is installed in the procapsid 160.A plurality of securing members 183 are used for insert 180 is attached to the inner peripheral surface of procapsid 160.Insert 180 comprises the surface 182 of inclination or taper, and it is used for reducing the interior internal volume of procapsid.As noted above, the internal volume of procapsid 160 this reduces can help to reduce or eliminate the resonance of not expecting.
Because insert 180 is attached to procapsid 160 by securing member 183, so one or more in the securing member 183 are may be in gas turbine operating period loosening or disconnect.If this thing happens, securing member 183 might be passed combustion liner 110 by purging and in the turbine section of turbogenerator so.In case be in the turbine section, securing member 183 will affect rotary turbine blade and fixed stator blade, and this might cause turbogenerator badly damaged, thereby need hard stop and maintenance.
Although may become flexible the only very little possibility of existence for one of securing member 183 that insert 180 is attached to procapsid 160, if this thing happens, the infringement amount that then will occur is huge and very expensive.It also will cause the shutdown of turbogenerator, and this will seriously affect the ability that TRT produces enough electric power.
Summary of the invention
Disclose a kind of burner assembly for turbogenerator, this burner assembly comprises: end cap; Back casing, it has the combustion liner that is installed on wherein; Cap assembly, it is installed between procapsid and the end cap; At least one fuel nozzle, it is installed on the cap assembly; And the integral type procapsid, it is installed between back casing and the end cap, and wherein, procapsid comprises circumferential angled surfaces, and this circumferential angled surfaces slopes inwardly to the end cap side of procapsid from the back casing side.
Description of drawings
Fig. 1 is the cutaway view of a part of the burner assembly of turbogenerator;
Fig. 2 is the cutaway view of a part that comprises the burner assembly of the turbogenerator that is installed on the removable insert in the procapsid;
Fig. 3 is the fragmentary, perspective view that comprises the integral type procapsid of inclination peripheral surface;
Fig. 4 is the partial sectional view of burner assembly that comprises the turbogenerator of integral type procapsid shown in Figure 3; And
Fig. 5 is the partial sectional view of a part of the burner assembly of turbogenerator, and it comprises the integral type procapsid as shown in Figure 3 with recessed circumferential angled surfaces.
Reference numeral:
The inside of 106 combustion liners
110 combustion liners
120 flow sleeves
130 back casings
140 cap assemblies
142 installation elements
150 fuel nozzles
160 procapsids
162 fuel feed passage
164 fuel nozzles
165 front flanges
167 rear flanges
170 end caps
180 removable inserts
182 conical surfaces
More than 183 securing member
300 procapsids
362 fuel channels
364 fuel nozzles
365,367 mounting flanges
366 ends
368 inclined surfaces
568 inclined surfaces.
The specific embodiment
Owing to all reasons of explaining in the part of background technology above, removable insert is attached to that the procapsid of compressor assembly is inner may be dangerous, may fluff moving and be inhaled into the turbine section of turbogenerator because be used for the securing member of this purpose.Owing to these reasons, can be surpassed by contingent potential damage by using the resulting benefit of insert.
Fig. 3 illustrates the new procapsid for the burner assembly of turbogenerator.Procapsid 300 comprises the substantially main body of cylindricality, and it is with the rear mounting flange 367 of the first end that is formed at cylindrical bodies.Rear mounting flange 367 is used for procapsid 300 is attached to the back casing of burner assembly.In addition, be positioned at the end cap that the front mounting flange 365 of the second end of cylindrical bodies substantially is used for procapsid 300 is attached to burner assembly.Procapsid 300 also comprises circumferential fuel passage 362, and it is to a plurality of fuel nozzle that extends radially inwardly 364 feed fuels.
Procapsid shown in Figure 3 also comprises circumferential angled surfaces 368, and its front side towards cylindrical bodies slopes inwardly.Then the end 366 of radially extending extends back to front mounting flange 365 from the smallest diameter portion of circumferential angled surfaces 368.
Procapsid with circumferential angled surfaces as shown in Figure 3 provides the benefit of removable insert 180 shown in Figure 2.Particularly, circumferential angled surfaces 368 has reduced total internal volume of procapsid, to help to reduce or elimination otherwise the generable resonance of not expecting.Yet, because circumferential angled surfaces 368 is the integral part of procapsid 300, so securing member can not fluff moving and turbogenerator is caused damage.
Fig. 4 illustrates the partial sectional view of a part of the burner assembly of the integral type procapsid that has as shown in Figure 3.As by among Fig. 4 shown in the arrow, the compressed air that enters procapsid will be by circumferential angled surfaces 368 deflections of integral type procapsid 300, with help to make the compressed air circulation to, but so that its reverse directions.In addition, as shown in Figure 4, circumferential angled surfaces 368 is used for reducing the interior internal volume of procapsid.
Fig. 5 illustrates another cutaway view that comprises with the part of the burner assembly of the integral type procapsid of circumferential angled surfaces 568.In this embodiment, circumferential angled surfaces 568 has concave shape.The concave shape of circumferential angled surfaces 568 can help better to make compressed air circulation to so that it can be in procapsid reverse directions.
Although in conjunction with thinking that at present the most practical and preferred embodiment described the present invention, but should be appreciated that, the present invention is not limited to the disclosed embodiments, on the contrary, the invention is intended to contain various modifications and equivalent arrangements included in the spirit and scope of the appended claims.

Claims (7)

1. burner assembly that is used for turbogenerator comprises:
End cap;
Back casing, it has the combustion liner that is installed on wherein;
Cap assembly, it is installed between described procapsid and the described end cap;
At least one fuel nozzle, it is installed on the described cap assembly; And
The integral type procapsid, it is installed between described back casing and the described end cap, and wherein, described procapsid comprises circumferential angled surfaces, and described circumferential angled surfaces slopes inwardly to the end cap side of described procapsid from described back casing side.
2. burner assembly according to claim 1 is characterized in that, described integral type procapsid comprises the circumferential fuel passage, and described circumferential fuel passage extends around the outside of described procapsid.
3. burner assembly according to claim 2, it is characterized in that, also comprise a plurality of fuel nozzles, its inwall from described procapsid extends radially inwardly, and operatively be connected to described circumferential fuel passage, so that the fuel in the described circumferential fuel passage is fed in described a plurality of fuel nozzle.
4. burner assembly according to claim 3 is characterized in that, the circumferential angled surfaces of described integral type procapsid is positioned on the end cap side of described a plurality of fuel nozzles.
5. burner assembly according to claim 1 is characterized in that, described circumferential angled surfaces is smooth, so that described circumferential angled surfaces is taper.
6. burner assembly according to claim 1 is characterized in that, described circumferential angled surfaces is recessed shape.
7. burner assembly according to claim 1 is characterized in that, described integral type procapsid comprises substantially cylindrical bodies, and wherein, described cardinal principle cylindrical bodies and described circumferential angled surfaces form a single body component.
CN2012103671244A 2011-10-04 2012-09-28 Forward casing with a circumferential sloped surface and a combustor assembly including same Pending CN103032901A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/252,525 US20130081397A1 (en) 2011-10-04 2011-10-04 Forward casing with a circumferential sloped surface and a combustor assembly including same
US13/252525 2011-10-04

Publications (1)

Publication Number Publication Date
CN103032901A true CN103032901A (en) 2013-04-10

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EP (1) EP2578945A2 (en)
CN (1) CN103032901A (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9400108B2 (en) * 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine

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US20020152751A1 (en) * 2001-04-19 2002-10-24 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
CN1401938A (en) * 2001-08-29 2003-03-12 株式会社日立制作所 Burner of gas turbine and its operation method
US6634175B1 (en) * 1999-06-09 2003-10-21 Mitsubishi Heavy Industries, Ltd. Gas turbine and gas turbine combustor
CN1497217A (en) * 2002-09-26 2004-05-19 通用电气公司 Cylinder combustion chamber irrelevant on dynamic
JP2006220350A (en) * 2005-02-10 2006-08-24 Hitachi Ltd Gas turbine equipment and its operation method
CN102192508A (en) * 2010-02-16 2011-09-21 通用电气公司 Axially staged premixed combustion chamber

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US4483149A (en) * 1982-05-20 1984-11-20 United Technologies Corporation Diffuser case for a gas turbine engine
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Publication number Priority date Publication date Assignee Title
CN2173906Y (en) * 1993-09-19 1994-08-10 汤民生 Inclined spiral-flow burner
US6634175B1 (en) * 1999-06-09 2003-10-21 Mitsubishi Heavy Industries, Ltd. Gas turbine and gas turbine combustor
US20020152751A1 (en) * 2001-04-19 2002-10-24 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor
CN1401938A (en) * 2001-08-29 2003-03-12 株式会社日立制作所 Burner of gas turbine and its operation method
CN1497217A (en) * 2002-09-26 2004-05-19 通用电气公司 Cylinder combustion chamber irrelevant on dynamic
JP2006220350A (en) * 2005-02-10 2006-08-24 Hitachi Ltd Gas turbine equipment and its operation method
CN102192508A (en) * 2010-02-16 2011-09-21 通用电气公司 Axially staged premixed combustion chamber

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EP2578945A2 (en) 2013-04-10
US20130081397A1 (en) 2013-04-04

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Application publication date: 20130410