WO2018132185A1 - Accessoire de fixation mécanique d'une fusée à combustible sur une base de boîtier de support - Google Patents

Accessoire de fixation mécanique d'une fusée à combustible sur une base de boîtier de support Download PDF

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Publication number
WO2018132185A1
WO2018132185A1 PCT/US2017/063373 US2017063373W WO2018132185A1 WO 2018132185 A1 WO2018132185 A1 WO 2018132185A1 US 2017063373 W US2017063373 W US 2017063373W WO 2018132185 A1 WO2018132185 A1 WO 2018132185A1
Authority
WO
WIPO (PCT)
Prior art keywords
support housing
fuel rocket
fuel
rocket
threaded
Prior art date
Application number
PCT/US2017/063373
Other languages
English (en)
Inventor
Keith W. PIERSALL
Mark Murray Carter
Original Assignee
Siemens Energy, Inc.
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
Priority claimed from US15/403,746 external-priority patent/US20170122566A1/en
Application filed by Siemens Energy, Inc. filed Critical Siemens Energy, Inc.
Publication of WO2018132185A1 publication Critical patent/WO2018132185A1/fr

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
    • F23R3/28—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
    • 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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14641—Special features of gas burners with gas distribution manifolds or bars provided with a plurality of nozzles

Definitions

  • the present disclosure relates generally to a combustion system of a turbine engine, and more particularly to a field configurable support housing assembly and a method for rapid on-site reconfiguration of a fuel rocket.
  • a turbomachine such as a gas turbine engine
  • air is pressurized in a compressor section then mixed with fuel and burned in a combustion section to generate hot combustion gases.
  • the hot combustion gases are expanded within a turbine section of the engine where energy is extracted from the combustion gases to power the compressor section to produce useful work, such as turning a generator to produce electricity.
  • Turbine engine fuel systems typically include a pilot nozzle surrounded by a circumferential configuration of fuel rockets for injecting fuel into the combustor.
  • the pilot nozzle is bolted to a support housing assembly and the fuel rockets are welded to the support housing assembly which attaches the pilot nozzle and the fuel rockets to the turbine engine.
  • Typical support housing includes a base having orifices extending through the base to receive the pilot nozzle and the fuel rockets.
  • Heat and gases generated from the combustion process may shorten the life of the combustor components, including the components making up the pilot nozzle and the fuel rockets.
  • oxidation and/or burning and wear of the support rocket tips may cause damage necessitating that the support housing be sent to a repair facility for repair or replacement during an engine outage.
  • Sending the entire support housing assembly to a repair facility is expensive and may take an undesirable amount of time to replace it in the turbine engine.
  • the ability to replace the pilot nozzle components and the fuel rocket components in the field would enable a greater number of support housing and pilot nozzle assemblies to continue normal operation in the turbine and reduce the time the turbine is in an outage.
  • aspects of the present disclosure relate to a field configurable support housing assembly and a method for rapid on-site reconfiguration of a cylindrical hollow fuel rocket.
  • a field configurable support housing assembly comprises a support housing base and a cylindrical hollow fuel rocket.
  • the support housing base includes at least one through hole.
  • the cylindrical hollow fuel rocket includes a nozzle tip positioned such that the hollow fuel rocket generally aligns with the through hole.
  • the fuel rocket is reconfigurable on-site using a mechanical attachment.
  • a method for rapid in-situ reconfiguration of a cylindrical hollow fuel rocket includes mechanically coupling a cylindrical fuel rocket to the support housing on-site and clocking the coupled support housing and fuel rocket such that a tip of the fuel rocket is oriented at a predetermined angular orientation relative to a flow-guiding element.
  • FIG. 1 illustrates a perspective view of a fuel rocket assembly
  • FIG. 2 illustrates a cross section of a conventional fuel rocket welded to a support housing collar
  • FIG. 3 illustrates a cross section of a first embodiment of a fuel rocket mechanically attached to a support housing
  • Fig. 4 illustrates a second embodiment of a fuel rocket mechanically attached to a support housing.
  • the present application proposes an attachment scheme to mechanically attach a fuel rocket to a support housing on-site.
  • On-site in the context of the application, may mean on the grounds of the plant in which the gas turbine is installed or a location within a 5 mile radius of the gas turbine plant.
  • This mechanical attachment scheme may replace the previously described conventional welded attachment scheme.
  • Replacing a fuel rocket having a conventionally welded attachment scheme requires that the rocket be cut off, the surfaces of the support housing as well as the mating surface of the fuel rocket to be re-machined, and a new fuel rocket to be welded on in a repair facility. Mechanically attaching the fuel rocket to the support housing may enable a quick on site repair.
  • the support housing assembly 10 includes a base 20, fuel support ports 80, and a plurality of fuel rockets 40.
  • the fuel rockets including a nozzle tip 50 which includes the fuel metering orifice 60.
  • the central orifice 70 may receive a pilot nozzle.
  • Fuel enters the support housing assembly 10 via the fuel supply ports 80 and is distributed to the fuel rockets 40 by internally cast passages in the base 20.
  • the fuel exits the support housing assembly 10 and enters the combustion chamber through the fuel rocket orifices 60.
  • the plurality of fuel rockets 40 may be disposed in a circumferential arrangement around a central orifice 70.
  • the central orifice 70 may receive a pilot nozzle.
  • eight fuel rockets 40 are disposed in a circumferential arrangement around the central orifice 70, however, other arrangements of fuel rockets 40 may also be applicable for the proposed support housing assembly 10.
  • Each fuel rocket 40 may be configured as a hollow cylinder configured to deliver fuel gas to a combustion system.
  • One end of the fuel rocket 40 illustrated as the upstream end, may be attached to the support housing base 20.
  • Another opposite, downstream end of the fuel rocket 40 may include a nozzle tip 50 including one or more fuel flow orifices 60 through which a fuel may flow into a combustion system, for example.
  • a fuel may flow into a combustion system, for example.
  • respective supply lines shown generally as 80, leading into the support housing base 20. The respective fuel passes through the support housing base 20, then through the fuel rockets 40 and into the combustion system.
  • FIG 2 illustrates a cross section of a conventional fuel rocket 40 in which the fuel rocket 40 is attached to the support housing base 20 by a weld 90.
  • the nozzle tip 50 may be manufactured integral with the remaining portion of the fuel rocket.
  • This damage may include wear and/or oxidation and is due to, for example, a flashback occurrence where the flame travels backwards in a direction away from the turbine section.
  • a flame flashback may cause damage to the nozzle tips as these components are not typically designed to withstand such high temperatures.
  • the entire support housing assembly is removed and sent to a repair facility where the welded connections are dismantled.
  • a replacement support housing assembly 10 must be supplied to the site to replace the removed support housing assembly.
  • FIG 3 illustrates an embodiment of a cross section of a proposed fuel rocket 40 mechanically attached to a support housing base 20.
  • the support housing base 20 includes an internally cast hole 95 through which fuel flows into the hollow interior of the fuel rocket 40.
  • the fuel rocket 40 may be coupled to the support housing base 20 using a non-welded mechanical attachment 100 enabling the replacement of the fuel rocket assembly on-site. Only conventional tools, such as a wrench, would be required for the repair/replacement. Enabling the easy removal and replacement of the fuel rockets 40 where the majority of support housing damage occurs would eliminate the need to replace the entire support housing assembly 10 and ship it into a repair facility for refurbishment.
  • the mechanical attachment 100 for the illustrated fuel rocket 40 includes a threaded joint such that the exterior surface of the upstream end 140 of the fuel rocket 40 is threaded.
  • the threaded upstream end 140 will be used to mechanically couple the fuel rocket 40 to the support housing base 20.
  • the threads could be tapped directly into the cast hole 95 or a gas turbine component 110 may abut the support housing base 20 and may be positioned so that its hollow interior is coaxial with the through- hole of the support housing base 20.
  • the gas turbine component 110 may be a bushing.
  • the gas turbine component 110 will be referred to hereinafter as a bushing 110, however, other gas turbine components may also be used.
  • the bushing 110 may be attached to the support housing base 20 by a weld, for example.
  • the interior surface of a downstream end of the bushing 110 may include threads such that this threaded portion receives the threaded upstream end 140 of the fuel rocket 40.
  • the threaded portions of the fuel rocket 40 and the bushing 110 interengage coupling the fuel rocket 40 and the bushing 110 together. Wrench flats 130 are provided to properly torque the fuel rocket 40 to the threaded bushing 110.
  • the mechanical attachment 100 includes a bushing 110 which is shown surrounding the fuel rocket 40 and coupled to the fuel rocket 40 by the threaded connection.
  • a locking spring washer 120 is disposed to prevent the fuel rocket 40 from backing out during operation.
  • a seal 150 may be incorporated to seal the interface such that the fuel remains in the fuel passage.
  • FIG 4 illustrates a further embodiment of a cross section of a fuel rocket 40 mechanically attached to a support housing base 20.
  • the mechanical attachment 100 includes a bolt on flange seal.
  • the bolt on flange seal comprises a flange retainer 160.
  • the flange retainer 160 may be welded onto a surface of the support housing base 20.
  • the flange retainer 160 may be made integral with the fuel rocket 40.
  • An outer surface of upstream end of the fuel rocket 40 includes a stepped portion 170 such that the stepped portion 170 fits within the flange retainer 160.
  • a fastener 180 such as a bolt, secures the flange retainer and the fuel rocket 40 to the support housing base 20 mechanically coupling the fuel rocket 40 to the support housing base 20.
  • a seal 150 is disposed within a gap between the stepped portion 170 of the fuel rocket 40 and a surface of the support housing base 20.
  • a method for rapid on-site reconfiguration of a fuel rocket assembly 10 includes mechanically coupling the fuel rocket 40 to the support housing on-site. Additionally, the method includes clocking the coupled fuel rocket 40 such that a tip 50 of the fuel rocket 40 is oriented at a predetermined angular orientation relative to a flow guiding element.
  • the mechanical coupling of the fuel rocket 40 to the support housing base 20 on-site includes providing a gas turbine component 110 having an internal threaded portion attached to the support housing base 20.
  • the gas turbine component 110 may be a bushing having internal threads.
  • the fuel rocket 40 includes an outer surface having a threaded upstream end 140.
  • the internal threaded portion of the bushing 110 and the threaded upstream end 140 are threaded together such that the internal threaded portion and the threaded upstream end 140 interengage and couple the fuel rocket 40 to the support housing base 20.
  • the threaded connection is secured using the provided wrench flats 130.
  • the fastener 130 may be a hex nut, for example.
  • a seal 150 may be disposed within a gap between a locking spring washer 120, the threaded upstream end, and the fuel rocket 40. The seal 150 creates a sealed interface such that a fuel flowing through the hollow fuel rocket 40 is sealed within the fuel rocket 40.
  • the mechanical coupling of the fuel rocket 40 to the support housing base 20 on-site includes providing a gas turbine component attached to the support housing base 20, the gas turbine component comprising a flange retainer 160.
  • the flange retainer 160 is positioned relative to the support housing base 20 such that a through hole in the support housing base 20 aligns with a through hole in the flange retainer 160.
  • the cylindrical fuel rocket 40 would then be positioned such that the hollow fuel rocket 40 aligns with the through hole.
  • the fuel rocket 40 includes a stepped portion 170 on its outer surface.
  • the stepped portion 170 abuts an interior surface of the flange retainer 160.
  • the flange retainer and the fuel rocket may be secured to a surface of the support housing using a fastener.
  • a seal may be disposed within a gap between the stepped portion of the fuel rocket and a surface of the support housing.
  • the fastener may compress the seal and create a sealed interface such that a fuel flowing through the hollow fuel rocket is sealed within the
  • the coupled support housing base 20 and fuel rocket 40 may be clocked such that a tip 50 of the fuel rocket 40 is oriented at a predetermined angular orientation.
  • the fuel rocket 40 may also be decoupled from the support housing on-site.
  • the method steps described previously may be performed in reverse, for example, untightening the fastener 130 and unthreading the fuel rocket 40 from the internally threaded gas turbine component.
  • the support housing is attached to a gas turbine engine during the mechanical coupling of the fuel rocket to the support housing on-site.
  • the ability to couple and uncouple the fuel rocket 40 and the support housing base 20 on-site may enable customization of fuel rocket 40 having an orifice size to specific field site conditions.
  • the specific field site conditions may include environmental conditions at the field site or may include the particular requirements of the gas turbine.

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)

Abstract

Ensemble boîtier de support (10) configurable sur le terrain. L'ensemble boîtier de support comprend une base (20) de boîtier de support et une fusée à combustible creuse cylindrique (40). La base (20) de boîtier de support comprend au moins un trou traversant. La fusée à combustible creuse cylindrique (40) comprend une pointe (50) de buse positionnée de telle sorte que la fusée à combustible creuse (40) s'aligne globalement sur le trou traversant. La fusée à combustible (40) est reconfigurable sur site à l'aide d'un accessoire de fixation mécanique (100). L'invention concerne également un procédé de reconfiguration rapide sur site d'une fusée à combustible creuse cylindrique (40).
PCT/US2017/063373 2017-01-11 2017-11-28 Accessoire de fixation mécanique d'une fusée à combustible sur une base de boîtier de support WO2018132185A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US15/403,746 US20170122566A1 (en) 2015-05-12 2017-01-11 Mechanical Attachment of Support Housing Rocket
US15/403,746 2017-01-11

Publications (1)

Publication Number Publication Date
WO2018132185A1 true WO2018132185A1 (fr) 2018-07-19

Family

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Family Applications (1)

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PCT/US2017/063373 WO2018132185A1 (fr) 2017-01-11 2017-11-28 Accessoire de fixation mécanique d'une fusée à combustible sur une base de boîtier de support

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5253810A (en) * 1992-03-13 1993-10-19 The United States Of America As Represented By The Secretary Of The Navy High heat, high pressure, non-corrosive injector assembly
WO1999019670A2 (fr) * 1997-10-10 1999-04-22 Siemens Westinghouse Power Corporation DISTRIBUTEUR DE COMBUSTIBLE POUR DISPOSITIF COMBUSTOR A FAIBLE TENEUR EN NOx
EP2362141A1 (fr) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Agencement de brûleur
US20130043324A1 (en) * 2011-08-18 2013-02-21 General Electric Company Flow adjustment orifice systems for fuel nozzles
US20150000283A1 (en) * 2013-06-27 2015-01-01 Stephen A. Ramier Combustor apparatus in a gas turbine engine
US20150089954A1 (en) * 2012-08-17 2015-04-02 Dürr Systems GmbH Burners having fuel plenums
EP3109554A1 (fr) * 2015-06-22 2016-12-28 Doosan Heavy Industries & Construction Co. Ltd. Unité de buse d'alimentation en combustible ayant une structure d'étanchéité

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5253810A (en) * 1992-03-13 1993-10-19 The United States Of America As Represented By The Secretary Of The Navy High heat, high pressure, non-corrosive injector assembly
WO1999019670A2 (fr) * 1997-10-10 1999-04-22 Siemens Westinghouse Power Corporation DISTRIBUTEUR DE COMBUSTIBLE POUR DISPOSITIF COMBUSTOR A FAIBLE TENEUR EN NOx
EP2362141A1 (fr) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Agencement de brûleur
US20130043324A1 (en) * 2011-08-18 2013-02-21 General Electric Company Flow adjustment orifice systems for fuel nozzles
US20150089954A1 (en) * 2012-08-17 2015-04-02 Dürr Systems GmbH Burners having fuel plenums
US20150000283A1 (en) * 2013-06-27 2015-01-01 Stephen A. Ramier Combustor apparatus in a gas turbine engine
EP3109554A1 (fr) * 2015-06-22 2016-12-28 Doosan Heavy Industries & Construction Co. Ltd. Unité de buse d'alimentation en combustible ayant une structure d'étanchéité

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