WO2013157976A1 - Combustor liner stop - Google Patents

Combustor liner stop Download PDF

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Publication number
WO2013157976A1
WO2013157976A1 PCT/RU2012/000302 RU2012000302W WO2013157976A1 WO 2013157976 A1 WO2013157976 A1 WO 2013157976A1 RU 2012000302 W RU2012000302 W RU 2012000302W WO 2013157976 A1 WO2013157976 A1 WO 2013157976A1
Authority
WO
WIPO (PCT)
Prior art keywords
flow sleeve
plural
liner
spaced
cylindrical body
Prior art date
Application number
PCT/RU2012/000302
Other languages
French (fr)
Inventor
Leonid Yulevich GINESIN
Boris Borisovich SHERSHNYOV
Original Assignee
General Electric Company
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 Company filed Critical General Electric Company
Priority to US14/394,339 priority Critical patent/US20150068212A1/en
Priority to PCT/RU2012/000302 priority patent/WO2013157976A1/en
Publication of WO2013157976A1 publication Critical patent/WO2013157976A1/en

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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05002—Means for accommodate thermal expansion of the wall liner
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • 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
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • the invention relates to gas turbine combustor technology generally, and more specifically, to a combustor liner stop extending radially between the combustor liner and a surrounding flow sleeve.
  • a combustor liner (which encloses the combustion chamber), is surrounded by a flow sleeve providing an annular flow path therebetween. Compressor discharge air is supplied by to the annular flow path so as to provide air to the head end of the combustor liner for introduction into the combustion chamber with fuel supplied by one or more nozzles also attached to the head end of the combustor assembly.
  • a combustor liner stop is provided as part of the support assembly for the liner and also to restrict axial, angular and radial movement of the combustor liner relative to the flow sleeve.
  • the combustor liner stop is typically located within the flow annulus between the combustor and the flow sleeve thereby creating a flow disturbance within the flow annulus. It would therefore be desirable to provide a combustor liner flow stop that reduces flow disturbances and prevents flame-holding effects in the fuel- injection area for the combustion chambers, having fuel injections upstream of the combustor head-end (so-called "quaternary fuel injection").
  • a combustion liner comprising a substantially cylindrical body having forward and aft ends, the forward end provided with plural, circumferentially-shaped stops adapted for connection to a flow sleeve surrounding the substantially cylindrical body, each stop comprised of a radially-projecting strut having an end remote from the substantially-cylindrical body provided with a tab having a shape different than the strut.
  • a combustor liner and flow sleeve assembly comprising a combustor liner having an aft end and a forward end; a flow sleeve surrounding the combustor liner and defining an axially-extending, annular flow passage radially therebetween, the flow sleeve provided with plural slots at an aft end thereof; the combustor liner provided with plural, circumferentially-spaced stops extending radially outwardly and through respective ones of the plural slots in the flow sleeve; each strut provided with a tab that lies on an exterior surface of the flow sleeve, outside the annular flow passage.
  • a combustor liner and flow sleeve assembly comprising a combustor liner having an aft end and a forward end; and a flow sleeve surrounding the combustor liner and defining an axially-extending flow passage radially therebetween, the flow sleeve provided with plural slots at a forward end thereof; the combustor liner provided with plural, circumferentially-spaced airfoil- shaped struts slanted toward the aft end of the substantially-cylindrical body and extending radially outwardly and through respective ones of the plural slots in the flow sleeve; each of the plural circumferentially-spaced struts provided with a remote tab having a shape different than the strut and wherein said tab lies on an exterior surface of the flow sleeve.
  • FIG. 1 is a simplified cross-section showing a combustor liner and flow sleeve assembly incorporating a liner stop in accordance with an exemplary but nonlimiting embodiment of the invention
  • FIG. 2 is an enlarged perspective view of the liner stop shown in Fig. 1 , but with the flow sleeve removed;
  • FIG. 3 is an end view of the combustor liner head end, showing the circumferential location of plural liner stops in accordance with the exemplary but nonlimiting embodiment of the invention.
  • FIG. 4 is a partial perspective view of the forward end of the flow sleeve illustrating circumferentially-spaced slots which receive the liner stops shown in Figs. 2 and 3.
  • FIG. 1 illustrates a combustor liner-flow sleeve assembly 10 that includes a substantially cylindrical combustor liner body (or, simply, combustor liner) 12 having a forward end 14 and an aft end 16.
  • the combustor liner 12 is telescopically received in, or surrounded by, a substantially cylindrical flow sleeve 18, also having a forward end 20 and an aft end 22.
  • a combustor cap assembly also referred to as a combustion head-end, (not shown) supporting a plurality of nozzles is secured to the forward end of the combustor liner.
  • the aft ends 16, 22 of the combustor liner 12 and flow sleeve 18, respectively, are typically connected to a transition piece 24 and surrounding impingement sleeve 26.
  • compressor air enters an annular flow passage located radially between the impingement sleeve and the transition piece and flows through an axial extension of that passage (denoted as the radial passage 28) between the flow sleeve and the combustor liner. Air flowing through the passage 28 cools the combustor liner and is thereafter introduced into the combustion chamber 30 for mixing with the fuel supplied via the nozzles.
  • the transition piece 24 then carries the hot combustion gases to, for example, a first stage of a gas turbine in conventional fashion.
  • the forward end 14 of the combustor liner 12 is provided with plural liner stops 32 (Figs. 1 and 2). Three such stops 32 are illustrated in Fig. 3, substantially equally spaced about the circumference of the liner 12. It will be appreciated that the number of stops may vary but three is regarded as the minimum number needed to insure the required stability between the liner 12 and the flow sleeve 18.
  • each liner stop 32 includes a strut 34 and a tab or foot 36 at the remote or free end of the strut.
  • the strut 34 may be air-foil shaped and slanted in a radially-outward direction toward the aft end of the liner. The slanting of the strut and the airfoil shape of the strut minimize flow disruption in the air passing through the radial flow passage 28.
  • the tab or foot 36 has a shape different than the strut. In the exemplary embodiment, the tab 36 is shown to have a substantially rectangular block-like shape but the exact shape may vary.
  • the inner surface 38 is shaped to conform to the outer surface 40 of the flow sleeve 18.
  • the forward end 20 of the flow sleeve 18 is formed with slots 40 that open to the forward end of the flow sleeve.
  • the slots correspond in number and circumferential location to the liner stops 32.
  • the flow sleeve 18 is secured by sliding the flow sleeve into the combustor casing 35.
  • the foot 36 of each strut 34 is received radially outwardly of the respective slot 40 such that the enlarged foot 36 is outside the flow sleeve 18 and thus outside the annular flow path 28.
  • the width of each foot 36 is wider than the respective slot 40, preventing any radial dislodgement of the liner 12 relative to the flow sleeve 18.
  • a single or plural closure parts for example ring 42 (Fig. 4) may be bolted or otherwise suitably attached to the combustor case 35 and/or the forward end 20 of the flow sleeve 18, closing the open forward ends of the slots 40, and therefore precluding excessive axial displacement of the liner relative to the flow sleeve.
  • Some space is permitted, however, for accommodating differential thermal growth of the respective liner and flow sleeve components.

Abstract

A combustion liner includes a substantially cylindrical body having forward and aft ends, the forward end provided with plural, circumferentially-shaped stops adapted for connection to a flow sleeve surrounding the substantially cylindrical body. Each stop includes a radially-projecting strut having an end remote from the substantially-cylindrical body provided with a tab having a shape different than the strut. Each strut is received in a slot formed in the flow sleeve, with the tab on an exterior surface of the flow sleeve.

Description

COMBUSTOR LINER STOP BACKGROUND OF THE INVENTION
[ 0001 ] The invention relates to gas turbine combustor technology generally, and more specifically, to a combustor liner stop extending radially between the combustor liner and a surrounding flow sleeve.
[ 0002 ] In the construction of gas turbine combustor assemblies, and particularly in can-annular combustor arrangements, a combustor liner (which encloses the combustion chamber), is surrounded by a flow sleeve providing an annular flow path therebetween. Compressor discharge air is supplied by to the annular flow path so as to provide air to the head end of the combustor liner for introduction into the combustion chamber with fuel supplied by one or more nozzles also attached to the head end of the combustor assembly.
[ 0003 ] In various known arrangements, a combustor liner stop is provided as part of the support assembly for the liner and also to restrict axial, angular and radial movement of the combustor liner relative to the flow sleeve. In the known arrangements, the combustor liner stop is typically located within the flow annulus between the combustor and the flow sleeve thereby creating a flow disturbance within the flow annulus. It would therefore be desirable to provide a combustor liner flow stop that reduces flow disturbances and prevents flame-holding effects in the fuel- injection area for the combustion chambers, having fuel injections upstream of the combustor head-end (so-called "quaternary fuel injection").
BRIEF SUMMARY OF THE INVENTION
[ 0004 ] In accordance with an exemplary but nonlimiting embodiment, a combustion liner comprising a substantially cylindrical body having forward and aft ends, the forward end provided with plural, circumferentially-shaped stops adapted for connection to a flow sleeve surrounding the substantially cylindrical body, each stop comprised of a radially-projecting strut having an end remote from the substantially-cylindrical body provided with a tab having a shape different than the strut.
[ 0005 ] In another aspect, a combustor liner and flow sleeve assembly comprising a combustor liner having an aft end and a forward end; a flow sleeve surrounding the combustor liner and defining an axially-extending, annular flow passage radially therebetween, the flow sleeve provided with plural slots at an aft end thereof; the combustor liner provided with plural, circumferentially-spaced stops extending radially outwardly and through respective ones of the plural slots in the flow sleeve; each strut provided with a tab that lies on an exterior surface of the flow sleeve, outside the annular flow passage.
[ 0006 ] In still another aspect, a combustor liner and flow sleeve assembly comprising a combustor liner having an aft end and a forward end; and a flow sleeve surrounding the combustor liner and defining an axially-extending flow passage radially therebetween, the flow sleeve provided with plural slots at a forward end thereof; the combustor liner provided with plural, circumferentially-spaced airfoil- shaped struts slanted toward the aft end of the substantially-cylindrical body and extending radially outwardly and through respective ones of the plural slots in the flow sleeve; each of the plural circumferentially-spaced struts provided with a remote tab having a shape different than the strut and wherein said tab lies on an exterior surface of the flow sleeve.
[ 0007 ] The invention will now be described in detail in connection with the drawings identified below.
BRIEF DESCRIPTION OF THE DRAWINGS
[ 0008 ] FIG. 1 is a simplified cross-section showing a combustor liner and flow sleeve assembly incorporating a liner stop in accordance with an exemplary but nonlimiting embodiment of the invention; [ 0009 ] FIG. 2 is an enlarged perspective view of the liner stop shown in Fig. 1 , but with the flow sleeve removed;
[ 0010 ] FIG. 3 is an end view of the combustor liner head end, showing the circumferential location of plural liner stops in accordance with the exemplary but nonlimiting embodiment of the invention; and
FIG. 4 is a partial perspective view of the forward end of the flow sleeve illustrating circumferentially-spaced slots which receive the liner stops shown in Figs. 2 and 3.
DETAILED DESCRIPTION OF THE INVENTION [ 0011 ] FIG. 1 illustrates a combustor liner-flow sleeve assembly 10 that includes a substantially cylindrical combustor liner body (or, simply, combustor liner) 12 having a forward end 14 and an aft end 16. The combustor liner 12 is telescopically received in, or surrounded by, a substantially cylindrical flow sleeve 18, also having a forward end 20 and an aft end 22. Typically, a combustor cap assembly, also referred to as a combustion head-end, (not shown) supporting a plurality of nozzles is secured to the forward end of the combustor liner. The aft ends 16, 22 of the combustor liner 12 and flow sleeve 18, respectively, are typically connected to a transition piece 24 and surrounding impingement sleeve 26. In typical can-annular combustor arrangements, compressor air enters an annular flow passage located radially between the impingement sleeve and the transition piece and flows through an axial extension of that passage (denoted as the radial passage 28) between the flow sleeve and the combustor liner. Air flowing through the passage 28 cools the combustor liner and is thereafter introduced into the combustion chamber 30 for mixing with the fuel supplied via the nozzles. The transition piece 24 then carries the hot combustion gases to, for example, a first stage of a gas turbine in conventional fashion.
[ 0012 ] The concern here is for combustor liner stops used to secure the forward end of the combustor liner to the forward end of the combustor flow sleeve, and therefore, the nozzle and transition piece/impingement sleeve configurations need not be described further. [ 0013 ] In the exemplary but nonlimiting embodiment, the forward end 14 of the combustor liner 12 is provided with plural liner stops 32 (Figs. 1 and 2). Three such stops 32 are illustrated in Fig. 3, substantially equally spaced about the circumference of the liner 12. It will be appreciated that the number of stops may vary but three is regarded as the minimum number needed to insure the required stability between the liner 12 and the flow sleeve 18.
[ 0014 ] As best seen in Fig. 2, each liner stop 32 includes a strut 34 and a tab or foot 36 at the remote or free end of the strut. The strut 34 may be air-foil shaped and slanted in a radially-outward direction toward the aft end of the liner. The slanting of the strut and the airfoil shape of the strut minimize flow disruption in the air passing through the radial flow passage 28. The tab or foot 36 has a shape different than the strut. In the exemplary embodiment, the tab 36 is shown to have a substantially rectangular block-like shape but the exact shape may vary. Preferably, the inner surface 38 is shaped to conform to the outer surface 40 of the flow sleeve 18.
[ 0015 ] The forward end 20 of the flow sleeve 18 is formed with slots 40 that open to the forward end of the flow sleeve. The slots correspond in number and circumferential location to the liner stops 32. The flow sleeve 18 is secured by sliding the flow sleeve into the combustor casing 35. Note that the foot 36 of each strut 34 is received radially outwardly of the respective slot 40 such that the enlarged foot 36 is outside the flow sleeve 18 and thus outside the annular flow path 28. Note also that the width of each foot 36 is wider than the respective slot 40, preventing any radial dislodgement of the liner 12 relative to the flow sleeve 18. After the flow sleeve and liner are fully assembled, a single or plural closure parts, for example ring 42 (Fig. 4) may be bolted or otherwise suitably attached to the combustor case 35 and/or the forward end 20 of the flow sleeve 18, closing the open forward ends of the slots 40, and therefore precluding excessive axial displacement of the liner relative to the flow sleeve. Some space is permitted, however, for accommodating differential thermal growth of the respective liner and flow sleeve components. [ 0016 ] It may also be desirable to take up some of this axial space through elastic members or elements that can be inserted into the remaining spaces in the slots 40 and that still permit axial growth but in a more controlled manner, and prevent excessive wear of the respective contact surfaces during operation. [ 0017 ] While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

WHAT IS CLAIMED IS:
1. A combustion liner comprising: a substantially cylindrical body having forward and aft ends, the forward end provided with plural, circumferentially-shaped stops adapted for connection to a flow sleeve surrounding said substantially cylindrical body, each stop comprised of a radially-projecting strut having an end remote from the substantially-cylindrical body provided with a tab having a shape different than said strut.
2. The combustion liner of claim 1 wherein said strut is substantially airfoil- shaped.
3. The combustion liner of claim 1 wherein said strut is slanted toward said aft end of said substantially-cylindrical body.
4. The combustion liner of claim 1 wherein said tab is formed to have an elongated, substantially-rectangular block shape.
5. The combustion liner of claim 1 wherein said plural, circumferentially-spaced stops comprise three stops substantially equally-spaced about a circumference of said substantially cylindrical body.
6. The combustion liner of claim 2 wherein said strut is slanted toward said aft end of said substantially-cylindrical body.
7. The combustion liner of claim 6 wherein said plural, circumferentially-spaced stops comprise three stops substantially equally-spaced about a circumference of said substantially cylindrical body.
8. A combustor liner and flow sleeve assembly comprising: a combustor liner having an aft end and a forward end; a flow sleeve surrounding said combustor liner and defining an axially- extending, annular flow passage radially therebetween, the flow sleeve provided with plural slots at a forward end thereof; the combustor liner provided with plural, circumferentially-spaced struts extending radially outwardly and through respective ones of said plural slots in said flow sleeve; each of said plural circumferentially- spaced struts provided with a tab that lies on an exterior surface of said flow sleeve outside said annular flow passage.
9. The combustor liner and flow sleeve assembly of claim 8 wherein each of said plural circumferentially-spaced struts is substantially airfoil-shaped.
10. The combustion liner and flow sleeve assembly of claim 8 wherein each of said plural circumferentially-spaced struts is slanted toward said aft end of said substantially-cylindrical body.
11. The combustion liner and flow sleeve assembly of claim 8 wherein said tab is formed to have an elongated, substantially-rectangular block shape.
12. The combustion liner and flow sleeve assembly of claim 8 wherein said plural, circumferentially-spaced struts comprise three struts substantially equally-spaced about a circumference of said substantially cylindrical body.
13. The combustion liner and flow sleeve assembly of claim 9 wherein each of said plural circumferentially-spaced struts is slanted toward said aft end of said substantially-cylindrical body.
14. The combustion liner and flow sleeve assembly of claim 13 wherein said plural, circumferentially-spaced struts comprise three struts substantially equally- spaced about a circumference of said substantially cylindrical body.
15. The combustion liner and flow sleeve and flow sleeve assembly of claim 8 wherein said plural slots are substantially rectangular, with open ends at said forward end of said flow sleeve.
16. The combustion liner and flow sleeve assembly of claim 15 wherein after assembly, said plural slots are closed at said open ends by an annular ring attached to the forward end of said flow sleeve.
17. A combustor liner and flow sleeve assembly comprising: a combustor liner having an aft end and a forward end; and a flow sleeve surrounding said combustor liner and defining an axially- extending flow passage radially therebetween, the flow sleeve provided with plural slots at a forward end thereof; wherein the combustor liner is provided with plural, circumferentially-spaced airfoil-shaped struts slanted toward said aft end of said substantially-cylindrical body and extending radially outwardly and through respective ones of said plural slots in said flow sleeve; each of said plural circumferentially-spaced struts provided with a remote tab having a shape different than that strut, and wherein said tab lies on an exterior surface of said flow sleeve.
18. The combustion liner and flow sleeve assembly of claim 17 wherein said tab is formed to have an elongated, substantially-rectangular block shape.
19. The combustion liner and flow sleeve assembly of claim 17 wherein said plural, circumferentially-spaced struts comprise three struts substantially equally- spaced about a circumference of said substantially cylindrical body.
20. The combustion liner and flow sleeve assembly of claim 17 wherein said plural slots have open ends at said forward end of said flow sleeve and, after assembly, said plural slots are closed at said open ends by a single or plural closure parts, attached to the combustor casing or forward end of the flow sleeve.
PCT/RU2012/000302 2012-04-19 2012-04-19 Combustor liner stop WO2013157976A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US14/394,339 US20150068212A1 (en) 2012-04-19 2012-04-19 Combustor liner stop
PCT/RU2012/000302 WO2013157976A1 (en) 2012-04-19 2012-04-19 Combustor liner stop

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2012/000302 WO2013157976A1 (en) 2012-04-19 2012-04-19 Combustor liner stop

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WO2013157976A1 true WO2013157976A1 (en) 2013-10-24

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3290806A1 (en) * 2016-09-05 2018-03-07 Ansaldo Energia Switzerland AG Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device
US11009232B2 (en) 2016-09-05 2021-05-18 Ansaldo Energia Switzerland AG Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device

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