EP2657609A1 - Structure de montage de bouchon de chambre de combustion pour moteur de turbine - Google Patents

Structure de montage de bouchon de chambre de combustion pour moteur de turbine Download PDF

Info

Publication number
EP2657609A1
EP2657609A1 EP13164743.0A EP13164743A EP2657609A1 EP 2657609 A1 EP2657609 A1 EP 2657609A1 EP 13164743 A EP13164743 A EP 13164743A EP 2657609 A1 EP2657609 A1 EP 2657609A1
Authority
EP
European Patent Office
Prior art keywords
combustor cap
support strut
combustor
barrel flange
leading edge
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Withdrawn
Application number
EP13164743.0A
Other languages
German (de)
English (en)
Inventor
Christopher Paul Keener
Jason Stewart
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 EP2657609A1 publication Critical patent/EP2657609A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances

Definitions

  • a combustor for a turbine engine used in the power generation industry can include a combustor cap that is mounted adjacent a forward end of the combustor.
  • a plurality of fuel nozzles are typically mounted to an end cover and pass through the combustor cap. Compressed air flows around the exterior periphery of the combustor cap, makes a 180° turn, and then flows through the fuel nozzles, where the air is mixed with fuel. The air-fuel mixture is then ignited downstream from the combustor cap.
  • FIGS 1 and 2 illustrate a typical background art combustor cap assembly mounted in a combustor.
  • a combustor cap 110 having openings 112 to receive a plurality of fuel nozzles is mounted to a combustor cap barrel flange 118 by a plurality of A-frame spacers 116.
  • the A-frame spacers 116 are typically formed from flat metal strips. Center portions of the A-frame spacers are mounted to the inner circumference of the combustor cap barrel flange 118, and ends of the A-frame spacers 116 are attached to the outer circumference 114 of the combustor cap 110.
  • the combustor cap barrel flange 118 includes a protruding flange 120.
  • the protruding flange 120 is mounted between a flange 106 of an outer casing 105 and a flange 132 of a forward casing 130.
  • a flow sleeve 102 is positioned inside the outer casing 106.
  • a combustor liner 104 is mounted concentrically inside the flow sleeve 102.
  • a forward end of the combustor liner 104 engages a hula seal 117 on the exterior circumference 114 of the combustor cap 110.
  • a flow of compressed air from the compressor section of the turbine engine flows through the annular space 103 between the flow sleeve 102 and the combustor liner 104, as illustrated by the arrows appearing in Figure 1 .
  • This flow of compressed air also flows through the annular space between the outer circumference 114 of the combustor cap 110 and the inner circumference of the combustor cap barrel flange 118.
  • the A-frame spacers 116 are positioned between the outer circumference 114 of the combustor cap 110 and the inner circumference of the combustor cap barrel flange 118, the A-frame spacers 116 tend to impede and/or disrupt the flow of compressed air, resulting in flow losses and separation.
  • the combustor cap design illustrated in Figure 1 can result in a step located between the outer circumferential surface of the combustor cap barrel flange 118 and the inner circumferential surface of the forward casing 130.
  • This step can cause disturbances in the flow of compressed air and a low pressure cavity 133 in the volume between the outer circumferential surface of the combustor cap barrel flange 118 and the inner circumferential surface of the forward casing 130.
  • the disturbances caused by this step can provide a path for fuel to migrate upstream from the fuel peg 135.
  • the invention may be embodied in a combustor cap assembly for a turbine engine that includes a generally cylindrical combustor cap configured to receive at least one fuel nozzle, a generally cylindrical combustor cap barrel flange that surrounds an outer circumference of the combustor cap, and a plurality of support struts that mount the combustor cap to the combustor cap barrel flange.
  • the support struts extend between the outer circumference of the combustor cap and an inner circumference of the combustor cap barrel flange.
  • An interior passageway extends through an interior of each support strut.
  • the invention may be embodied in a support strut that is configured to mount a combustor cap to a combustor cap barrel flange of a combustor of a turbine engine.
  • the support strut includes a main body having an inner end that is configured to be attached to the outer circumference of a combustor cap and an outer end that is configured to be attached to an inner circumference of a combustor cap barrel flange.
  • an interior passageway extends through the main body between an entrance aperture and an exit aperture.
  • FIGs 3 and 4 illustrate a support strut 160 which can be used to mount a combustor cap to a combustor cap barrel flange.
  • the support strut 160 replaces the A-frame spacers 116 used for this purpose in the background art combustor cap assembly illustrated in Figures 1 and 2 .
  • the support strut 160 has an airfoil shape, with a rounded leading edge 161 and a tapered trailing edge 163.
  • an interior passageway extends through the interior of the support strut 160 between an entrance aperture 162 and an exit aperture 164.
  • Figure 4 which is a cross-sectional view of a support strut 160 attached to a combustor cap barrel flange 150, illustrates that the inner end 166 and outer end 168 of the support strut 160 are substantially parallel to one another. In alternate embodiment, however, the inner and outer ends could be angled relative to one another. In some embodiments, the leading edge 161 and trailing edge 163 of each support strut 160 may be angled with respect to the inner end 166 and outer end 168.
  • Figure 4 also illustrates that an interior passageway 165 passes between an entrance aperture 162 and an exit aperture 164 of the support strut. The exit aperture 164 is in communication with a vent aperture 152 in the combustor cap barrel flange 150. As a result, air entering the entrance aperture 162, flowing through the interior passageway 165 and exiting the exit aperture 164 can pass through the vent aperture 164 of the combustor cap barrel flange 150.
  • Figure 5 illustrates how a plurality of support struts 160 are used to mount a combustor cap 110 to a combustor cap barrel flange 150.
  • Inner ends 166 of each support strut 160 are mounted to an exterior circumference 114 of the combustor cap 110.
  • Outer ends 168 of each support strut 160 are mounted to an interior circumferential surface 154 of the combustor cap barrel flange 150.
  • the inner and outer ends of the support struts 160 may be integral to the combustor cap 110 and combustor cap barrel flange 150, respectively.
  • FIG. 5 presents a view which shows the leading edges of the support struts 160. As a result, one can see the entrance apertures 162 on the leading edges of the support struts 160.
  • Figure 6 illustrates a side view of the combustor assembly, which shows how the support struts 160 are mounted between the combustor cap 110 and the combustor cap barrel flange 150.
  • Figure 6 also illustrates that the leading edge 161 of the support struts are positioned so that the flow of compressed air exiting the annular space 103 between the flow sleeve 102 and the combustor liner 104 impinges directly on the leading edges 161 of the support struts 160.
  • the airfoil shape of the support struts 160 also help to minimize any flow losses that result from the flow of compressed air impinging on the structure used to attach the combustor cap 110 to the combustor cap barrel flange 150. Another benefit of the airfoil shape is that it helps to minimize wakes if the flow of compressed air has a tangential component (swirl). If the air coming from the annular space 103 is swirling, the background art A-frames tended to cause a large wake, as they essentially act like flat plates with an angle of attack. In contrast, when airfoil shapes are used for the support struts the air will tend to stay attached to the airfoil in moderate angles of attack (swirl) thereby minimizing wakes or flow deficits from the structure.
  • Figure 7 illustrates an alternate embodiment of a support strut 190 that can be used to attach a combustor cap 110 to a combustor cap barrel flange 150.
  • the interior passageway 175 makes a smooth curve between the entrance aperture 162 on the leading edge 161 of the support strut and the exit aperture 164 that is in communication with the vent aperture 152 in the combustor cap barrel flange 150.
  • the smoothly curved interior passageway 175 also serves to minimize flow losses and maximize the flow of air that is used to purge the dead cavity.
  • the entrance aperture of a support strut could be located on portions of the sidewall of the support strut other than the leading edge.
  • the entrance aperture could be located on a portion of the sidewall between the leading and trailing edges.
  • multiple entrance apertures could be provided on multiple portions of the sidewall of the support strut.
  • multiple entrance apertures could be formed on the leading edge 161 of a support strut.
  • all of the entrance apertures would lead to the same interior passageway.
  • each entrance aperture could lead to a separate interior passageway.
  • the exit aperture is located on the outer end of the support struts. In alternate embodiments, the exit aperture could be located in different locations. Also, multiple exit apertures could be provided.
  • multiple interior passageways may be provided.
  • the support struts have a cross-sectional shape with a rounded leading edge and a tapered trailing edge.
  • the support strut could have alternate cross-sectional shapes.
  • the support struts could have a rectangular cross-sectional shape, with or without rounded edges.
  • the support struts could have a circular or oval cross-sectional shape. Still other cross-sectional shapes are also possible, depending on design considerations.
  • leading and trailing edges of the support struts were angled with respect to the inner and outer ends.
  • the inner and outer ends could form right angles with the leading and trailing edges of the support struts.
  • the leading and trailing edges may be angled such that the inner ends of the support struts extend further rearward than the outer ends.
  • Figure 8 illustrates another embodiment of a combustor assembly where support struts 160 are mounted between a combustor cap 110 and a combustor cap barrel flange 150.
  • a slot 137 is cut in the forward casing 130, and the combustor cap barrel flange 150 is mounted in the slot 137.
  • a cavity 139 is formed between the inner circumference of the slot 137 and the outer circumference of the combustor cap barrel flange 150.
  • a portion of the compressed air exiting the annular space 103 flows into the entrance aperture of the support strut 160, through the interior passageway, out the exit aperture of the support strut 160, and then through a vent aperture in the combustor cap barrel flange 150 and into the cavity 139, as illustrated by the arrows in Figure 6 .
  • a flow of air continuously purges the cavity 139.
  • the flow of air exiting the cavity 139 through the gap 151 prevents fuel delivered from a downstream fuel peg 135 from migrating upstream into the location adjacent the trailing edges of the support struts 160.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP13164743.0A 2012-04-23 2013-04-22 Structure de montage de bouchon de chambre de combustion pour moteur de turbine Withdrawn EP2657609A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/453,320 US20130276449A1 (en) 2012-04-23 2012-04-23 Combustor cap mounting structure for a turbine engine

Publications (1)

Publication Number Publication Date
EP2657609A1 true EP2657609A1 (fr) 2013-10-30

Family

ID=48139843

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13164743.0A Withdrawn EP2657609A1 (fr) 2012-04-23 2013-04-22 Structure de montage de bouchon de chambre de combustion pour moteur de turbine

Country Status (5)

Country Link
US (1) US20130276449A1 (fr)
EP (1) EP2657609A1 (fr)
JP (1) JP2013224659A (fr)
CN (1) CN103375802A (fr)
RU (1) RU2013118438A (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150068212A1 (en) * 2012-04-19 2015-03-12 General Electric Company Combustor liner stop
US11629857B2 (en) 2021-03-31 2023-04-18 General Electric Company Combustor having a wake energizer
CN113739203B (zh) * 2021-09-13 2023-03-10 中国联合重型燃气轮机技术有限公司 用于燃烧器的罩帽组件
CN115307179B (zh) * 2022-08-15 2023-08-01 北京航空航天大学 一种弯曲支板双凹腔一体化加力燃烧室

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1271057A2 (fr) * 2001-06-29 2003-01-02 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine à gaz
EP2208933A2 (fr) * 2009-01-16 2010-07-21 General Electric Company Ensemble de chambre de combustion et dôme pour moteur de turbine
CH702684A2 (de) * 2010-02-15 2011-08-15 Gen Electric Brennkammer.
EP2520864A2 (fr) * 2011-05-03 2012-11-07 General Electric Company Injecteur de carburant et plaque de support

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1271057A2 (fr) * 2001-06-29 2003-01-02 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine à gaz
EP2208933A2 (fr) * 2009-01-16 2010-07-21 General Electric Company Ensemble de chambre de combustion et dôme pour moteur de turbine
CH702684A2 (de) * 2010-02-15 2011-08-15 Gen Electric Brennkammer.
EP2520864A2 (fr) * 2011-05-03 2012-11-07 General Electric Company Injecteur de carburant et plaque de support

Also Published As

Publication number Publication date
RU2013118438A (ru) 2014-10-27
CN103375802A (zh) 2013-10-30
JP2013224659A (ja) 2013-10-31
US20130276449A1 (en) 2013-10-24

Similar Documents

Publication Publication Date Title
US8371123B2 (en) Apparatus for conditioning airflow through a nozzle
ES2298972T3 (es) Difusor para camara de combustion anular, y camara de combustion y turbopropulsor comprendiendo dicho difusor.
EP2657609A1 (fr) Structure de montage de bouchon de chambre de combustion pour moteur de turbine
EP2256299A3 (fr) Déflecteur pour ensemble d'anneau d'aube de moteur de turbine à gaz
EP2660520A3 (fr) Système de prémélange air/carburant pour moteur à turbine
US10392975B2 (en) Exhaust gas diffuser with main struts and small struts
US8579211B2 (en) System and method for enhancing flow in a nozzle
RU2007124389A (ru) Конструкция камеры сгорания для газотурбинного двигателя, имеющей дефлектор с выступающей кромкой, камера сгорания газотурбинного двигателя, содержащая вышеуказанную конструкцию, и газотурбинный двигатель
US20140260283A1 (en) Gas turbine engine exhaust mixer with aerodynamic struts
EP2806217B1 (fr) Moteurs à turbine à gaz avec ensembles d'injecteur de carburant
JP7237444B2 (ja) 排気ディフューザ
US20130160452A1 (en) Aerodynamic shroud for the back of a combustion chamber of a turbomachine
EP2584155A2 (fr) Diffuseur de gaz d'échappement
RU2015150519A (ru) Дренажная продувка наружной камеры предварительного смешивания
RU2011141837A (ru) Камера сгорания турбомашины, содержащая улучшенные средства питания воздухом
EP2628897A2 (fr) Système de turbine à gaz
CA2606580A1 (fr) Plenum d'ouie d'entree ameliore pour turbine a gaz
US10151325B2 (en) Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same
EP3182015B1 (fr) Chambre de combustion et turbine à gaz la comprenant
JP5816264B2 (ja) フロースプリッタを備える圧縮器排出ケーシングを有するガスタービンエンジン
US20170363290A1 (en) Air intake ring for a turbomachine combustion chamber injection system and method of atomizing fuel in an injection system comprising said air intake ring
WO2018205889A9 (fr) Pelle de retournement d'extrémité de tête pour une turbine à gaz
CN115127125A (zh) 耐沙尘燃烧室火焰筒及含其的燃烧室、发动机
CN106471258B (zh) 包括扩压器相对于燃烧室的方位角定位的航空器发动机
CN107620984B (zh) 燃气轮机的燃料喷嘴

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20140501