EP4414609A1 - Distributeur de carburant à plaque perforée avec dispositif de tourbillonnement simplifié - Google Patents

Distributeur de carburant à plaque perforée avec dispositif de tourbillonnement simplifié Download PDF

Info

Publication number
EP4414609A1
EP4414609A1 EP24156411.1A EP24156411A EP4414609A1 EP 4414609 A1 EP4414609 A1 EP 4414609A1 EP 24156411 A EP24156411 A EP 24156411A EP 4414609 A1 EP4414609 A1 EP 4414609A1
Authority
EP
European Patent Office
Prior art keywords
fuel
tubular element
fuel nozzle
swirler
holes
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.)
Pending
Application number
EP24156411.1A
Other languages
German (de)
English (en)
Inventor
Kian Mccaldon
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.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
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 Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of EP4414609A1 publication Critical patent/EP4414609A1/fr
Pending 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

  • the present invention relates to fuel distribution and, in particular, to a perforated plate fuel distributor with a simplified swirler.
  • a fuel nozzle for a turbine engine using hydrogen fuel includes a tubular element, a perforated fuel distributor disposed along the tubular element and comprising a plate body defining holes and a swirler element abuttable with an end wall of a combustor of the turbine engine.
  • the swirler element includes an inner swirler body formed to define a swirl area receptive of hydrogen fuel from the tubular element via the holes and an outer swirler body disposed about the inner swirler body and formed to define openings through which fluid flows radially into the swirl area to mix with the hydrogen fuel prior to flowing into the combustor.
  • the fuel nozzle further includes at least one of a valve at an upstream end of the tubular element to selectively block hydrogen fuel flow through the tubular element and an orifice at an upstream end of the tubular element to control hydrogen fuel flow through the tubular element.
  • At least one of the perforated fuel distributor and the swirler element includes at least one of metallic materials and ceramic materials.
  • the fuel nozzle further includes a thermal coating on at least the holes.
  • the holes are counter-angled relative to the openings of the outer swirler body.
  • the holes are non-uniformly distributed across a plane of the plate body.
  • one or more of the holes are tapered.
  • the openings of the outer swirler body are at least one of vane openings and holes.
  • a fuel nozzle for a turbine engine using hydrogen fuel includes a tubular element, a radial fuel distributor disposed along the tubular element and comprising a plate body defining one or more circumferential apertures and a swirler element abuttable with an end wall of a combustor of the turbine engine.
  • the swirler element includes an inner swirler body formed to define a swirl area receptive of hydrogen fuel from the tubular element via the one or more circumferential apertures and an outer swirler body disposed about the inner swirler body and formed to define openings through which fluid flows radially into the swirl area to mix with the hydrogen fuel prior to flowing into the combustor.
  • the fuel nozzle further includes at least one of a valve at an upstream end of the tubular element to selectively block hydrogen fuel flow through the tubular element and an orifice at an upstream end of the tubular element to control hydrogen fuel flow through the tubular element.
  • At least one of the radial fuel distributor and the swirler element includes at least one of metallic materials and ceramic materials.
  • the fuel nozzle further includes a thermal coating on at least the one or more circumferential apertures.
  • the one or more circumferential apertures are pointed radially outwardly.
  • the one or more circumferential apertures are pointed radially inwardly.
  • the openings of the outer swirler body are at least one of vane openings and holes.
  • a fuel nozzle for a turbine engine using hydrogen fuel includes a tubular element, a foamed fuel distributor disposed along the tubular element and a swirler element abuttable with an end wall of a combustor of the turbine engine.
  • the swirler element includes an inner swirler body formed to define a swirl area receptive of hydrogen fuel from the tubular element through the foamed fuel distributor and an outer swirler body disposed about the inner swirler body and formed to define openings through which fluid flows radially into the swirl area to mix with the hydrogen fuel prior to flowing into the combustor.
  • the fuel nozzle further includes at least one of a valve at an upstream end of the tubular element to selectively block hydrogen fuel flow through the tubular element and an orifice at an upstream end of the tubular element to control hydrogen fuel flow through the tubular element.
  • the foamed fuel distributor includes at least one or more of metallic foam, a ceramic foam and a polymeric foam.
  • the fuel nozzle further includes a thermal coating on at least the foamed fuel distributor.
  • the openings of the outer swirler body are at least one of vane openings and holes.
  • a fuel nozzle is proposed for use with a turbine engine in flight applications and other applications that is compatible with hydrogen as a fuel.
  • the fuel nozzle is flush with an end wall of a combustor and includes a tubular element leading to a perforated plate fuel distributor that distributes hydrogen fuel to a swirler area that abuts and is conformal with the end wall of the combustor.
  • a hole distribution and flow area are provided to obtain mixing and a correct pressure drop and to arrest flashback.
  • the swirler allows fluid to enter the swirler area through vanes or holes in a radial dimension with a circumferential component to mix with hydrogen fuel passing through the holes in the perforated plate fuel distributor prior to entering the combustor.
  • the perforated plate fuel distributor can be replaced by a rounded edge element or an element produced from metallic foam.
  • the fuel nozzle can be turned on or off selectively to achieve certain performance characteristics.
  • a fuel nozzle 101 is provided for a turbine engine that uses hydrogen fuel for combustion in a combustor 102 having an end wall 103.
  • the fuel nozzle 101 includes a tubular element 110, a perforated fuel distributor 120 and a swirler element 130.
  • the tubular element 110 can be a duct defining a flow path having an inlet 111 and an outlet 112 that connects to an interior of the combustor 102 by way of an opening in the end wall 103.
  • the perforated fuel distributor 120 is disposed along the tubular element 110 and includes a plate body 121.
  • the plate body 121 is formed to define holes 122.
  • the swirler element 130 is abuttable with the end wall 103.
  • the swirler element 130 includes an inner swirler body 131 and an outer swirler body 132.
  • the inner swirler body 131 is formed to define a swirl area 133.
  • the swirl areas 133 is receptive of hydrogen fuel from the tubular element 110 via the holes 122.
  • the outer swirler body 132 is disposed about the inner swirler body 131 and is formed to define openings 134 through which fluid flows radially into the swirl area 133 to mix with the hydrogen fuel prior to flowing into the combustor 102.
  • the fluid can be various types of combustible fluids including, but not limited to, air, oxygen and hydrogen and/or combinations thereof.
  • the openings 134 of the outer swirler body 132 can be provided as at least one of vane openings 134 1 that are generally elongate, and holes 134 2 that are generally annular.
  • At least one of the perforated fuel distributor 120 and the swirler element 130 includes at least one of metallic materials and ceramic materials (e.g., ceramic matrix composite materials).
  • the fuel nozzle 101 can further include a thermal coating 160, such as thermal barrier coating (TBC), on at least the surfaces of the holes 122.
  • TBC thermal barrier coating
  • the TBC can be designed to prevent or inhibit hydrogen embrittlement, for example, and can be applied using various processes such as chemical vapor deposition (CVD) or other similar processes.
  • the fuel nozzle 101 can further include at least one of a valve 140 (see FIG. 2 ) and an orifice 150 (see FIG. 3 ).
  • the valve 140 and the orifice 150 may be combined.
  • the orifice 150 may be used to adjust the flow capacity of the fuel nozzle 101 to obtain the desired fuel distribution within the engine.
  • the valve 140 can be disposed at an upstream end (i.e., the inlet 111) of the tubular element 110 to selectively permit, adjust or block hydrogen fuel flow through the tubular element 110.
  • FIG. 2 the valve 140 can be disposed at an upstream end (i.e., the inlet 111) of the tubular element 110 to selectively permit, adjust or block hydrogen fuel flow through the tubular element 110.
  • the orifice 150 can be disposed at the upstream end (i.e., the inlet 111) of the tubular element 110 to control hydrogen fuel flow through the tubular element 110. At least the orifice 150 can be aimed to encourage hydrogen flow at a given angle through the tubular element 110, especially in a case in which the tubular element 110 is curved or bent as in FIG. 1 . For example, in a case in which the tubular element 110 is bent as in FIG. 1 , the orifice 150 can be aimed toward an outside of the bend to promote laminar hydrogen flow toward the perforated fuel distributor 120.
  • the holes 122 can be counter-angled relative to the openings 134 of the outer swirler body 130 (see FIG. 4 ), the holes 122 can be non-uniformly distributed across a plane P of the plate body 121 (see FIG. 5 ) and one or more of the holes 122 can be tapered (see FIG. 6 ).
  • the holes 122 can be counter-angled in a counter-clockwise direction 402. In this way, as hydrogen fuel passes through the holes 122, mixing of the clockwise flowing fluid and the counter-clockwise flow of hydrogen fuel can be increased. As shown in FIG.
  • the holes 122 can be arranged in concentric rows around a centerline of the plate body 121 (see FIG. 1 ) but can also be non-uniformly distributed toward one or more sides.
  • a greater number of holes 122 can be provided on the side of the plate body 121 closest to the outside of the bend to form a non-uniform distribution 501 at a location where most of the hydrogen fuel flow will be located as it completes its flow around the bend in the tubular element 110.
  • one or more of the holes 122 can be tapered in either the upstream or downstream direction.
  • the holes 122 can exhibit an inward tapering 601 toward the swirl area 133.
  • a fuel nozzle 701 is provided and is generally similar to the fuel nozzle 101 with the primary difference being that the fuel nozzle 701 includes a radial fuel distributor 710 instead of the flat plate perforated fuel distributor 120 described above.
  • the radial fuel distributor 701 may be envisioned.
  • FIG. 7 describes a conical shape
  • FIGS. 8A and 8B and FIG. 9 describe a cylindrical shape.
  • a variation of the conical distributor is also envisioned, where the shape of the distributor is defined according to the local fuel and air flows within the nozzle.
  • the radial fuel distributor 710 is disposed along the tubular element 110 and includes a plate body 711 that defines one or more circumferential apertures 712.
  • the one or more circumferential apertures 712 can be, but are not required to be, generally disposed at a periphery of the plate body 711 and are configured to allow hydrogen fuel to flow through to the swirl area 133.
  • the one or more circumferential apertures 712 can point radially outwardly with decreasing distance to the swirl area 133 so that the circumferential apertures direct flow with an outward radial component (see FIG.
  • each of the one or more circumferential apertures 712 can have a circumferential taper to thereby impart a swirling effect to the flow of the hydrogen fuel. It is to be understood that the thermal coating 160 and the embodiments of FIGS. 2 and 3 can be incorporated into the fuel nozzle 701.
  • a fuel nozzle 1001 is provided and is generally similar to the fuel nozzles 101 and 701 with the primary difference being that the fuel nozzle 1001 includes a foamed fuel distributor 1010 instead of the perforated fuel distributor 120 or the radial fuel distributor 710 described above.
  • the foamed fuel distributor 1010 is disposed along the tubular element 110 and can be formed of at least one or more of metallic foam, a ceramic foam and a polymeric foam. It is to be understood that the thermal coating 160 and the embodiments of FIGS. 2 and 3 can be incorporated into the fuel nozzle 1001.
  • the various embodiments described herein can be generally interchangeable with one another without undue experimentation.
  • the counter-angled holes 122 of FIG. 4 can be non-uniformly distributed as shown in FIG. 5 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Spray-Type Burners (AREA)
EP24156411.1A 2023-02-07 2024-02-07 Distributeur de carburant à plaque perforée avec dispositif de tourbillonnement simplifié Pending EP4414609A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US18/165,813 US20240263792A1 (en) 2023-02-07 2023-02-07 Perforated plate fuel distributor with simiplified swirler

Publications (1)

Publication Number Publication Date
EP4414609A1 true EP4414609A1 (fr) 2024-08-14

Family

ID=89854374

Family Applications (1)

Application Number Title Priority Date Filing Date
EP24156411.1A Pending EP4414609A1 (fr) 2023-02-07 2024-02-07 Distributeur de carburant à plaque perforée avec dispositif de tourbillonnement simplifié

Country Status (3)

Country Link
US (2) US20240263792A1 (fr)
EP (1) EP4414609A1 (fr)
CA (1) CA3228339A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0673490B1 (fr) * 1993-10-19 1997-12-29 European Gas Turbines Limited Injecteur de carburant
US6684640B2 (en) * 2000-10-23 2004-02-03 Alstom Power N.V. Gas turbine engine combustion system
US7065972B2 (en) * 2004-05-21 2006-06-27 Honeywell International, Inc. Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions
US20100126176A1 (en) * 2008-11-26 2010-05-27 Ik Soo Kim Dual swirler
US20120186256A1 (en) * 2011-01-26 2012-07-26 United Technologies Corporation Mixer assembly for a gas turbine engine
US20150033752A1 (en) * 2012-03-13 2015-02-05 Siemens Aktiengesellschaft Gas turbine combustion system and method of flame stabilization in such a system
US20170211807A1 (en) * 2014-04-07 2017-07-27 Siemens Aktiengesellschaft A burner tip and a burner for a gas turbine
US20190162414A1 (en) * 2016-06-30 2019-05-30 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor
GB2593123A (en) * 2019-06-25 2021-09-22 Siemens Ag Combustor for a gas turbine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0673490B1 (fr) * 1993-10-19 1997-12-29 European Gas Turbines Limited Injecteur de carburant
US6684640B2 (en) * 2000-10-23 2004-02-03 Alstom Power N.V. Gas turbine engine combustion system
US7065972B2 (en) * 2004-05-21 2006-06-27 Honeywell International, Inc. Fuel-air mixing apparatus for reducing gas turbine combustor exhaust emissions
US20100126176A1 (en) * 2008-11-26 2010-05-27 Ik Soo Kim Dual swirler
US20120186256A1 (en) * 2011-01-26 2012-07-26 United Technologies Corporation Mixer assembly for a gas turbine engine
US20150033752A1 (en) * 2012-03-13 2015-02-05 Siemens Aktiengesellschaft Gas turbine combustion system and method of flame stabilization in such a system
US20170211807A1 (en) * 2014-04-07 2017-07-27 Siemens Aktiengesellschaft A burner tip and a burner for a gas turbine
US20190162414A1 (en) * 2016-06-30 2019-05-30 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor
GB2593123A (en) * 2019-06-25 2021-09-22 Siemens Ag Combustor for a gas turbine

Also Published As

Publication number Publication date
CA3228339A1 (en) 2025-04-10
US20240263792A1 (en) 2024-08-08
US20260043546A1 (en) 2026-02-12

Similar Documents

Publication Publication Date Title
US11655979B2 (en) Airblast fuel nozzle
US11002190B2 (en) Segmented annular combustion system
US10184665B2 (en) Prefilming air blast (PAB) pilot having annular splitter surrounding a pilot fuel injector
EP2375163B1 (fr) Distributeur de carburant quaternaire à collecteur-bague annulaire segmentée
US20120125004A1 (en) Combustor premixer
US9927126B2 (en) Prefilming air blast (PAB) pilot for low emissions combustors
US9939157B2 (en) Hybrid air blast fuel nozzle
EP2218966B1 (fr) Injection de combustible pour chambres de combustion de turbine à gaz
US20140291418A1 (en) Multi-circuit airblast fuel nozzle
US20110271682A1 (en) Device for injecting a mixture of air and fuel into a turbomachine combustion chamber
US20170268786A1 (en) Axially staged fuel injector assembly
CN102261673A (zh) 用于燃气轮机燃烧器的混合式双燃料喷嘴
EP4202302B1 (fr) Buse de combustible et tourbillonneur
HUP0203137A2 (en) Atomizing burner
US11680527B2 (en) Nozzles with internal manifolding
EP4414609A1 (fr) Distributeur de carburant à plaque perforée avec dispositif de tourbillonnement simplifié
US20150020501A1 (en) An annular combustion chamber in a turbine engine
US20250383090A1 (en) Injector assembly for an engine, and aircraft
US20260063299A1 (en) Burner for combustor with ammonia injection downstream of swozzle assembly and related method

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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 ME MK MT NL NO PL PT RO RS SE SI SK SM TR

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20250213