EP2378201A2 - Appareil et procédé pour minimiser et/ou supprimer les fuites d'air de dilution dans un ensemble de chemise de combustion - Google Patents

Appareil et procédé pour minimiser et/ou supprimer les fuites d'air de dilution dans un ensemble de chemise de combustion Download PDF

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Publication number
EP2378201A2
EP2378201A2 EP11162106A EP11162106A EP2378201A2 EP 2378201 A2 EP2378201 A2 EP 2378201A2 EP 11162106 A EP11162106 A EP 11162106A EP 11162106 A EP11162106 A EP 11162106A EP 2378201 A2 EP2378201 A2 EP 2378201A2
Authority
EP
European Patent Office
Prior art keywords
liner
combustion
wall
combustion liner
liner assembly
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Withdrawn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
EP11162106A
Other languages
German (de)
English (en)
Other versions
EP2378201A3 (fr
Inventor
Predrag Popovic
Krishna Kumar Venkataraman
Derrick Walter Simons
Ajay Kumar Gupta
William Kirk Hessler
Jeffrey Lebegue
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 EP2378201A2 publication Critical patent/EP2378201A2/fr
Publication of EP2378201A3 publication Critical patent/EP2378201A3/fr
Withdrawn legal-status Critical Current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
    • F23R3/02—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
    • 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
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses

Definitions

  • the present invention relates to apparatus and methods for minimizing or eliminating dilution air leakage paths in a gas turbine combustor and particularly relates to apparatus and methods for managing dilution air leakage to achieve lower emission levels.
  • NO and NO 2 oxides of nitrogen
  • CO carbon monoxide
  • unburned hydrocarbons as well as other particulates.
  • Various systems have been proposed and utilized for reducing emissions. For example, water or steam injection into the burning zone of the gas turbine combustor, catalytic clean-up of NO x and CO from the gas turbine exhaust and dry low NO x combustors have been used in the past. Compressor discharge dilution air introduced into the liner sleeve of the combustor and transition piece has also been utilized to reduce emissions.
  • a combustion liner assembly for a gas turbine comprises an outer liner, the outer liner having a flange at a forward end; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; and a slip joint connected to the second inner wall, the slip joint receiving the flange of the outer liner.
  • a combustion liner assembly for a gas turbine comprises an outer liner; an inner liner disposed within the outer liner, the inner liner having a first inner wall; a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; an aft section connected to aft ends of the outer liner and the inner liner; and a slip joint provided between the aft section and the inner liner.
  • a combustion liner assembly 2 comprises an outer liner 4 and an inner liner 6.
  • a venturi 8 is provided at a forward end of the combustion liner assembly 2 and includes a venturi throat 10 which is provided between the inner liner 6 and an inner wall 12.
  • a flange 14 may be integrally formed with the outer liner 4 and is received in a slip joint 16 that is connected to the inner wall 12 of the venturi 8.
  • the inner liner 6 includes an inner wall 24 and turbulators 18 provided on an outer surface.
  • An aft section, or gooseneck section, 20 is connected to the aft portion of the outer liner 4 and the inner liner 6.
  • Radial drain or dump holes 22 are provided in the inner liner at an area adjacent to the aft section 20.
  • the combustion liner assembly 2 may be welded to a liner sleeve at areas A and B corresponding to the slip joint 16 and the end of the aft section 20, respectively.
  • the combustion liner assembly 2 may be circumferentially welded to the liner sleeve, rather than riveted as in prior art arrangements.
  • the venturi 10 may be circumferentially welded to the inner wall 12 and the inner wall 24 of the inner liner 6.
  • the thickness of the inner wall 24 and the thickness of the inner wall 24 of the inner liner 6 at the portion containing the circumferential weld may be thicker than prior art combustion liner assembly inner liners to increase the structural integrity of the venturi, as the venturi will be welded to the liner sleeve as opposed to riveted.
  • the radial drain or dump holes 22 of the embodiment shown in Figs. 1 and 2 provides a radial discharge of cooling flow into the flame zone.
  • the embodiments shown in Figs. 1 and 2 may also have an increased impingement cooling area combined with the turbulators 18.
  • a small controlled leak may be provided into the cooling channel between the outer liner 4 and the inner liner 6 as an alternative to a bellows.
  • the combustion liner assembly 2 includes the aft section, or gooseneck section 20 which comprises axial drain or dump holes 24, rather than radial drain or dump holes. It has been found that the use of radial drain or dump holes, as shown in the embodiment of Figs. 1 and 2 , may trigger high frequency combustion instability, or screech, during transfer to the premix combustion and at the turndown when the flame temperature is reduced. However, the axial drain or dump holes 24 do not trigger high frequency instability with the integral venturi of the embodiment shown in Fig. 3 .
  • the venturi cooling is rerouted to have an axial discharge with the same effective area as the radial discharge of the venturi of the embodiment shown in Fig. 3 .
  • a combustion liner assembly 2 comprises an outer liner 4 and an inner liner 6.
  • the outer liner 4 includes a flange 14 that is received in a slip joint 16 that is connected to an inner wall 12 of a venturi 8 that comprises a venturi throat 10 that connects the inner wall 12 and a portion of the inner liners 6 having axial drain or dump holes 24.
  • the combustion liner assembly 2 comprises radial drain or dump holes 22 formed in the inner liner 6.
  • the dump holes 26 may be provided as holes on the face of the aft section 20, i.e. at the intersection of the cylindrical and conical portions of the aft section 20.
  • a combustion liner assembly according to another embodiment comprises an outer liner 4 and an inner liner 6.
  • a venturi 8 is provided at a forward section of the combustion liner assembly 2 and includes a venturi throat 10 and an inner wall 12.
  • the venturi 8 also includes an inner wall 24 connected between the venturi throat 10 and the inner liner 6.
  • An aft section 20 is connected to the outer liner 4 and the inner liner 6 by an aft slip joint 30.
  • the combustion liner assembly 2 comprises radial drain or dump holes 22 provided in the inner liner 6.
  • the aft end of the combustion liner assembly 2 comprises a bellows 28, as well as a slip joint 30 as disclosed in the previous embodiments.
  • a combustion liner assembly 2 includes an outer liner 4 and an inner liner 6.
  • a venturi 8 comprises a venturi throat 10 welded to an inner wall 12 and an inner wall 24 connected to the inner liner 6.
  • a flange 14 of the outer liner 4 is received in a slip joint 16 at the forward end of the combustion liner assembly 2.
  • An aft section 20 of the combustion liner 2 is connected to the outer liner 4 and the inner liner 6 by an aft slip joint 30.
  • the slip joint 16 may be formed of, for example, an alloy of primarily nickel, such as Hastelloy®, and the flange 14 may be formed of, for example, stainless steel.
  • the slip joint 16 may also be provided with a wear resistant coating.
  • the slip joint 16 provides a double seal on both sides of the flange 14 and may be machined to tight tolerances. As the temperature of the combustion liner assembly 2 increases during operation of the gas turbine, the small leakage area between the flange 14 and the slip joint 16 decreases as the flange 14 expands into the slip joint 16.
  • the combustion liner assemblies reduce, or eliminate, airflow losses in between the venturi wall and the liner wall so that airflow can be used and more evenly dispersed. Reduction, or elimination, of variance to air flow will allow more consistent air flow to be utilized in fuel air mixture in the head end combustion zone rather than leak air flow into direct "stream".
  • the combustion liner assemblies are relatively easy to manufacture and produce a more repeatable air flow from can to can and in turn help to create better fuel air mixture pattern than current design and lower combustion emissions. These are improvements to variation and mixing fuel air better through the mixing holes than would happen through the current design.
  • the combustion liner assemblies reduce, or eliminate, leaks so airflow in more noncritical areas is conserved and made more consistent, i.e. can to can variation is lowered.
  • the combustion liner assemblies also increase airflow in useable areas in a more dispersed and even mixing through the mixing holes than would happen through current designs.
  • the combustion liner assemblies can be replaced in the field easily.
  • the existing liners can be pulled out and replaced with the combustion liner assemblies disclosed herein.
  • the combustion liner assemblies may also use current production methods and machining to produce.
  • the combustion liner assemblies do not change the fit, form or function of the overall liner assembly.

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)
EP11162106A 2010-04-13 2011-04-12 Appareil et procédé pour minimiser et/ou supprimer les fuites d'air de dilution dans un ensemble de chemise de combustion Withdrawn EP2378201A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/759,042 US20110247340A1 (en) 2010-04-13 2010-04-13 Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly

Publications (2)

Publication Number Publication Date
EP2378201A2 true EP2378201A2 (fr) 2011-10-19
EP2378201A3 EP2378201A3 (fr) 2013-04-03

Family

ID=44262859

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11162106A Withdrawn EP2378201A3 (fr) 2010-04-13 2011-04-12 Appareil et procédé pour minimiser et/ou supprimer les fuites d'air de dilution dans un ensemble de chemise de combustion

Country Status (4)

Country Link
US (1) US20110247340A1 (fr)
EP (1) EP2378201A3 (fr)
CN (1) CN102221208A (fr)
WO (1) WO2011130001A2 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120047895A1 (en) * 2010-08-26 2012-03-01 General Electric Company Systems and apparatus relating to combustor cooling and operation in gas turbine engines
US8931280B2 (en) * 2011-04-26 2015-01-13 General Electric Company Fully impingement cooled venturi with inbuilt resonator for reduced dynamics and better heat transfer capabilities
WO2016167784A1 (fr) * 2015-04-17 2016-10-20 Siemens Aktiengesellschaft Système d'interface flexible pour chambre de combustion de turbine à gaz
US20180283287A1 (en) 2015-04-30 2018-10-04 Nuovo Pignone Tecnologie Srl Ultra-low nox emission gas turbine engine in mechanical drive applications
US10139108B2 (en) * 2015-06-08 2018-11-27 Siemens Energy, Inc. D5/D5A DF-42 integrated exit cone and splash plate

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US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US6921014B2 (en) * 2002-05-07 2005-07-26 General Electric Company Method for forming a channel on the surface of a metal substrate
US6832482B2 (en) * 2002-06-25 2004-12-21 Power Systems Mfg, Llc Pressure ram device on a gas turbine combustor
US6865892B2 (en) * 2002-12-17 2005-03-15 Power Systems Mfg, Llc Combustion chamber/venturi configuration and assembly method
US20090019854A1 (en) * 2007-07-16 2009-01-22 General Electric Company APPARATUS/METHOD FOR COOLING COMBUSTION CHAMBER/VENTURI IN A LOW NOx COMBUSTOR
US20110041507A1 (en) * 2009-08-18 2011-02-24 William Kirk Hessler Integral Liner and Venturi for Eliminating Air Leakage

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

Also Published As

Publication number Publication date
WO2011130001A3 (fr) 2013-05-10
EP2378201A3 (fr) 2013-04-03
CN102221208A (zh) 2011-10-19
US20110247340A1 (en) 2011-10-13
WO2011130001A2 (fr) 2011-10-20

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