EP1943464A1 - Fuel lance - Google Patents

Fuel lance

Info

Publication number
EP1943464A1
EP1943464A1 EP20060819090 EP06819090A EP1943464A1 EP 1943464 A1 EP1943464 A1 EP 1943464A1 EP 20060819090 EP20060819090 EP 20060819090 EP 06819090 A EP06819090 A EP 06819090A EP 1943464 A1 EP1943464 A1 EP 1943464A1
Authority
EP
European Patent Office
Prior art keywords
fuel
lance
head
lance head
arranged
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Withdrawn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
EP20060819090
Other languages
German (de)
French (fr)
Inventor
Thomas Ruck
Christian Steinbach
Martin Von Planta
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 Technology GmbH
Original Assignee
General Electric Technology GmbH
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 to CH17692005 priority Critical
Application filed by General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to PCT/EP2006/067525 priority patent/WO2007051705A1/en
Publication of EP1943464A1 publication Critical patent/EP1943464A1/en
Application status is Withdrawn legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23DBURNERS
    • F23D14/00Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021Details of lances

Abstract

The invention relates to a lance (3) for introducing a fuel into a mixing path (2) of a burner (1), in particular of a turbine plant, which is provided with a swirl generator for generating a swirling combustion air flow, comprising a lance head (5), a fuel supply (8) and an oxidant supply (10). According to the invention, the lance head (5) projects into the mixing path (2), has at least one fuel nozzle (6) for injecting the fuel into the mixing path (2) and has least one oxidant outlet opening (7) for introducing an oxidant into the mixing path (2). The fuel supply (8) runs in the lance (3) and is connected to the at least one fuel nozzle (6). The oxidant supply (10) runs in the lance head (5) and is connected to the at least one oxidant outlet opening (7). In order to improve the operation of the burner (1), the at least one oxidant outlet opening (7) is arranged centrally on the lance head (5), and the at least one fuel nozzle (6) is arranged on the lance head (5) so as to be offset radially outward in relation to the at least one oxidant outlet opening (7).

Description

fuel lance

technical field

The invention relates to a lance for introducing a fuel into a combustion chamber of a burner provided with a swirl generator, in particular a turbine plant having the features of the preamble of claim 1.

State of the art

From DE 100 50 248 A1, such a lance for consisting essentially of a swirl generator for generating a wire combustion air stream and of means for introducing at least a quantity of fuel in this combustion air stream burner is known, which comprises a lance head, a fuel supply and an oxidizer. The lance head protrudes into the combustion chamber in the assembled state, has a central fuel nozzle for injecting the fuel into the combustion chamber and also has an oxidator for introducing the oxidant into the combustion room. The fuel supply of the lance extends into and is connected to the fuel nozzle. The oxidator extends in the lance head and is connected to the oxidator. In the known lance the fuel nozzle on the lance head is arranged centrally, so that the fuel eindüste coaxially to the longitudinal axis of the lance enters the combustion chamber. The oxidator is of annular configuration and surrounds the fuel nozzle coaxially. The oxidizer also occurs axially from the lance head and envelops the injected fuel. The additionally introduced into the combustion chamber via the lance head oxidizer, usually air is required for cooling and rinsing of the lance head.

In the process known from DE 100 50 248 A1 burner with swirl generator a negative pressure so that there is in the center of a powerful suction, which is of great importance for the burner momentum is being built on the axis.

For larger such burners, so in burners with higher power or greater fuel conversion, it has been found that the introduction of the fuel via the lance at a comparatively poor mixing and thus result in relatively unfavorable combustion reactions with increased pollutant emission.

Summary of the Invention

The invention aims to provide a remedy. The invention, as characterized in the claims, is concerned with the problem of providing an improved embodiment for a lance of the type mentioned, which is characterized in particular by an improved fuel injector.

According to the invention this problem is solved by the subject matter of the independent claim. Advantageous embodiments are subject of the dependent claims. The invention is based on the general idea which is at least to arrange a oxidator on the lance head centrally and to arrange the at least one fuel nozzle radially offset to the outside. The injection of the fuel thus occurs on a relatively large radius relative to the longitudinal central axis of the lance. In addition, the injection of the fuel takes place radially outwardly of the centrally via the lance supplied oxidant. The two media (oxidant / fuel) are thereby deflected past each other by means of crossing Verteilbohrungssysteme.

It has been shown that these measures lead to improved mixture formation and improved combustion reaction and thus reduced emissions. At the same time, however, the cooling and flushing function of the centrally supplied oxidizer is maintained.

Accordingly, preferred embodiments can have a lance extending in the fuel line, the fuel supply. Furthermore, it can be provided is arranged in the lance head annular fuel channel to which the one hand, a fuel nozzle is connected at least and the other hand is connected via fuel channels connecting to the fuel line. By this design, the at least one fuel nozzle can move particularly far radially outward as the fuel channels can designing so that they can connect the centrally arranged fuel line to the fuel ring channel which can virtually have an arbitrarily large radius. Instead of a common fuel annular channel and a plurality of separate supply channels may be provided which each connect one of the fuel nozzles with a compound of the fuel channels. also embodiments wherein the oxidizer comprises a centrally arranged in the lance head Oxidatorraum whose open end towards the combustion chamber forms the oxidator are advantageous. Furthermore, several Oxidatorverbindungskanäle may be provided which connect the Oxidatorraum each provided with a radially outwardly disposed on the lance head Oxidatoreinlassöffnung. With the aid of a relatively large Oxidatorraums pressurized with the oxidant surface is provided inside the lance head, improving the cooling effect of the oxidator.

Further important features and advantages of the invention will be apparent from the dependent claims, from the drawings and from the associated description of the figures of the drawing.

Brief Description of Drawings

Two preferred embodiments of the invention are illustrated in the drawings and are explained in more detail in the following description.

Show it.

Fig. 1 is a simplified axial section through a flask equipped with a lance and a swirl generator in the region of the burner lance head in a first embodiment of the invention, and

Fig. 2 is a simplified axial section through a flask equipped with a lance and a swirl generator in the region of the burner lance head in a second embodiment of the invention. Ways of carrying out the invention

According to Fig. 1 comprises a burner 1, shown only partially, which is equipped with a not shown swirl generator for generating a wire combustion air stream, a mixing section 2, which leads to a not-shown combustion chamber. This mixing section 2 can also be called a combustion chamber. The burner 1 can be a component of a turbine installation, in particular a gas turbine plant. The burner 1 is provided in the example shown here, the intake-side head portion having a lance 3 by means of which a fuel can be introduced into the mixing path. 2 As is known, such lances separate components, which are slidably disposed in the burner and, if necessary can be pulled out relatively easily.

The lance 3 has a lance shaft 4, and a lance head 5, which is attached to the burner 1 associated end arranged or formed on the lance shank. 4 In the illustrated assembled state of the lance head 5 extends into the mixing section. 2 the embodiment shown here, in which the lance 3 and the burner 1 are arranged coaxially with one another so that the lance head 5 extends coaxially in the mixing section 2 thereby being preferred.

The lance head 5 comprises at least one fuel nozzle 6 can be injects into the mixing section 2 with the aid of the fuel. Preferably, the lance head 5 has a plurality of such fuel nozzles 6, of which only one is visible in Fig. 1 due to the selected sectional plane. The fuel nozzles 6 are distributed in the circumferential direction and circumferentially spaced from each other on the lance head 5 is arranged. For example, the lance head 5 is equipped with four such fuel nozzles 6, which are arranged offset in the circumferential direction by 90 ° to each other. Further, the lance head 5 is equipped with at least one oxidator 7, by which an oxidizing agent can be introduced into the mixing path. 2 Preferably, only a single such oxidator 7 is provided.

When fuel is preferably a liquid fuel such as fuel oil. Likewise, it may, be a gaseous fuel such as natural gas. When oxidant is preferably a gaseous oxidizer, usually air.

The lance 3 is also equipped with a fuel supply 8 which is connected to the fuel nozzles. 6 The fuel supply 8 runs within the lance 3 and is connected in the assembled state to an external fuel supply 9, which is symbolized in Fig. 1 by an arrow. 3 further comprises the lance an oxidizer 10. The oxidizer 10 is connected to the oxidator 7 and runs inside the lance head 5. In the mounted state, the oxidizer 10 is connected to an external Oxidatorversorgung 11, which is symbolized by an arrow, and, for example, at least includes an axis extending in the burner 1 Oxidatorleitung 12th

The lance 3 shown here has the special feature that the oxidator 7 is arranged centrally on the lance head. 5 In this way, the oxidizer in operation coaxially to the longitudinal central axis 13 of the lance 3 in the mixing section 2 can be introduced. Further, the fuel nozzle 6 with respect to the oxidator 7 offset radially outwards on the lance head 5 is arranged in the embodiment shown here lance. 3 In this way, the fuel in operation at a relatively large radius in the combustion chamber 2 can be injected. Thus, the further is the location of the fuel injection in any case radially outside the centrally supplied oxidant. The injection of the fuel itself is carried out at said location then preferably at an angle in the radial and tangential direction, which will be explained in more detail below.

This design has several advantages. On the one supplied via the lance 3 oxidizer to fulfill its cooling function and cleaning function. On the other hand, the introduced for cooling and cleaning through the lance head 5 oxidizer does not affect the fuel injection. In addition, the radially outer fuel injection takes place resulting in an improved mixing with a Hauptoxidatorstrom, which is introduced at point not shown in the mixing section. 2

The fuel supply 8 includes in the preferred embodiment shown here a fuel line 14 extending in the lance. 3 For this purpose the lance shaft 4 is configured as a tube. The fuel line 14 is connected to the fuel supply. 9 In addition, the fuel supplier may include a fuel annular channel 15 8 that is arranged in the lance head. 5 The fuel annular channel 15 is connected to the fuel nozzles. 6 Furthermore, the annular fuel passage 15 extends coaxially to the longitudinal central axis 13 of the lance 3. It is worth noting that the annular fuel passage 15 having a larger diameter than the fuel line 14 and as the lance shaft 4. In place of all fuel nozzles 6 together associated fuel annular channel 15 and a plurality of axially extending supply channels or bores may be provided which are each connected to one of the fuel nozzles. 6 These supply channels can even out the flow to the respective fuel nozzle 6 and avoid so-called dead water regions near the fuel nozzle 6, which simplifies the flushing when switching off the fuel supply. Furthermore, the fuel supply may 8 more

Fuel connection channels 16 have. These fuel connection channels 16 are arranged in the lance head 5, in a transition portion 17 with which the lance head 5 passes into the lance shank. 4 This transitional portion 17 is a conical shape here and has a decreasing to the lance shaft 4 in cross-section. By means of the conical transition portion 17 ensures that the lance head 5 outside the transition portion 17 has a significantly larger outside cross-section than the lance shaft 4. This can be achieved for the positioning of the fuel nozzles 6, a particularly large radius or distance from the longitudinal central axis. 13

The fuel connection channels 16 extend from the centrally disposed fuel pipe 14 axially as well as radially outwardly until the annular fuel passage 15. Preferably, a plurality, for example three, fuel connection channels 16 are provided in order to supply the fuel annular channel 15 with sufficient fuel. In principle, a single fuel communication passage 16 may be sufficient. Provided that instead of the common fuel annular channel 15, the above-mentioned separate supply channels or bores are used, these are each connected to a connecting channel such fuel sixteenth

The oxidizer 10 preferably comprises a Oxidatorraum 18 having a to the mixing section 2 toward open axial end which forms the oxidator. 7 The Oxidatorraum 18 is arranged for this purpose in the lance head 5 centrally. In a circular oxidator 7 18 has the Oxidatorraum on a corresponding cylindrical portion, which adjoins the oxidator. 7 Furthermore, the Oxidatorraum 18 at the end remote from the oxidator 7 end at a truncated cone portion.

The oxidizer 10 also includes multiple Oxidatoreinlassöffnung 19, which are respectively arranged radially outside of the lance head 5, preferably at the transition region 17th This Oxidatoreinlassöffnungen 19 may be connected to the Oxidatorversorgung 11 for example via the Oxidatorleitungen 12th In addition, the oxidizer 10 includes a plurality Oxidatorverbindungskanäle 20, each of which connects one of the Oxidatoreinlassöffnungen 19 with the Oxidatorraum 18 and this open into the truncated conical portion. Also, the Oxidatorverbindungskanäle 20 are arranged in the lance head 5, and preferably in the transition portion 17th Here, the Oxidatorverbindungskanäle 20 of the respective outboard Oxidatoreinlassöffnung 19 extend axially and radially inwards towards the Oxidatorraum 18th

In the embodiment shown here this results in a constellation in which the fuel annular channel 15 surrounds the Oxidatorraum 18 coaxially results. In this way, the fuel in the lance head 5 is located radially outer than the oxidizer. The fuel channels 16 and the connection Oxidatorverbindungskanäle 20 are arranged in the lance head 5 so that they alternate in the circumferential direction. Conveniently, many Oxidatorverbindungskanäle 20 as fuel connection channels 16 are thus equal provided. In the lance head 5 or in the transition section 17, the guided radially from the inside to the outside of the fuel stream and guided radially from the outside inwards oxidant intersect, but in separate and mutually sealed channels 16, 20th

The lance head 5 is dimensioned in the example shown so that the radius at which the fuel nozzles 6 are arranged, is greater than the radius of the lance shaft 4. The fuel nozzles 6 are thus arranged radially further out than an outer cross section of the lance 3 outside of the lance head 5 . the fuel nozzles 6 may in principle be designed such that it as shown with respect to the axial direction of the lance inclined inject into the mixing section 2 the fuel 3. In addition, the fuel nozzle 6 can also be designed so as to inject the fuel towards a central longitudinal plane of the lance 3, so with respect to a longitudinal centerline axis 13 plane containing inclined in the mixing zone. 2 The fuel injection can thus be carried out approximately in the direction or in the opposite direction of a swirl flow, which is formed in the mixing section 2 by a corresponding tangential introduction of Hauptoxidatorströmung.

In the example shown, the lance head is assembled 5 of a base body 21 and a sleeve body 22nd For this purpose, the sleeve body is fitted onto the base body 21 coaxial with 22 and fixed thereto by means of welds 23rd

The embodiment according to Fig. 2 differs from that shown in Fig. 1 embodiment only in that the Oxidatorleitung 12 axially, that is disposed coaxially with the fuel supply 8 so that the air can flow axially. In the transition portion 17 of the lance head 5, the air is then directed from the outer diameter to the center of the lance, while the fuel (eg oil) is moved from the center to outer diameter. As with the first embodiment, the oxidizer and the fuel injection from the lance 3 in the mixing section 2 are realized on an almost identical plane, so that the axial Oxidatorzufuhr is completely enclosed with a fuel-conducting plenum.

LIST OF REFERENCE NUMBERS

burner

mixing section

lance

lance shaft

lance head

fuel nozzle

oxidator

fuel supply

fuel supply

oxidizer

Oxidatorversorgung

Oxidatorleitung

Longitudinal central axis 3

fuel line

Fuel annular channel

Fuel connecting passage

Transition section of 5

Oxidatorraum

Oxidatoreinlassöffnung

Oxidatorverbindungskanal

body

sleeve body

welded joint

Claims

claims
1. lance for introducing a fuel into a mixing section (2) of a burner provided with a swirl generator for generating a wire combustion air stream (1), especially a turbine system,
- with a lance head (5) which in the mounted state in the mixing section (2) protrude, having at least one fuel nozzle (6) for injecting the fuel into the mixing section (2) and the at least one oxidator (7) for introducing an oxidizer in the mixing section (2),
- extending a in the lance (3) fuel supply (8), which is connected to the at least one fuel nozzle (6),
- extending a in the lance head (5) oxidizer (10), which is connected to the at least one oxidator (7), characterized in
- the at least one oxidator (7) is arranged centrally on the lance head (5),
- that the at least one fuel nozzle (6) with respect to the at least one oxidator (7) offset radially outwards on the lance head (5) is arranged.
2. A lance according to claim 1, characterized in that
- that the fuel feed (8) in the lance (3) (14) extending fuel line, and / or - that the fuel supply (8) for each fuel nozzle (6) has a lance head (5) has arranged supply channel to which the respectively associated fuel nozzle (6) is connected, and / or
- that the fuel feed (8) arranged in a lance head (5) annular fuel channel (15) to which the at least one fuel nozzle (6) is connected, and / or
- that the fuel feed (8) comprises a plurality of fuel connecting channels (16) that connect the fuel ring channel (15) or the supply ducts to the fuel line (14).
3. A lance according to claim 1 or 2, characterized in that
- that the oxidizer (10) disposed centrally in a lance head (5) Oxidatorraum (18), of which the mixing section (2) open towards the end forms the oxidator (7), and / or
- that the oxidizer (10) comprises a plurality Oxidatorverbindungskanäle (20) connecting the Oxidatorraum (18) arranged in each case with a radially outside of the lance head (5) Oxidatoreinlassöffnung (19).
4. A lance according to claim 2 and 3, characterized in that
- that the Oxidatorverbindungskanäle (20) and the fuel connecting channels (16) in the lance head (5) are alternately arranged in the circumferential direction, and / or
- enclosing the annular fuel channel (15) the Oxidatorraum (18) coaxially.
5. A lance according to any one of claims 1 to 4, characterized in - that the lance head (5) having a larger outer cross-section a of the lance head (5) adjacent the lance portion and (4), and / or
- that the at least one fuel nozzle (6) lies at a greater radius than the outer cross section of the lance (3) outside of the lance head (5), and / or
- that the lance head (5) has a conical transition portion (17) through which the lance head (5) with the adjoining lance portion (4) is connected.
6. A lance according to claim 5 and according to claim 3 or 4, characterized in that
- that the Oxidatoreinlassöffnungen (19) in the transition section (17) are arranged, and / or
- that the fuel connection channels (16) in the transition section (17) are arranged, and / or
- that the Oxidatorverbindungskanäle (20) in the transition section (17) are arranged.
7. A lance according to any one of claims 1 to 6, characterized in that
- that only a single central oxidator (7) is provided, and / or
- that a plurality of fuel nozzles (6) are provided which are arranged distributed on the lance head (5) in the circumferential direction.
8. A lance according to any one of claims 1 to 7, characterized in that the at least one fuel nozzle (6) is designed such that the fuel with respect to the axial direction of the lance (3) and / or with respect to a central longitudinal plane of the lance (3) inclined in the mixing section (2) aids.
9. A lance according to any one of claims 1 to 8, characterized in that it is in the introduced fuel to liquid fuel.
EP20060819090 2005-11-04 2006-10-18 Fuel lance Withdrawn EP1943464A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CH17692005 2005-11-04
PCT/EP2006/067525 WO2007051705A1 (en) 2005-11-04 2006-10-18 Fuel lance

Publications (1)

Publication Number Publication Date
EP1943464A1 true EP1943464A1 (en) 2008-07-16

Family

ID=35840456

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20060819090 Withdrawn EP1943464A1 (en) 2005-11-04 2006-10-18 Fuel lance

Country Status (4)

Country Link
US (1) US20080229752A1 (en)
EP (1) EP1943464A1 (en)
CN (1) CN101365913A (en)
WO (1) WO2007051705A1 (en)

Families Citing this family (4)

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Publication number Priority date Publication date Assignee Title
JP5571197B2 (en) 2010-10-28 2014-08-13 三菱重工業株式会社 Gas turbine and gas turbine plant equipped with the same
US9127844B2 (en) * 2011-08-02 2015-09-08 General Electric Company Fuel nozzle
US9016039B2 (en) * 2012-04-05 2015-04-28 General Electric Company Combustor and method for supplying fuel to a combustor
DE102013202940A1 (en) * 2013-02-22 2014-09-11 Siemens Aktiengesellschaft Cooling a fuel lance by the fuel

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Publication number Priority date Publication date Assignee Title
GB1444673A (en) * 1973-03-20 1976-08-04 Nippon Musical Instruments Mfg Gas burners
US4139157A (en) * 1976-09-02 1979-02-13 Parker-Hannifin Corporation Dual air-blast fuel nozzle
CH674561A5 (en) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
US5086979A (en) * 1989-07-07 1992-02-11 Fuel Systems Textron Inc. Small airblast fuel nozzle with high efficiency inner air swirler
GB9326367D0 (en) * 1993-12-23 1994-02-23 Rolls Royce Plc Fuel injection apparatus
US5685139A (en) * 1996-03-29 1997-11-11 General Electric Company Diffusion-premix nozzle for a gas turbine combustor and related method
DE19652899A1 (en) * 1996-12-19 1998-06-25 Asea Brown Boveri Burner assembly for a gas turbine
DE59709510D1 (en) * 1997-09-15 2003-04-17 Alstom Switzerland Ltd Combined pressure atomizer nozzle
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
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ITMI991204A1 (en) * 1999-05-31 2000-11-30 Nuovo Pignone Spa liquid fuel injector for burners in gas turbines
DE10050248A1 (en) * 2000-10-11 2002-04-18 Alstom Switzerland Ltd Pre-mixing burner comprises swirl burner with inner chamber, with widening passage, injector with adjustable elements.
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Title
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Also Published As

Publication number Publication date
WO2007051705A1 (en) 2007-05-10
CN101365913A (en) 2009-02-11
US20080229752A1 (en) 2008-09-25

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