EP2719953A2 - Mehrpunktinjektoren mit Hilfsstufe - Google Patents

Mehrpunktinjektoren mit Hilfsstufe Download PDF

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Publication number
EP2719953A2
EP2719953A2 EP13187920.7A EP13187920A EP2719953A2 EP 2719953 A2 EP2719953 A2 EP 2719953A2 EP 13187920 A EP13187920 A EP 13187920A EP 2719953 A2 EP2719953 A2 EP 2719953A2
Authority
EP
European Patent Office
Prior art keywords
fuel
auxiliary
injector
nozzle body
nozzle
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Withdrawn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
EP13187920.7A
Other languages
English (en)
French (fr)
Other versions
EP2719953A3 (de
Inventor
Lev Alexander Prociw
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.)
Collins Engine Nozzles Inc
Original Assignee
Delavan 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 US13/647,867 external-priority patent/US9003804B2/en
Application filed by Delavan Inc filed Critical Delavan Inc
Publication of EP2719953A2 publication Critical patent/EP2719953A2/de
Publication of EP2719953A3 publication Critical patent/EP2719953A3/de
Withdrawn legal-status Critical Current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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the present invention relates to gas turbine engines, and more particularly to gas turbine engines utilizing low calorific value fuels.
  • LCV low calorific value
  • LCV gas can have a heating value on the order of only about 130 BTU/Ft 3 (4.84 kJ/m 3 ) and less.
  • LCV gas can be used with or as a replacement for more traditional fuels in applications including internal combustion engines, furnaces, boilers, and the like.
  • fluctuating fuel costs and availability drive a growing interest in use of LCV fuels where more traditional fuels, such as natural gas, are typically used.
  • LCV fuel While there is growing interest in LCV fuels, the low heating value of LCV fuel creates obstacles to its more widespread use. Thus there is an ongoing need for improved LCV fuel combustion systems. For example, the use of LCV fuel in an existing, conventional gas turbine engine requires special considerations regarding the fuel injection system. Flammability of LCV fuel gas can be unknown due to variables in the gasification process, so there is typically an unpredictable flameout limit when lowering fuel flow to operate at reduced power. Due to the relatively low heating value, LCV fuel can require 10 to 12 times the volumetric flow rate of natural gas for which the original engine was designed, which can give rise to capacity complications for traditional combustion systems. Typical gasification systems produce LCV fuel through high-temperature processes, and LCV fuel is often supplied directly from the gasification system. The LCV fuel temperature can be significantly hotter than in conventional fuel systems, which can give rise to further thermal management concerns. Additionally, due to the low calorific value, the fuel can present difficulties in terms of start up and flame stabilization.
  • the subject invention is directed to a new and useful a multipoint combustion system for a gas turbine engine.
  • the system includes a housing defining a pressure vessel.
  • a master injector is mounted to the housing for injecting fuel in an injection plume along a central axis defined through the pressure vessel.
  • a plurality of slave injectors are each disposed outward of and substantially parallel to the master injector for injecting fuel and air in an ignition plume radially outward of fuel injected through the master injector.
  • the master injector and slave injectors are configured and adapted so the injection plume of the master injector intersects with the ignition plumes of the slave injectors.
  • Each of the slave injectors is an injector for a low-calorific value fuel as described below.
  • a primary manifold is included within the pressure vessel for distributing fuel to the slave injectors.
  • An auxiliary manifold is in fluid communication with the auxiliary nozzles of the slave injectors for issuing an auxiliary flow of fuel from the auxiliary nozzles that is separate from the fuel flow of the primary manifold.
  • the pressure vessel includes a pressure dome with a central aperture and a central inlet fitting mounted to the central aperture of the pressure dome, wherein the auxiliary manifold is external to the pressure dome.
  • the primary and auxiliary manifolds can advantageously be thermally isolated from one another.
  • the auxiliary nozzles of the slave injectors can be mounted to the pressure vessel with floating seals to accommodate thermal expansion differentials between the pressure vessel and the auxiliary manifold.
  • the auxiliary manifold can advantageously be flexible for ease of installation and to accommodate thermal expansion differentials for example.
  • the auxiliary manifold can be configured and adapted to issue at least one of natural gas and liquid fuel to the auxiliary nozzles of the slave injectors.
  • the auxiliary manifold can be operatively connected to an external valve to permit purging of the auxiliary manifold and auxiliary nozzles with engine air for complete shutdown of the auxiliary manifold and nozzles.
  • the invention also provides an injector for a low-calorific value fuel combustion system.
  • the injector includes a nozzle body defining a fuel circuit for injecting low-calorific value fuel.
  • An auxiliary nozzle is mounted to the nozzle body and defines a fuel circuit for injecting at least one of natural gas and liquid fuel.
  • the auxiliary nozzle is mounted to the nozzle body with a floating seal to accommodate a differential in thermal expansion between the auxiliary nozzle and the nozzle body.
  • the fuel circuit of the nozzle body can be annular and the nozzle body can define an outer air circuit outboard of the fuel circuit of the nozzle body.
  • the auxiliary nozzle can advantageously include a fuel outlet configured and adapted to issue a spray of fuel that diverges away from a longitudinal axis defined by the auxiliary nozzle.
  • the nozzle body includes an inner wall and an outer wall outboard of and spaced apart from the inner wall, wherein the fuel circuit of the nozzle body passes through the inner and outer walls.
  • the outer wall can define at least one aperture configured for passage of fuel from the primary manifold into the nozzle body for selective injection of at least natural gas and LCV fuel gas in a proportional mix.
  • the auxiliary nozzle can be inboard of and spaced apart from the inner wall of the nozzle body. It is contemplated that the nozzle body and auxiliary nozzle can define a common longitudinal axis, wherein the auxiliary nozzle and nozzle body each include a respective fuel outlet, and wherein the fuel outlet of the auxiliary nozzle is upstream relative to the outlet of the nozzle body along the longitudinal axis.
  • Fig. 1 a partial view of an exemplary embodiment of a multipoint combustion system in accordance with the invention is shown in Fig. 1 and is designated generally by reference character 100.
  • Fig. 2 Other embodiments of combustion systems in accordance with the invention, or aspects thereof, are provided in Fig. 2 , as will be described.
  • the systems and methods of the invention can be used to supply low temperature fuel to LCV combustors, for example liquid fuel for startup.
  • a multipoint combustion system 100 for a gas turbine engine includes a housing 102 defining a pressure vessel.
  • a master injector 124 is mounted to the housing 102 for injecting fuel in an injection plume along a central axis A defined through the pressure vessel.
  • a plurality of slave injectors 112 are each disposed outward of and substantially parallel to master injector 124 for injecting fuel and air in an ignition plume radially outward of fuel injected through master injector 124.
  • Master injector 124 and slave injectors 112 are configured and adapted so the injection plume of the master injector intersects with the ignition plumes of slave injectors 112.
  • Each of the slave injectors 112 is an injector for a low-calorific value fuel as described below.
  • a primary manifold 114 is included within the pressure vessel for distributing fuel, e.g., low-calorific value gaseous fuel, to slave injectors 112.
  • An auxiliary manifold 116 is in fluid communication with the auxiliary nozzles 113 of slave injectors 112 for issuing an auxiliary flow of fuel, e.g., liquid fuel used for starting the ignition sequence of system 100, from auxiliary nozzles 113.
  • Auxiliary manifold 116 provides for a separate fuel flow from the fuel flow of primary manifold 114.
  • the pressure vessel of housing 102 includes a pressure dome 108 with a central aperture and a central inlet fitting 118 mounted to the central aperture of the pressure dome 108.
  • Auxiliary manifold 116 is external to pressure dome 108.
  • the primary and auxiliary manifolds 114 and 116 are advantageously thermally isolated from one another.
  • the auxiliary nozzle 113 of each respective slave injector 112 is mounted to the pressure vessel, namely at pressure dome 108, with floating seals 120 to accommodate thermal expansion differentials between the pressure vessel and auxiliary manifold 116.
  • Auxiliary manifold 116 is advantageously flexible, e.g., for ease of installation and to accommodate thermal expansion differentials.
  • auxiliary manifold 116 can be a high temperature hose or other suitable conduit with flexibility.
  • Auxiliary manifold 116 is configured to issue natural gas and/or liquid fuel to auxiliary nozzles 113 of slave injectors 112, or any other suitable type of liquid or gaseous fuel.
  • Auxiliary manifold 116 is operatively connected to an external valve 122, which can be opened to permit purging of auxiliary manifold 116 and auxiliary nozzles 113, for example with engine air, for complete shutdown of auxiliary manifold 116 and auxiliary nozzles 113.
  • auxiliary manifold 116 and nozzles 113 for startup of system 100
  • auxiliary manifold 116 and nozzles 113 can be purged to prevent stagnant liquid fuel from coking therein when system 100 is operating at full operational temperatures.
  • Slave injectors 112 are configured for use in low-calorific value fuel combustion systems as described above.
  • Each slave injector 112 includes a nozzle body 126 defining a fuel circuit 128 for injecting low-calorific value fuel.
  • An auxiliary nozzle 113 is mounted to nozzle body 126 and defines a fuel circuit 130 for injecting an auxiliary fuel, for example natural gas or liquid fuel, such as for use in engine startup.
  • Each auxiliary nozzle 113 is mounted to the respective nozzle body 126 with a floating seal 132, which can be for example a grommet, to accommodate a differential in thermal expansion between auxiliary nozzle 113 and nozzle body 126, e.g., when cold liquid fuel is flowing through auxiliary circuit 130, but the overall system is heating up during startup.
  • the auxiliary stage is more suitable than the primary stage for bringing an engine up to power due to the small passage size and relatively high back pressure of the auxiliary stage.
  • the auxiliary stage can be turned down to pilot the LCV fuel operation, or could be flushed and shut down for long term LCV operation using valve 122.
  • Fuel circuit 128 of nozzle body 126 is annular and nozzle body 126 defines an outer air circuit 134 outboard of fuel circuit 128.
  • Each auxiliary nozzle 113 advantageously includes a fuel outlet 136 configured and adapted to issue a spray of fuel that diverges away from a longitudinal axis defined by the auxiliary nozzle 113.
  • Nozzle body 126 includes an inner wall 138 and an outer wall 140 outboard of and spaced apart from inner wall 138.
  • Fuel circuit 128 of nozzle body 126 passes through, e.g., between, inner and outer walls 138 and 140.
  • Outer wall 140 defines at least one aperture 142 configured for passage of fuel from primary manifold 114 into nozzle body 126 for selective injection of natural gas and LCV fuel gas in a proportional mix, for example.
  • Auxiliary nozzle 113 is inboard of and spaced apart from inner wall 138 of nozzle body 126.
  • Nozzle body 126 and auxiliary nozzle 113 define a common longitudinal axis B.
  • Auxiliary nozzle 113 defines outlet 136 as described above, and nozzle body 126 includes fuel outlet 144.
  • Fuel outlet 136 of auxiliary nozzle 113 is upstream relative to outlet 144 of nozzle body 126 along longitudinal axis B.
  • an injector for a low-calorific value fuel combustion system comprising: a nozzle body defining a fuel circuit for injecting low-calorific value fuel; and an auxiliary nozzle mounted to the nozzle body and defining a fuel circuit for injecting at least one of natural gas and liquid fuel, wherein the nozzle body includes an inner wall and an outer wall outboard of and spaced apart from the inner wall, wherein the fuel circuit of the nozzle body passes through the inner and outer walls, wherein the auxiliary nozzle is inboard of and spaced apart from the inner wall of the nozzle body, wherein the nozzle body and auxiliary nozzle define a common longitudinal axis, wherein the auxiliary nozzle and nozzle body each include a respective fuel outlet, wherein the fuel outlet of the auxiliary nozzle is upstream relative to the outlet of the nozzle body along the longitudinal axis, and wherein the auxiliary nozzle includes a fuel outlet configured and adapted to issue a spray of fuel that diverges away from

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Fuel-Injection Apparatus (AREA)
EP13187920.7A 2012-10-09 2013-10-09 Mehrpunktinjektoren mit Hilfsstufe Withdrawn EP2719953A3 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/647,867 US9003804B2 (en) 2010-11-24 2012-10-09 Multipoint injectors with auxiliary stage

Publications (2)

Publication Number Publication Date
EP2719953A2 true EP2719953A2 (de) 2014-04-16
EP2719953A3 EP2719953A3 (de) 2018-01-03

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13187920.7A Withdrawn EP2719953A3 (de) 2012-10-09 2013-10-09 Mehrpunktinjektoren mit Hilfsstufe

Country Status (1)

Country Link
EP (1) EP2719953A3 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3182014A1 (de) * 2015-12-16 2017-06-21 Delavan, Inc. Injektoranschlussstücke

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5359847B1 (en) * 1993-06-01 1996-04-09 Westinghouse Electric Corp Dual fuel ultra-flow nox combustor
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US6405536B1 (en) * 2000-03-27 2002-06-18 Wu-Chi Ho Gas turbine combustor burning LBTU fuel gas
US8220272B2 (en) * 2008-12-04 2012-07-17 General Electric Company Combustor housing for combustion of low-BTU fuel gases and methods of making and using the same
US20100170253A1 (en) * 2009-01-07 2010-07-08 General Electric Company Method and apparatus for fuel injection in a turbine engine
US8899048B2 (en) * 2010-11-24 2014-12-02 Delavan Inc. Low calorific value fuel combustion systems for gas turbine engines

Non-Patent Citations (1)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3182014A1 (de) * 2015-12-16 2017-06-21 Delavan, Inc. Injektoranschlussstücke
US10436448B2 (en) 2015-12-16 2019-10-08 Delavan Inc. Injector fittings

Also Published As

Publication number Publication date
EP2719953A3 (de) 2018-01-03

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