EP2314923A2 - Tourbillonneur - Google Patents

Tourbillonneur Download PDF

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Publication number
EP2314923A2
EP2314923A2 EP10171361A EP10171361A EP2314923A2 EP 2314923 A2 EP2314923 A2 EP 2314923A2 EP 10171361 A EP10171361 A EP 10171361A EP 10171361 A EP10171361 A EP 10171361A EP 2314923 A2 EP2314923 A2 EP 2314923A2
Authority
EP
European Patent Office
Prior art keywords
swirl generator
fuel
fuel injector
segment
insert
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.)
Granted
Application number
EP10171361A
Other languages
German (de)
English (en)
Other versions
EP2314923B1 (fr
EP2314923A3 (fr
Inventor
Holger Dr. Huitenga
Jaman El Masalme
Emil Aschenbruck
Reiner Brinkmann
Eric Norster
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.)
Everllence SE
Original Assignee
MAN Diesel and Turbo SE
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 MAN Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2314923A2 publication Critical patent/EP2314923A2/fr
Publication of EP2314923A3 publication Critical patent/EP2314923A3/fr
Application granted granted Critical
Publication of EP2314923B1 publication Critical patent/EP2314923B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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

Definitions

  • the present invention relates to a swirl generator and a method for injecting fuel into a gas turbine.
  • the WO 2004/057236 A2 for this purpose shows fuel outlets in an upstream cover of the swirl generator, the EP 1 890 083 A1 in a downstream bottom of the swirl generator.
  • the fuel outlets are formed in side channel walls of the swirler segments, the WO 2007/131818 A1 frontal fuel outlets in axial shoulders of the swirler segments.
  • a swirl generator according to the preamble of claim 1 with a plurality of pie-shaped swirl generator segments known, in each of which fuel-supplying and parallel air-supplying axial bores are formed.
  • the air supply hole communicates with a right-angled opening in this bore in a side wall of the channel defined by the swirler segment for injecting additional combustion air therein.
  • Into this larger bore is inserted a smaller diameter hollow tube which meets the fuel feeding axial bore at right angles so that fuel is injected into the channel through this fuel injector insert inside the annular supplemental air supply.
  • the fuel injection through the fuel outlets is always constructively determined.
  • the fuel injection and combustion air mixing dependent on the fuel injection is very sensitive, in particular with regard to the properties of the fuel gas, for example its composition, its density and its calorific value, as well as with regard to the air throughput which varies with different power outputs of the gas turbine.
  • the object of the present invention is therefore to improve the mixing of fuel with combustion air in a swirl generator of a gas turbine.
  • a swirl generator according to the preamble of claim 1 is further developed by its characterizing feature.
  • Claim 20 provides a method for injecting fuel by means of such a swirl generator into a gas turbine, claim 19, the gas turbine, the claims 15, 17 elements of a swirl generator according to the invention under protection.
  • the subclaims relate to advantageous developments.
  • the injection of fuel into a channel of a swirl generator of a gas turbine by the variable arrangement of fuel injector inserts in air-conducting swirler segments of the swirl generator is proposed.
  • the fuel injection can thus be adapted to different fuel properties or air flow rates.
  • a swirl generator segment optionally arranged in a swirl generator segment various types of fuel injector inserts which have different fuel outlets.
  • two fuel injector inserts that may alternatively be disposed in a swirler segment may differ in number, shape, size, location, and / or direction of one or more fuel outlets.
  • a plurality of fuel outlets of a fuel injector insert may be identical or different, spaced equidistantly or differently from one another in the direction of the channel height, and / or may be angularly offset from one another or disposed one upon the other on the shell surface of the fuel injector insert.
  • the fuel injector inserts with a predetermined orientation in the swirler segments receivable.
  • the fuel injector inserts in particular rotatably, preferably be received positively in the swirl generator segments.
  • fuel injection into the passage may also be dictated by the placement of the fuel injector insert in the swirler segment.
  • the fuel injector insert for example, rotationally symmetrical and arranged in a corresponding cavity of the swirl generator, where it can be fixed permanently or detachably, for example frictionally or cohesively, for example by welding, in any orientation or angular position about its axis of symmetry.
  • the fuel injector insert also have a rotationally symmetry-breaking geometry, so that it can be used only in one or more selected angular positions in the swirl generator segment.
  • Both aspects may be advantageously combined with one another by alternatively employing one of several different fuel injector inserts in one of several possible orientations in a swirler segment.
  • a fuel injector insert is disposed in one or more leading edges of a swirler segment.
  • a fuel injector insert can in particular be positively inserted into a recess, which is open towards the channel, in the leading edge of the swirl generator segment, so that the inlet contour of the channel or the leading edge of the swirl generator segment is at least partially formed by the fuel injector insert used.
  • the inlet contour of the channel can also be adapted to changed boundary conditions.
  • this leading edge may be made in a different material, namely that of the fuel injector insert, than the remainder of the swirler segment whose walls define the side surfaces of the channel.
  • a fuel injector insert is only partially, ie not taken over its entire lateral surface, in the swirl generator segment, wherein remaining areas of its lateral surface have fuel outlets and / or at least partially form an inlet edge of the swirl generator segment.
  • a fuel injector insert accommodated in a swirl generator segment is understood to mean, in particular, a fuel injector insert which is only partially accommodated in the swirl generator segment.
  • a fuel injector insert is interchangeably received in a swirler segment so as to dictate fuel injection into a conduit by reorientation or replacement with another fuel injector insert.
  • the replaceable fuel injector can be frictionally, for example, by screwing a lid on the swirl generator segment, or cohesively, for example, by welding the fuel injector with the swirl generator segment defined, the interchangeability is advantageously ensured in this case by forming predetermined breaking points of cohesive connection.
  • a fuel injector can be compared to him receiving swirler segment and / or a lid are sealed, in which a fuel supply line may be formed to the fuel injector insert.
  • a swirl generator for injecting fuel into a gas turbine comprises a plurality of swirler segments, between which channels for supplying swirling air to a combustion chamber Gas turbine are formed, wherein the swirler segments are arranged interchangeable in the swirl generator.
  • the swirl generator are adapted to different properties of the fuel gas or varying with different power outputs of the gas turbine air flow.
  • the present invention finds particular application in stationary gas turbines, radial swirl generators, and / or gaseous fuel injection.
  • Fig. 1 . 2 show one half of a radial swirl generator according to an embodiment of the present invention in transverse or axial section.
  • each rotationally symmetrical, outwardly open bores are formed.
  • the insert body can also be arranged deeper within the swirler segment, so that a larger part of its lateral surface is received in the complementary bore, which can then extend over more than a three-quarter circle.
  • the insert body may also be less deep be arranged in the swirl generator segment, so that a smaller part of its lateral surface is received in the complementary bore, which then extends correspondingly over less than a three-quarter circle.
  • a cover ring 10 in which the swirl generator segments 1.1, 1.2, 1.3 are integrally formed or materially or frictionally fixed in a modification, not shown, complementary circular recesses are formed with a flattened chord, so that the fuel injector inserts 2, 2 'only in one through the flat side 2.3 or 2.3 'predetermined orientation in the swirler segments 1.1, 1.2, 1.3 can be used. In this they are tacked by means of a detachable weld and are additionally sealed by metallic C-rings 60 against the cover ring 10.
  • a lid 20 of the swirl generator is screwed, in which an annular fuel feed line 50 is formed, which is to the insert heads 2.1 and 2.1 '(see. Fig. 3 ) is open to the fuel injector inserts.
  • screws 40 pass through the cover 20, the cover ring 10 and the swirl generator segments 1.1, 1.2, 1.3, and are screwed into a swirl generator floor 30, which together with the cover ring 10 and the side walls of the swirler segments 1.1, 1.2, 1.3 defines the air supply channels K, and in which the insert body 2.2 or 2.2 'of the fuel injector inserts 2 and 2' are inserted frontally (see. Fig. 2 ).
  • the lid 20 also secures the fuel injector inserts positively and frictionally.
  • the fuel injector inserts have an axial bore open towards the insert head (cf. Fig. 2 ) communicate with which radial bores 3.
  • Gaseous fuel which is supplied to the fuel injector inserts 2 via the fuel supply line 50, flows through the axial or axial bore in the insert head and is injected into the channel K through the radial bores 3 functioning as fuel outlets.
  • the position of the fuel outlets 3 relative to the flattening 2.3 or 2.3 'of the insert head 2.1 or 2.1' determines a Eindüsraum in cross-section, ie relative to the air flow L, when the fuel injector inserted into the swirler segment is.
  • the fuel outlets 3 are arranged relative to the flattening 2.3 of the insert head 2.1 such that the fuel B, as in Fig. 1 indicated, is injected with inserted fuel injector insert 2 substantially perpendicular to the air flow L.
  • the fuel outlets 3 ' are offset relative to the flattening 2.3' of the insert head 2.1 'in such a way that the injection direction of the fuel into the channel has a component which is oriented counter to the flow direction, ie radially outwards, if the fuel injector insert 2' instead of the Fuelsindüs tenues 2 with the predetermined by the flattening 2.3 'orientation in a swirler segment rotatably inserted and attached by welding.
  • This injection against the air flow of the combustion air can improve the mixing with the injected fuel, in particular with a lower air throughput by blocking points formed in the flow of the combustion air L upstream of the fuel outlets 3 '.
  • the fuel outlets 3, 3 ' differ not only in their angular position to the flattening 2.3 and 2.3', but also in their height, in which they are arranged in the channel K.
  • the fuel injection can be predetermined and adapted to changed properties of the fuel gas or a varying air throughput.
  • further fuel injector inserts may be inserted, which have fuel outlets of a different shape, number and / or outflow direction, and thus, for example, an in Fig. 2 implement non-horizontal Eindüsraum by the Brennstoffauslassachse forms with the longitudinal axis of the fuel injector insert a different angle from 90 °.
  • the recesses in the cover ring 10 for receiving the insert heads of the fuel injector inserts are completely rotationally symmetrical and thus allow a recording of the fuel injector inserts in the swirler segments with arbitrarily specifiable orientation relative to its longitudinal or symmetry axis.
  • the fuel injector inserts are rotated during or after insertion into the swirler segments so that their fuel outlets 3 and 3 'convey a desired Eindüsraum, and then, for example by welding with the cover ring 10 rotatably fixed in this angular position, the fuel injection can also in the desired Be given way.
  • the insert heads 2.1 and 2.1 'of the fuel injector inserts 2 and / or 2' and the receiving recesses in the cover ring 10 are formed so as to receive the fuel injector inserts in the swirler segments at various discrete angles from each other at an angle to allow orientation about its longitudinal axis.
  • the insert heads and they receiving recesses have a cross-section in the form of a regular polyhedron, such as a regular 36-corner, which allows each offset by 10 ° rotatable recordings.
  • the fuel injector inserts are disposed in the radially outer leading edges of the swirler segments. This advantageously combines a rounded channel inlet through the cylindrical insert body 2.2 or 2.2 'of the fuel injector inserts, a protection of the inserts against mechanical environmental influences, a favorable thermal loading of the inserts and a beneficial injection of the fuel on or - depending on the angular position - before the channel inlet , so that the entire channel is used as a mixing section.
  • the fuel injector inserts disposed in the entrance edges of a swirler segment thus advantageously form part of the surface of the swirler segment and thus equally allow compact integration of the fuel injector inserts into the swirler segments and the variation of their outer contour.
  • the insert body of a not shown further fuel injector insert as well as the insert head have a flattening in which the fuel outlets are formed.
  • swirler segments 1.1, 1.2, 1.3 screwed another cover ring with the cover 20 and the swirl generator floor 30, whose swirl generator segments are in the form of the channel side surfaces, the channel height, the arrangement of fuel injector inserts or the like of the in Fig. 1 . 2
  • the swirl generator segments 1.1, 1.2, 1.3 shown differ, the channel shape, height and / or number of the swirl generator can be varied as well as the fuel injection.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
EP10171361.8A 2009-10-23 2010-07-30 Tourbillonneur Active EP2314923B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009045950A DE102009045950A1 (de) 2009-10-23 2009-10-23 Drallerzeuger

Publications (3)

Publication Number Publication Date
EP2314923A2 true EP2314923A2 (fr) 2011-04-27
EP2314923A3 EP2314923A3 (fr) 2014-06-18
EP2314923B1 EP2314923B1 (fr) 2017-08-30

Family

ID=43011897

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10171361.8A Active EP2314923B1 (fr) 2009-10-23 2010-07-30 Tourbillonneur

Country Status (5)

Country Link
US (1) US20110094240A1 (fr)
EP (1) EP2314923B1 (fr)
JP (1) JP5520767B2 (fr)
CA (1) CA2714525C (fr)
DE (1) DE102009045950A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2942563A1 (fr) * 2014-05-09 2015-11-11 Siemens Aktiengesellschaft Élément de tourbillonnement d'un brûleur de moteur de turbine à gaz, brûleur de moteur de turbine à gaz et moteur de turbine à gaz

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DE102009054669A1 (de) * 2009-12-15 2011-06-16 Man Diesel & Turbo Se Brenner für eine Turbine
DE102011082884A1 (de) 2011-09-16 2013-03-21 Man Diesel & Turbo Se Brenner und Gasturbine mit einem solchen Brenner
US11149941B2 (en) * 2018-12-14 2021-10-19 Delavan Inc. Multipoint fuel injection for radial in-flow swirl premix gas fuel injectors
DE102018132766A1 (de) 2018-12-19 2020-06-25 Man Energy Solutions Se Drallerzeuger zur Einbringung von Brennstoff in eine Gasturbine
CN110594786B (zh) * 2019-10-29 2021-07-13 中国船舶重工集团公司第七0三研究所 一种混合分级超低排放燃烧器
CN116371235B (zh) * 2023-03-20 2026-01-23 中国石油化工股份有限公司 一种化学药剂混配装置
CN119042666B (zh) * 2024-07-02 2025-11-21 北京航空航天大学 一种采用多孔阵列排布的氢燃料微扩散分级燃烧室

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Publication number Priority date Publication date Assignee Title
EP0718550B1 (fr) 1994-12-19 2000-03-01 Asea Brown Boveri Ag Gicleur
EP0728989B1 (fr) 1995-01-13 2001-11-28 European Gas Turbines Limited Appareil de combustion pour moteur de turbine à gaz
EP0870989B1 (fr) 1997-04-10 2004-08-25 European Gas Turbines Limited Disposition d'injection de carburant pour une chambre de combustion de turbine à gaz
WO2004057236A2 (fr) 2002-12-23 2004-07-08 Bowman Power Systems Limited Dispositif de combustion
WO2007033876A1 (fr) 2005-09-24 2007-03-29 Siemens Aktiengesellschaft Dispositif de preparation d'un combustible pour combustion
WO2007093248A1 (fr) 2006-02-15 2007-08-23 Siemens Aktiengesellschaft Bruleur pour turbine a gaz et procede de melange de carburant et d'air dans une zone de tourbillon d'un bruleur pour turbine a gaz
WO2007131818A1 (fr) 2006-05-12 2007-11-22 Siemens Aktiengesellschaft Coupelle rotative destinée à être utilisée dans un brûleur d'un moteur à turbine à gaz
EP1890083A1 (fr) 2006-08-16 2008-02-20 Siemens Aktiengesellschaft Injecteur de carburant pour une turbine à gaz
EP1892469A1 (fr) 2006-08-16 2008-02-27 Siemens Aktiengesellschaft Passage de tourbillonneur et brûleur pour une turbine à gaz
WO2008141955A1 (fr) 2007-05-18 2008-11-27 Siemens Aktiengesellschaft Distributeur de combustible

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2942563A1 (fr) * 2014-05-09 2015-11-11 Siemens Aktiengesellschaft Élément de tourbillonnement d'un brûleur de moteur de turbine à gaz, brûleur de moteur de turbine à gaz et moteur de turbine à gaz
WO2015169930A1 (fr) * 2014-05-09 2015-11-12 Siemens Aktiengesellschaft Coupelle rotative pour brûleur de turbine à gaz, brûleur de turbine à gaz et turbine à gaz
CN106461228A (zh) * 2014-05-09 2017-02-22 西门子股份公司 用于燃气涡轮发动机的燃烧器的旋流器、燃气涡轮发动机的燃烧器以及燃气涡轮发动机

Also Published As

Publication number Publication date
EP2314923B1 (fr) 2017-08-30
EP2314923A3 (fr) 2014-06-18
JP5520767B2 (ja) 2014-06-11
US20110094240A1 (en) 2011-04-28
CA2714525A1 (fr) 2011-04-23
CA2714525C (fr) 2012-04-17
DE102009045950A1 (de) 2011-04-28
JP2011089759A (ja) 2011-05-06

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