CN103438480A

CN103438480A - Nozzle and combustor for a gas turbine engine, and corresponding methods

Info

Publication number: CN103438480A
Application number: CN2013100614649A
Authority: CN
Inventors: 严钟昊; D.W.西蒙斯; G.A.博德曼; B.W.罗米格; K.爱德华兹; M.J.休斯
Original assignee: General Electric Co
Current assignee: General Electric Co PLC
Priority date: 2012-02-27
Filing date: 2013-02-27
Publication date: 2013-12-11
Anticipated expiration: 2033-02-27
Also published as: EP2631544B1; RU2013108313A; JP2013174431A; EP2631544A1; RU2621566C2; US20130219899A1; CN103438480B; US20150253011A1; JP6186132B2

Abstract

A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits.

Description

The nozzle of gas-turbine unit, combustion chamber and corresponding method

Technical field

The present invention relates generally to a kind of gas-turbine unit, the HC fuel that its burning mixes with air is to generate high temperature gas flow, this high temperature gas flow drives turbo blade so that be attached to the axostylus axostyle of described blade and rotate, or rather, the fuel nozzle that relates to engine, its directional nozzle had can by fuel and air pre-mixing merges and realize lower nitric oxide levels simultaneously.

Background technology

Gas-turbine unit is widely used in for many application generatings.Conventional gas-turbine unit comprises compressor, combustion chamber, and turbine.In typical gas-turbine unit machine, compressor provides the air of compression to combustion chamber.The air that enters combustion chamber is mixed with fuel and is burnt.The hot gas of burning is discharged and is flowed in the blade of turbine from combustion chamber, thereby makes in turbine the axostylus axostyle that is connected to described blade rotate.Some mechanical energy drive compression machines and/or other mechanical systems that rotary shaft produces.

Because government regulation does not allow nitrogen oxides emission in atmosphere, so, as the byproduct produced in the gas-turbine unit operation, the output of nitrogen oxide is devoted to maintain below permissible criterion.An approach that meets this kind of rules is to go to the combustion chamber of using complete premixed operational mode, adopting poor fuel and air mixture from flame spread type combustion chamber, for example, to reduce the discharge of () nitrogen oxide (being typically expressed as NOx) and carbon monoxide (CO).These combustion chambers differently are called dry low NOx (DLN), dry low emissions (DLE) or fuel-sean material premixed (LPM) combustion system in affiliated field.

The fuel-air mixing can affect the nitric oxide levels that generates in the hot gas of gas-turbine unit burning and the performance of engine.Gas-turbine unit can adopt one or more fuel nozzles to come air amount and fuel, to promote that in combustion chamber, fuel/air mixture is mixed.Described fuel nozzle can be positioned at the head portion of combustion chamber, and can be configured to suck the air stream that will mix with the fuel input.Usually, each fuel nozzle can be by the centerbody that is positioned at fuel nozzle inner in inner support, and igniter can be arranged on the downstream of centerbody.For example, as the 6th, 438, No. 961 United States Patent (USP) is described, and described patent is incorporated in Ben Wenben for various purposes by reference in full, and so-called swirl nozzle can be installed to the outside of centerbody, and is positioned at the upstream of igniter.Described swirl nozzle has the crooked wheel blade that radially extends through annular circulation flow path from centerbody, and fuel is introduced annular circulation flow path to be entrained in the air stream of swirl nozzle turn from described crooked wheel blade.

The various parameters of describing combustion process in gas-turbine unit are relevant to the generation of nitrogen oxide.For example, in the combustion reaction zone, higher gas temperature is the reason that generates more nitrogen oxide.A kind of method that reduces these temperature is the pre-mixed fuel air mixture fuel that also reduction is burnt and the ratio of air.Along with the ratio reduction of the fuel burnt and air, the amount that generates nitrogen oxide also reduces.Yet there is balance in the performance of gas-turbine unit.Because, along with the ratio of the fuel burnt and air reduces, the flame of fuel nozzle is more flame-out, thereby present the unstable of gas-turbine unit operation.Flame spread type igniter is for the flame of smooth combustion chamber better, but NOx also increases.

Summary of the invention

Various aspects of the present invention and advantage will be illustrated in the following description, or these aspects and advantage may be apparent in explanation, or can derive by putting into practice the present invention.

In theory, more approaching theory relates to each point in combustion chamber, stand to have stoichiometric relationship between the fuel of burning and air in given ignition temperature, the amount that described more approaching theory relates to the nitrogen oxide that the byproduct as burning is generated minimizes.Use the fuel nozzle of configuration as mentioned below, externally on the most advanced and sophisticated plane of the centerbody of nozzle, realize more uniform equivalent proportion, thereby more approaching this kind of theoretical condition realizing required stoichiometric relationship in the combustion chamber of gas-turbine unit, described required stoichiometric relationship is for standing the fuel of burning and the stoichiometric relationship between air in given ignition temperature.In addition, in order to overcome a shortcoming of flame spread type igniter, premixed pilot also can be used as stablizing the igniter of pilot flame, when even low for the ratio at fuel and air, prevents that the amount of NOx from increasing.

In an embodiment of fuel nozzle, described fuel nozzle comprises the premixed pipeline, its dispose be parallel to the tubular axis that burns concentric shafts from the premixed directional nozzle, axially to guide fuel/air mixture; Each premixed pipeline side has an air port at least, wherein each air port radially outward guides from the premixed pipeline, so that each air port can be carried some part of fuel/air mixture secretly from the premixed pipeline, radially outward to guide mixture, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane of nozzle, then enter in the combustion chamber of combustion gas turbine.The air port expection is arranged on the downstream of circular passage, and described circular passage is arranged on the radially outward direction of premixed pipeline.

In another embodiment of the present invention, around the axle about combustion tube, the center longitudinal axis with the acute angle setting is configured each premixed pipeline itself with one heart, radially outwards guide fuel/air mixture with the axle around combustion tube, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane of nozzle, then enter in the combustion chamber of combustion gas turbine.

In another embodiment of the present invention, each premixed pipeline itself is configured with one heart around two-way center longitudinal axis, the second supporting leg that described two-way center longitudinal axis has the first supporting leg that the axle that is parallel to combustion tube arranges and arranges with acute angle about the axle of combustion tube, with the radially outwards guiding of axle around combustion tube by fuel/air mixture, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane of nozzle, then enter in the combustion chamber of combustion gas turbine.

In another embodiment of fuel nozzle, wherein around the axle about combustion tube, the center longitudinal axis with the acute angle setting is configured each premixed pipeline itself with one heart, with the radially outwards guiding of axle around combustion tube by fuel/air mixture; Each premixed pipeline side has an air port at least, so that each air port can be carried some part of fuel/air mixture secretly further mixture is radially outward guided from the premixed pipeline, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane of nozzle, then enter in the combustion chamber of combustion gas turbine.In addition, one or more air port expections in air port radially outward guide from the premixed pipeline, to carry some part in fuel/air mixture secretly further mixture is radially outward guided from the premixed pipeline, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane of nozzle, then enter in the combustion chamber of combustion gas turbine.

Those of ordinary skill in the field will understand feature and aspect and other contents of this type of embodiment better by checking specification.

The accompanying drawing explanation

The remainder of this specification is with reference to accompanying drawing, for the those skilled in the art, complete and can disclose in detail the present invention with realizing, comprises its optimal mode, wherein:

Fig. 1 is that described turbine system has the fuel nozzle that is connected to combustion chamber according to the block diagram of the turbine system of an embodiment of present technique;

The sectional view that Fig. 2 is some parts of combustion chamber in gas turbine system of the present invention;

Fig. 3 has described the exemplary embodiment of parts of the present invention with part perspective view and partial cross section figure;

Fig. 4 has described another exemplary embodiment of parts of the present invention with sectional view;

Fig. 5 is the sectional view along the sight line intercepting that is designated as 5-5 in Fig. 4;

Fig. 6 has described the another exemplary embodiment of parts of the present invention with sectional view;

Fig. 7 has described the another exemplary embodiment of parts of the present invention with sectional view;

Fig. 8 has described the Alternative exemplary embodiment of the part of the dotted line limit that is designated as numeral 8 in Fig. 6 with sectional view;

Fig. 9 with the figure to shown in Fig. 4 similar sectional view another exemplary embodiments of parts of the present invention has been described;

Figure 10 has schematically meaned the embodiment of the present invention for the method for the fuel/air mixture nozzle of controlling gas turbine; And

Figure 11 has schematically meaned the alternate embodiment of the present invention for the method for the fuel/air mixture nozzle of controlling gas turbine.

The specific embodiment

Now with detailed reference to each embodiment of the present invention, shown in the drawings of one or more examples of the embodiment of the present invention.Refer to the feature in accompanying drawing by numeral and letter sign in the specific embodiment.In accompanying drawing and description, same or similar sign is used in reference to the same or similar part for embodiments of the invention.

The unrestricted the present invention in order to explain the present invention of each example.In fact, the those skilled in the art easily understands, do not depart from the scope of the present invention or the prerequisite of spirit under, can make various modifications and variations to the present invention.For example, the feature that describes or describe as the part of an embodiment can be used in another embodiment, thereby obtains another embodiment.Therefore, the present invention should be contained these type of modifications and variations in the scope that belongs to appended claims and equivalent thereof.

Should be appreciated that, unless otherwise mentioned, otherwise the scope of mentioning in the present patent application file and restriction comprise all subranges that are positioned at prescribed limits, comprising this restriction itself.For example, from 100 to 200 scope also comprises likely subrange of institute, for example, and from 100 to 150,170 to 190,153 to 162,145.3 to 149.6 and 187 to 200.In addition, be at most 7 restriction and also comprise and be at most 5, be at most 3 and be at most 4.5, and comprise all subranges in this restriction, for example, from approximately 0 to 5, comprising 0 and 5, and from 5.2 to 7, comprising 5.2 and 7.

With reference to figure 1, illustrate the sketch of some parts of gas turbine system 10.Turbine system 10 can be used liquid or gaseous fuel, and for example, natural gas and/or be rich in the synthesis gas of hydrogen, carry out operating turbine machine system 10.As shown in the figure, such a plurality of fuel nozzles 12 of hereinafter describing more fully suck fuel supply 14, fuel are mixed with air, and air fuel mixture is assigned in combustion chamber 16.Burn in the chamber of air fuel mixture in combustion chamber 16, thereby produce hot pressure exhaust.The bootable exhaust in combustion chamber 16 flows to outlet 20 by turbine 18.In exhaust, when the turbine 18, gas can order about one or more turbine blades rotates axostylus axostyle 22 along the axle of system 10.As shown in the figure, axostylus axostyle 22 can be connected to all parts of turbine system 10, comprises compressor 24.Compressor 24 also comprises the blade that can be connected to axostylus axostyle 22.When axostylus axostyle 22 rotation, the blade in compressor 24 also can rotate, thereby then the air compressed from air inlet 26 by compressor 24 enters in fuel nozzle 12 and/or combustion chamber 16.Axostylus axostyle 22 also can be connected to load 28, and described load 28 can be vehicle load or dead load, for example the generator in power plant or the propeller on aircraft.To understand, load 28 can comprise can be provided by the rotation output of turbine system 10 any appropriate device of power.

The sketch of the sectional view of some parts that Fig. 2 is the gas turbine system 10 schematically described in Fig. 1.As Fig. 2 schematically illustrates, turbine system 10 comprises one or more fuel/air mixture nozzles 12, and it is arranged in the head portion 27 of one or more combustion chambers 16 of gas-turbine unit.Each illustrated fuel nozzle 12 can comprise a plurality of fuel nozzle and/or the fuel nozzles independently of integrated group together, wherein each illustrated fuel nozzle 12 at least substantially or the interior structural support that places one's entire reliance upon (for example, bearing the load of fluid passage).With reference to figure 2, system 10 comprises that described gas is via in air inlet 26 inflow systems 10 for for example, compressor section 24 to gas (, air) pressurization.Be in operation, air enters turbine system 10 by air inlet 26, and can in compressor 24, be pressurizeed.Although should be understood that gas can be called air in the present patent application file, described gas can be any gas that is applicable to gas turbine system 10.The forced air flowing in combustion chamber part 16 of discharging from compressor section 24, described combustion chamber Partial Feature usually be a plurality of combustion chambers 16 (Fig. 1 and Fig. 2 only illustrate a combustion chamber) around the axle of system 10 with the annular array setting.Enter the air of combustion chamber part 16 and fuel mix and 16 combustion chamber 32 internal combustion in combustion chamber.For example, fuel nozzle 12 can inject combustion chamber 16 with suitable fuel-air ratio by fuel/air mixture, thereby carries out best burning, discharge, fuel consumption and electric power output.The pressure exhaust of burning Heat of Formation, then the pressure exhaust of described heat flows to turbine part 18 (Fig. 1 illustrates) from each combustion chamber 16, with drive system 10 generating.Hot gas drives turbine 18 interior one or more blade (not shown) so that axostylus axostyle 22 rotates, thereby compressor 24 and load 28 are rotated.The rotation of axostylus axostyle 22 makes blade 30 rotations in compressor 24 and introduces the air taken in by air inlet 26 and to this air pressurized.Yet should easily understand, combustion chamber 16 is without adopting the above-mentioned and described configuration of present patent application file, and usually can adopt any configuration with following functions: can make forced air and fuel mix, burn and enter the turbine part 18 of system 10.

Fig. 3 schematically illustrates the every embodiment according to the fuel/air mixture nozzle 12 of exemplary embodiment of the present invention to Fig. 9.For example, in each figure of Fig. 4, Fig. 8 and Fig. 9, at least each upstream extremity of each premixed pipeline 41 is provided with central shaft 41d, and described central shaft is configured and arranges, and makes the fluid stream of the ingate 66a that enters each premixed pipeline 41 be parallel to the central shaft 36 of centerbody 52 and guide.For example, in each figure of Fig. 6 and Fig. 7, at least each upstream extremity of each premixed pipeline 41 is provided with central shaft 41d, described central shaft is configured and arranges, the fluid stream that makes the ingate 66a that enters each premixed pipeline 41 is acute angle with the central shaft 36 of centerbody 52 and guides, described acute angle scope at 0.1 degree between 20 degree.For example, as Fig. 3 schematically illustrates, an embodiment of fuel/air mixture nozzle 12 comprises premixed pipeline 41, its dispose be parallel to the tubular axis 36 that burns concentric shafts so that fuel/air mixture is axially guided from premixed directional nozzle 40.In the every embodiment schematically illustrated in Fig. 4, Fig. 5 and Fig. 9, each premixed pipeline 41 side has an air port 42 at least, wherein each air port 42 can be carried some part of fuel/air mixture secretly so that mixture is radially outward guided from premixed pipeline 41, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane 44 of nozzle 12, then enter in the combustion chamber 32 of combustion chamber 16 (Fig. 1 and Fig. 2 illustrate).In Fig. 4 and the described embodiment of Fig. 5, each air port 42 is expected and is radially outward guided from premixed pipeline 41, so that can more easily carrying more fuel/air mixture secretly, each air port 42 radially outward guides from premixed pipeline 41 to incite somebody to action more polyhybird thing, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane 44 of nozzle 12, then enter in the combustion chamber 32 of combustion chamber 16 (Fig. 1 and Fig. 2 illustrate).

For example, as Fig. 3 schematically illustrates, for the fuel/air mixture nozzle 12 of gas-turbine unit, expect and comprise axially extended peripheral wall 50, it defines the shell of nozzle 12.The peripheral wall 50 of fuel/air mixture nozzle 12 has outer surface 50a and inner surface 50b, and described inner surface 50b is back to outer surface 50a and define axially extended inner chamber 50c.

For example, as Fig. 3 schematically illustrates, fuel/air mixture nozzle 12 expection for gas-turbine unit comprises hollow, axially extended centerbody 52, and it is arranged in the inner chamber 50c of fuel/air mixture nozzle 12 and is provided with central shaft 36, and described central shaft 36 is identical with the central shaft of combustion tube.Centerbody 52You center body wall 52a defines, described center body wall 52a define upstream extremity 52b and with the axial opposed downstream 52c of upstream extremity 52b.Center body wall 52a defines by outer surface 52d and back to the inner surface 52e of outer surface 52d.The inner surface 52d of center body wall 52a defines axially extended internal path 53, and its central shaft around centerbody 52 36 is arranged with one heart.Primary air circulation flow path 51 is defined in the annular space between the outer surface 52d of inner surface 50bYu center body wall 52a of peripheral wall 50.

For example, as Fig. 3 schematically illustrates, comprise the fuel feed pipe 54 of axially extended hollow for fuel/air mixture nozzle 12 expections of gas-turbine unit, it extends axially the internal path 53 through centerbody 52.Fuel feed pipe 54 has upstream extremity 54a, and described upstream extremity is arranged on the upstream extremity 52b of centerbody 52 and is configured for being connected to the fuels sources (not shown).Fuel feed pipe 54 has downstream 54b, and it is arranged on the downstream 52c of centerbody 52.The secondary air circulation road is defined by the annular space between the outer surface of the inner surface 52e of centerbody 52 and fuel feed pipe 54, and this annular space defines the axially extended internal path 53 schematically illustrated in Fig. 3.

As Fig. 3 schematically illustrates, primary fuel can be fed to by a plurality of air cyclone wheel blades 56 combustion chamber 32 of combustion chamber 16 (Fig. 2 illustrates), and described air cyclone wheel blade is fixed and extends through the stream of primary air circulation road 51.These air cyclone wheel blades 56 form the so-called swirl nozzle radially extended out from the outer surface of center body wall 52a.As Fig. 3 schematically illustrates, each air cyclone wheel blade 56 expection of swirl nozzle have the fuel pipeline 57 in fuel injection tip or hole 58 terminations, the primary fuel (being illustrated by the arrow that is designated as digital 57a) flowed out from pipeline 57 can be ejected into primary air and (be illustrated by the arrow that is designated as digital 51a) from described fuel injection tip or hole 58, and described primary air flows through the fuel injection tip 58 in air cyclone wheel blade 56.Along with primary air stream 51a heads on air cyclone wheel blade 56 and guides, can apply eddy current type to promote mixing of primary air stream 51a and primary fuel to primary air stream 51a, described primary fuel from the hole 58 of air cyclone wheel blade 56 be ejected into through primary air stream 51a.The primary air stream 51a mixed with primary fuel can flow in premix cyclization 51 subsequently, and described premix cyclization 51 is defined between peripheral wall 50 and interior centerbody 52, and wherein primary air stream 51a and primary fuel continue to mix, and then enter combustion chamber 32.

For example, as Fig. 3 schematically illustrates, for the fuel/air mixture nozzle 12 of gas-turbine unit, expect and comprise premixed directional nozzle 40, it has the upstream extremity 40a of the downstream 52c that is connected to centerbody 52.In the described embodiment of Fig. 3, the upstream extremity 40a of the downstream 52c of centerbody 52 and premixed directional nozzle 40 part is defined with the outermost layer wall that defines premixed directional nozzle 40 by the different piece of the metallic cylinder that forms centerbody 52.Premixed directional nozzle 40 has the axial opposed downstream 40b with the upstream extremity 40a of premixed directional nozzle 40.

For example, as Fig. 3, Fig. 4 and Fig. 9 schematically illustrate, premixed directional nozzle 40 is provided with guiding fuel nozzle 60, and described igniter fuel nozzle is provided with upstream extremity 60a and downstream 60b.For example, as Fig. 4 and Fig. 9 schematically illustrate, the upstream extremity 60a of igniter fuel nozzle 60 is communicated with the downstream 54b fluid of fuel feed pipe 54.The downstream 60b of guiding fuel nozzle 60 is provided with at least one fuel nozzle ports 61, and described fuel nozzle ports 61 is configured with the upstream extremity 60a fluid of igniter fuel nozzle 60 and is communicated with.For example, as be designated as 62 arrow in Fig. 4 and Fig. 9, schematically illustrate, the fuel 62 that the downstream 54b by fuel feed pipe 54 enters guiding fuel nozzle 60 leaves by a plurality of fuel nozzle ports 61 (being shown in broken lines in Fig. 5) fuel nozzle 60 that leads.

For example, as Fig. 3, Fig. 4 and Fig. 9 schematically illustrate, premixed directional nozzle 40 further is provided with annular fuel locular wall 63, and described annular fuel locular wall 63 radially outward arranges from guiding fuel nozzle 60, and expects concentric about the fuel tubular axis 36 shown in Fig. 3.For example, as Fig. 3, Fig. 4 and Fig. 9 schematically illustrate, fuel locular wall 63 defines the fuel chambers 64 between guiding fuel nozzle 60 and fuel locular wall 63.For example, as Fig. 4 and Fig. 9 schematically illustrate, fuel locular wall 63 further defines a plurality of teasehole 63a, and fuel is discharged from fuel chambers 64 through described a plurality of teasehole 63a.For example, as Fig. 4 and Fig. 9 schematically illustrate, at least one teasehole 63a is communicated with by fuel chambers 64 fluids with at least one fuel nozzle ports 61.Ideally, each teasehole 63a is communicated with by fuel chambers 64 fluids with each fuel nozzle ports 61.

For example, as Fig. 3, Fig. 4 and Fig. 9 schematically illustrate, premixed directional nozzle 40 further is provided with a plurality of axially extended hollow premixed pipelines 41, and described premixed pipeline 41 radially outward arranges from fuel locular wall 63.For example, as schematically illustrated in Fig. 4 and the described embodiment of Fig. 9, each premixed pipeline 41 desired part ground is defined by partition 63.For example, as Fig. 3 schematically illustrates, each premixed pipeline 41 has near the upstream extremity 41a downstream 52c that is arranged on centerbody 52.For example, as Fig. 4 and Fig. 9 schematically illustrate, each premixed pipeline 41 41a at its upstream end is provided with ingate 66a, and described ingate 66a is communicated with internal path 53 fluids of centerbody 52.The arrow that is designated as 53a in Fig. 4 and Fig. 9 is schematically indicated air stream 53a, and described air stream 53a enters the ingate 66a of each premixed pipeline 41 from the internal path 53 of centerbody 52.

For example, as Fig. 4 and Fig. 9 schematically illustrate, each premixed pipeline 41 is communicated with at least one teasehole 63a fluid, and described teasehole 63a is defined in the fuel locular wall 63 of fuel chambers 64.The arrow that is designated as 62a in Fig. 4 and Fig. 9 is schematically indicated fuel flow 62a, and described fuel flow 62a flows out from fuel chambers 64 by the teasehole 63a be defined in fuel locular wall 63, then enters each premixed pipeline 41.The arrow that is designated as 62b in Fig. 4 and Fig. 9 is schematically indicated fuel-air mixed flow 62b, the downstream flow of described fuel-air mixed flow 62b in the premixed pipeline 41 of premixed directional nozzle 40.

For example, as Fig. 4 and Fig. 9 schematically illustrate, each premixed pipeline 41 has downstream 41b, and the upstream extremity 41a of described downstream 41b and premixed pipeline 41 is axially opposed, and is arranged near the downstream 40b of premixed directional nozzle 40.For example, as Fig. 4 and Fig. 9 schematically illustrate, each downstream 41b of each premixed pipeline 41 is provided with outlet opening 66b, and described outlet opening 66b allows fluid, that is, fuel air mixture 62b, discharge from the premixed pipeline 41 of hollow.For example, as Fig. 4 and Fig. 9 schematically illustrate, each downstream 41b of each premixed pipeline 41 is provided with central shaft 41c, and the wall that defines each premixed pipeline 41 is arranged with one heart around this central shaft 41c.In addition, for example, as the embodiment of Fig. 4 and the described premixed directional nozzle 40 of Fig. 9 schematically illustrates, each central shaft 41c is straight line, described straight line guides through being arranged so that fluid stream to be parallel to the central shaft 36 of centerbody 52, and described fluid stream is from the fuel of the outlet opening 66b discharge of each premixed pipeline 41 and the mixture of air.

Although, when fuel air mixture 62b leaves the outlet opening 66b of each premixed pipeline 41, fuel air mixture 62b trends towards from each central shaft 41c radial diffusion, the applicant has shown that radial diffusion is not remarkable.In fact, applicant's research shows, with regard to the equivalent proportion of each several part in the pelvic outlet plane 44 that burns (Fig. 4 and Fig. 9 illustrate), the part that is close to the outlet opening 66b downstream of each premixed pipeline 41 is about the twice of the part in central shaft 36 downstreams that are close to centerbody 52.Be close to each premixed pipeline 41 outlet opening 66b downstream position the high equivalent weight ratio can by axially extended inner chamber 50c (Fig. 3 illustrates) continuous effective light fuel/air mixture, even and flame also can keep flame stabilization under poor flame-out (LBO) condition.This is an important function of premixed pilot, and premixed pilot 60 is realized this effect in the situation that do not increase NOx.

Various embodiments of the present invention comprise for resisting this kind than the feature of high equivalent weight ratio, the described part that is present in the outlet opening 66b downstream of each premixed pipeline 41 of next-door neighbour in burning pelvic outlet plane 44 (Fig. 4 and Fig. 9 illustrate) than the high equivalent weight ratio.For example, the embodiment of premixed directional nozzle 40 as described as Fig. 3, Fig. 4, Fig. 5 and Fig. 9 schematically illustrates, and premixed directional nozzle 40 further is provided with the circular passage 70 radially outward arranged from premixed pipeline 41.For example, embodiment as described as Fig. 3, Fig. 4, Fig. 5 and Fig. 9, the inwall 43 of circular passage 70 also is used for defining the outer wall 43 of premixed pipeline 41.For example, embodiment as described as Fig. 3, Fig. 4, Fig. 5 and Fig. 9, center body wall 52a also is used for defining the outer wall 52a of circular passage 70.

For example, as the embodiment of Fig. 3, Fig. 4 and the described premixed directional nozzle 40 of Fig. 9 schematically illustrates, the upstream extremity of circular passage 70 is configured with internal path 53 fluids of centerbody 52 and is communicated with, thereby takes in air stream from the internal path 53 of centerbody 52.70 the downstream in circular passage, formed a plurality of air ports 42.At least one air port 42 is arranged near at least one outlet opening 66b of at least one premixed pipeline 41.Ideally, for example, as Fig. 4, Fig. 5 and Fig. 9 illustrate, at least one air port 42 is arranged near each outlet opening 66b of each premixed pipeline 41.

For example, as Fig. 9 schematically illustrates, each path that is provided with an air port 42 forms with one heart around central shaft 42a, the central shaft 41c of the downstream 41b of the premixed pipeline 41 described central shaft 42a is arranged to be parallel near.Like this, leave the higher speed air of each air port 42 and carry some fuel/air mixture of leaving premixed pipeline 41 secretly, and for the fuel/air mixture to being present in certain part of burning pelvic outlet plane 44 (Fig. 9 illustrates), guide, this part is close to the outlet opening 66b downstream of each premixed pipeline 41.Total result is that the burning pelvic outlet plane 44 (Fig. 9 illustrates) of fuel-air nozzle 12 locates to have more uniform equivalent proportion, and this also can be by ignition source as igniter.

For example, as Fig. 4 schematically illustrates, each path that is provided with an air port 42 forms with one heart around central shaft 42a, and described central shaft 42a is arranged to be acute angle about the central shaft 41c of the downstream 41b of premixed pipeline 41 near.The big or small desired extent of this acute angle at 0.1 degree between 20 degree.In addition, the air port in Fig. 4 embodiment 42 expection is configured and through being arranged so that air stream that each air port 42 guiding leave air port 42 flows on the direction of an outlet opening 66b in away from premixed pipeline 41 near.Therefore, for example, in the embodiment schematically illustrated as Fig. 4, each air port 42 makes the air that leaves this air port 42 move in following direction through sensing: in the downstream of the central shaft 36 of centerbody 52 and radially away from the central shaft 36 of centerbody 52, and radially away from the central shaft 41c of the downstream 41b of the premixed pipeline 41 each near.Like this, leave the air of each air port 42 and carry some fuel/air mixture of leaving premixed pipeline 41 secretly, and guide for the fuel/air mixture to being present in certain part of burning pelvic outlet plane 44 (Fig. 4 illustrates), this part next-door neighbour is towards the outlet opening 66b downstream of radially outer each the premixed pipeline 41 of peripheral wall 50 (Fig. 3 illustrates).Total result is that the burning pelvic outlet plane 44 (Fig. 4 illustrates) of fuel-air nozzle 12 locates to have more uniform equivalent proportion, and this also can be by ignition source as igniter.

For example, in the another embodiment of the present invention of schematically describing at Fig. 6, except the embodiment of the premixed directional nozzle 40 schematically described in Fig. 6, the embodiment of the embodiment of Fig. 6 and Fig. 3, Fig. 4, Fig. 5 and Fig. 9 is similar.As Fig. 6 schematically illustrates, each premixed pipeline 41 itself is configured with one heart around the center longitudinal axis 41c that is arranged to central shaft 36 about centerbody 52 and is acute angle.The big or small desired extent of this acute angle at 0.1 degree between 20 degree.Therefore, in the premixed directional nozzle 40 of schematically describing in Fig. 6, each premixed pipeline 41 is configured and radially outward guides away from the central shaft 36 of centerbody 52 through fuel/air mixture leaving from the outlet opening 66b of each premixed pipeline 41 is set, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane 44 of fuel-air nozzle 12, then enter in the combustion chamber of combustion gas turbine 10, thereby light to continuous effective by the fuel/air mixture of axially extended inner chamber 50c (Fig. 3 illustrates) supply of fuel-air nozzle 12.For example, although specifically do not illustrate in Fig. 6, but the axial length of the one or more premixed pipelines in premixed pipeline 41 can be with one heart around the mode of the central shaft 41c of the downstream 41b of premixed pipeline 41, extend beyond the downstream 40b of premixed directional nozzle 40.

For example, in the another embodiment of the present invention of schematically describing at Fig. 8, except the embodiment of the premixed pipeline 41 in the premixed directional nozzle 40 of schematically describing in Fig. 6, the embodiment of the embodiment of Fig. 8 and Fig. 3, Fig. 4, Fig. 5, Fig. 6 and Fig. 9 is similar.In the embodiment schematically described at Fig. 8, each premixed pipeline 41 is configured with one heart around two-way center longitudinal axis itself, and described two-way center longitudinal axis has the first supporting leg 41d and the second supporting leg 41c.As Fig. 8 schematically illustrates, the first supporting leg 41d of two-way center longitudinal axis is arranged to be parallel to the central shaft 36 of centerbody 52, and extends between the upstream extremity 41a of each premixed pipeline 41 and downstream 41b.The second supporting leg 41c of two-way center longitudinal axis is arranged to be acute angle about the central shaft 36 of centerbody 52, and extends through the downstream 41b of each premixed pipeline 41.The big or small desired extent of this acute angle at 0.1 degree between 20 degree.Therefore, the premixed pipeline 41 of schematically describing in Fig. 8 is configured and radially outward guides away from the central shaft 36 of centerbody 52 through fuel/air mixture leaving from outlet opening 66b is set, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane 44 of fuel-air nozzle 12, then enter in the combustion chamber of combustion gas turbine 12, thus continuous effective light the fuel/air mixture of axially extended inner chamber 50c (Fig. 3 illustrates) supply by fuel-air nozzle 12.

For example, in the another embodiment of the present invention of schematically describing at Fig. 7, except the premixed pipeline 41 in the premixed directional nozzle 40 of schematically describing in Fig. 3, Fig. 4, Fig. 5 and Fig. 9 and the embodiment of circular passage 70, the embodiment of the embodiment of Fig. 7 and Fig. 3, Fig. 4, Fig. 5 and Fig. 9 is similar.As Fig. 7 schematically illustrates, each premixed pipeline 41 itself is configured with one heart around the center longitudinal axis 41c that is arranged to central shaft 36 about centerbody 52 and is acute angle.The big or small desired extent of this acute angle at 0.1 degree between 20 degree.Therefore, in the premixed directional nozzle 40 of schematically describing in Fig. 7, each premixed pipeline 41 is configured and radially outward guides away from the central shaft 36 of centerbody 52 through fuel/air mixture leaving from the outlet opening 66b of each premixed pipeline 41 is set, thereby form more uniform fuel/air mixture in the burning pelvic outlet plane 44 of fuel-air nozzle 12, then enter in the combustion chamber of combustion gas turbine 10, thereby light to continuous effective by the fuel/air mixture of axially extended inner chamber 50c (Fig. 3 illustrates) supply of fuel-air nozzle 12.

For example, the embodiment of premixed directional nozzle 40 as described in Figure 7 schematically illustrates, and on the downstream direction that the upstream extremity of circular passage 70 is configured to advance towards the air port 42 on each the outlet opening side that is arranged on premixed pipeline 41 at it, is tapered.As above about Fig. 3, the embodiment of Fig. 4 and Fig. 5 is described, each air port 42 radially outward guides from premixed pipeline 41, so that certain part that each air port 42 can be carried secretly in fuel/air mixture is come further mixture radially outward to be guided from premixed pipeline 41, to form more uniform fuel/air mixture in the burning pelvic outlet plane 44 at fuel-air nozzle 12, then enter in the combustion chamber 32 of combustion chamber 16 (Fig. 1 and Fig. 2 illustrate), and with continuous effective light the fuel/air mixture of axially extended inner chamber 50c (Fig. 3 illustrates) supply by fuel-air nozzle 12.

Each embodiment of premixed directional nozzle 40 has small-sized fine fixing premixed flame near the pedestal of fuel-air nozzle 12, thereby fixes the eddy flow fuel air mixture that leaves fuel-air nozzle 12.The raising of flame holding can reduce the operation to fuel/air mixture, thus expansion LBO and discharge operability window.

Use for example fuel/air mixture nozzle 12 of above-mentioned embodiment, can implement the favorable method for the fuel/air mixture nozzle 12 of operating gas turbine engine 10.The embodiment expection for the method for the fuel/air mixture nozzle 12 of operating gas turbine engine 10 comprises the following steps that Figure 10 schematically illustrates: step 81, (for example be about to the primary air stream 51a in downstream, Fig. 3 illustrates) send through swirl nozzle, with the turn primary air stream; Step 82, be about to primary fuel flow 57a (for example, Fig. 3 illustrates) and send through swirl nozzle, with the downstream at swirl nozzle, with the primary air stream 51a of eddy flow, mixes; Step 83, be about to pilot fuel flow 62 (for example, Fig. 4 illustrates) and send the fuel feed pipe 54 arrival premixed directional nozzles 40 through hollow; Step 84, be about to secondary air stream 53a (for example, Fig. 4 illustrates) downstream delivery and for example, arrive premixed directional nozzle 40 through centerbody 52 (, Fig. 3 illustrates); Step 85, at a plurality of axially extended hollow premixed pipelines 41 (for example, Fig. 4 illustrates) in pilot fuel 62 and secondary air stream 53a is mixed, described premixed pipeline 41 is discharged fuel/air mixture 62b (for example, Fig. 4 and Fig. 9 illustrate) from the downstream 41b of premixed directional nozzle 40; And step 86, being about to fuel/air mixture 62b and discharging from the premixed pipeline 41 of premixed directional nozzle 40, described premixed pipeline 41 for example, away from the central shaft 36 (, Fig. 3, Fig. 4 and Fig. 6 illustrate to Fig. 9) of centerbody 52.

Another embodiment expection for the method for the fuel/air mixture nozzle 12 of operating gas turbine engine 10 comprises the following steps that Figure 11 schematically illustrates: step 81, (for example be about to primary air stream 51a, Fig. 3 illustrates) downstream delivery is through swirl nozzle, with the turn primary air stream; Step 82, be about to primary fuel flow 57a (for example, Fig. 3 illustrates) and send through swirl nozzle, with the downstream at swirl nozzle, with the primary air stream 51a of turn, mixes; Step 83, be about to pilot fuel flow 62 (for example, Fig. 4 illustrates) and send the fuel feed pipe 54 arrival premixed directional nozzles 40 through hollow; Step 84, be about to secondary air stream 53a (for example, Fig. 4 illustrates) downstream delivery and for example, arrive premixed directional nozzle 40 through centerbody 52 (, Fig. 3 illustrates); Step 85, at a plurality of axially extended hollow premixed pipelines 41 (for example, Fig. 4 illustrates) in pilot fuel 62 and secondary air stream 53a is mixed, described mixing duct 41 is discharged fuel/air mixture 62b (for example, Fig. 4 and Fig. 9 illustrate) from the downstream 41b of premixed directional nozzle 40; Step 87, be about to some secondary air stream 53a (for example, Fig. 4, Fig. 7 and Fig. 9 illustrate) and forward the circular passage 70 radially outward arranged from the premixed pipeline 41 of premixed directional nozzle 40 to; And step 88, be about to air and discharge from for example, circular passage 70 away from premixed directional nozzle 40 (, Fig. 4, Fig. 7 and Fig. 9 illustrate).Ideally, from circular passage, the pressure of 70 air of discharging surpasses the air pressure that enters circular passage 70.Ideally, for example, as Fig. 7 schematically illustrates, circular passage 70 comprises upstream extremity, and described upstream extremity is configured to be tapered on downstream direction.Ideally, for example, as Fig. 7 schematically illustrates, the another embodiment of described method comprises the following steps: fuel/air mixture is discharged from the premixed pipeline 41 of premixed directional nozzle 40, and described premixed pipeline 41 is away from the central shaft 36 of centerbody 52.Ideally, for example, as Fig. 4 schematically illustrates, the another embodiment of described method comprises the following steps: fuel/air mixture 62b is discharged towards the direction that is parallel to the central shaft 36 of centerbody 52 from the premixed pipeline 41 of premixed directional nozzle 40.Ideally, for example, as Fig. 4 and Fig. 7 schematically illustrate, the another embodiment of described method comprises the following steps: fuel/ air mixture 62b 70 is discharged towards the direction away from the central shaft 36 of centerbody 52 radially from circular passage.

This specification has used Multi-instance to disclose the present invention, comprises optimal mode, and under also allowing, any technical staff in field can put into practice the present invention, comprises and manufactures and use any device or system, and implement any contained method simultaneously.Protection scope of the present invention is defined by claims, and can comprise other examples that the those skilled in the art finds out.If the structural element of other these type of examples is identical with the letter of claims, if or the letter of the equivalent structure key element that comprises of this type of example and claims without essential difference, this type of example also belongs to the scope of claims so.

Claims

1. the nozzle of the fuel/air mixture for gas-turbine unit, described fuel/air mixture nozzle comprises:

Axially extended peripheral wall, described peripheral wall defines the shell of described fuel/air mixture nozzle, and described peripheral wall has outer surface and inner surface, and described inner surface is back to described outer surface and define axially extended inner chamber;

Hollow, axially extended centerbody, described centerbody is arranged in the described inner chamber of described fuel/air mixture nozzle and has central shaft, described centerbody is defined by the center body wall, described center body wall define upstream extremity and with the axial opposed downstream of described upstream extremity, described center body wall defines by outer surface and back to the inner surface of described outer surface, the described inner surface of described center body wall defines axially extended internal path, and described internal path arranges with one heart around the described central shaft of described centerbody;

The fuel feed pipe of elongated hollow, described fuel feed pipe axially extends through the described internal path of described centerbody, described fuel feed pipe has upstream extremity, described upstream extremity is arranged on the described upstream extremity place of described centerbody and is configured for being connected to fuels sources, described fuel feed pipe has downstream, and described downstream is arranged on the described downstream end of described centerbody;

The primary air circulation road, described primary air circulation road is defined by the annular space between the described inner surface of the described outer surface of described centerbody and described peripheral wall;

The premixed directional nozzle, described premixed directional nozzle has the upstream extremity of the described downstream that is connected to described centerbody, and described premixed directional nozzle has and the axial opposed downstream of the described upstream extremity of described premixed directional nozzle; And

Described premixed directional nozzle further is provided with a plurality of axially extended hollow premixed pipelines, each premixed pipeline has upstream extremity, described upstream extremity is arranged near the described downstream of described centerbody and defines the ingate be communicated with the described internal path fluid of described centerbody, each premixed pipeline has at least one teasehole, described teasehole is communicated with the described downstream fluid of described fuel feed pipe, each premixed pipeline has downstream, described downstream is provided with the outlet opening that fluid is discharged from described hollow premixed pipeline, each downstream of each premixed pipeline is provided with central shaft, the described central shaft of described central shaft and described centerbody is not parallel.

2. fuel/air mixture nozzle according to claim 1, wherein each central shaft of at least one premixed pipeline is arranged to be acute angle with the described central shaft of described centerbody.

3. fuel/air mixture nozzle according to claim 1, wherein said premixed directional nozzle further defines the circular passage radially outward arranged from described premixed pipeline, described circular passage is configured with the described internal path fluid of described centerbody and is communicated with, described circular passage is provided with a plurality of air ports, and at least one described air port is arranged near a described outlet opening of at least one described premixed pipeline and has central shaft.

4. fuel/air mixture nozzle according to claim 3, wherein the described central shaft of the described upstream extremity of at least one premixed pipeline be configured and the direction through the described central shaft to be parallel to described centerbody is set on extend.

5. fuel/air mixture nozzle according to claim 3, wherein the described central shaft of the described central shaft of at least one described air port and described centerbody forms acute angle.

6. fuel/air mixture nozzle according to claim 3, wherein said circular passage is tapered on the downstream direction advanced towards described air port.

7. fuel/air mixture nozzle according to claim 1, further comprise swirl nozzle, described swirl nozzle comprises a plurality of swirl vanes that radially extend through described primary air circulation road, at least one described swirl vane is provided with the fuel channel be communicated with described primary air circulation road fluid, and described fuel channel has entrance and has outlet in its opposite end at the one end.

8. fuel/air mixture nozzle according to claim 1, wherein said premixed directional nozzle is provided with the guiding fuel nozzle, described guiding fuel nozzle is provided with upstream extremity and downstream, the described upstream extremity of described guiding fuel nozzle is communicated with the described downstream fluid of described fuel feed pipe, and the described downstream of described guiding fuel nozzle is provided with and is configured at least one fuel nozzle ports be communicated with the described upstream extremity fluid of described guiding fuel nozzle; And

Described premixed directional nozzle further is provided with the fuel locular wall, described fuel locular wall radially outward arranges and defines the fuel chambers between described guiding fuel nozzle and described fuel locular wall from described guiding fuel nozzle, described fuel locular wall further is provided with a plurality of teaseholes, at least one described teasehole is communicated with by the described fuel nozzle ports fluid of described fuel chambers and at least one, and each premixed pipeline radially outward arranges and is communicated with at least one described teasehole fluid from described fuel locular wall.

9. the combustion chamber for gas-turbine unit, described combustion chamber comprises:

Head portion;

At least one the fuel/air mixture nozzle carried by described head portion, each fuel/air mixture nozzle further comprises:

Hollow, axially extended centerbody, described centerbody is arranged in the described inner chamber of described fuel/air mixture nozzle and is provided with central shaft, described centerbody is defined by the center body wall, described center body wall define upstream extremity and with the axial opposed downstream of described upstream extremity, described center body wall defines by outer surface and back to the inner surface of described outer surface, the described inner surface of described center body wall defines axially extended internal path, and described internal path arranges with one heart around the described central shaft of described centerbody;

The fuel feed pipe of elongated hollow, described fuel feed pipe extends axially the described internal path through described centerbody, described fuel feed pipe has upstream extremity, described upstream extremity is arranged on the described upstream extremity place of described centerbody and is configured for being connected to fuels sources, described fuel feed pipe has downstream, and described downstream is arranged on the described downstream end of described centerbody;

10. combustion chamber according to claim 9, wherein said premixed directional nozzle further defines the circular passage radially outward arranged from described premixed pipeline, described circular passage is configured with the described internal path fluid of described centerbody and is communicated with, and described annular channels is provided with a plurality of air ports.

11. combustion chamber according to claim 9, wherein at least one described air port is arranged near a described outlet opening of at least one described premixed pipeline and has central shaft, and described central shaft is arranged to be acute angle with the described central shaft of the described outlet opening of vicinity of at least one described premixed pipeline.

12. combustion chamber according to claim 9, wherein said circular passage is tapered on the downstream direction advanced towards described air port.

13. a method of discharging to improve flame holding and NOx for operating gas turbine engine fuel/air mixture nozzle, described fuel/air mixture nozzle defines by following: peripheral wall; Be arranged in described peripheral wall and be provided with the hollow central body of central shaft; Swirl nozzle, described swirl nozzle extends towards described peripheral wall from the outer radial of the described upstream extremity of described centerbody; And, at the premixed directional nozzle of the described downstream of centerbody, described premixed directional nozzle comprises a plurality of premixed pipelines with outlet opening, said method comprising the steps of:

The primary air stream downstream delivery is passed to described swirl nozzle, with the described primary air stream of turn;

Primary fuel flow is sent through described swirl nozzle, mixed with the primary air stream with the downstream turn of described swirl nozzle;

Pilot fuel flow is sent through the hollow fuel feed pipe and arrived described premixed directional nozzle;

Secondary air is flowed to downstream to be sent through described centerbody and arrives described premixed directional nozzle;

In a plurality of axially extended hollow premixed pipelines, described pilot fuel is mixed with described secondary air stream, wherein each premixed pipeline is provided with central shaft in its downstream end, and the described central shaft of described central shaft and described centerbody is not parallel and described fuel/air mixture is discharged from the described downstream of described premixed directional nozzle; And

Described fuel/air mixture is discharged from the described outlet opening of the described premixed pipeline of described premixed directional nozzle.

14. method according to claim 13 is further comprising the steps: from the described premixed pipeline of described premixed directional nozzle, described fuel/air mixture is discharged towards the direction away from the described central shaft of described centerbody radially.

15. method according to claim 13 is further comprising the steps: by some described secondary airs circular passage that circulates, described circular passage is radially outward arranged from the described premixed pipeline of described premixed directional nozzle.

16. method according to claim 15, the pressure of the described air of wherein discharging from described circular passage surpasses the pressure of the described air that enters described circular passage.

17. method according to claim 15, wherein said circular passage is tapered on the direction of its downstream advance.

18. method according to claim 15 is further comprising the steps: from the described circular passage of described premixed directional nozzle, air is discharged towards the direction of the described outlet opening away from described premixed pipeline.

19. method according to claim 18, the described air of wherein discharging from described circular passage is directed away from the described central shaft of described centerbody.

20. the nozzle of the fuel/air mixture for gas-turbine unit, described fuel/air mixture nozzle comprises:

The premixed directional nozzle, described premixed directional nozzle has the upstream extremity of the described downstream that is connected to described centerbody, and described premixed directional nozzle has and the axial opposed downstream of the described upstream extremity of described premixed directional nozzle;

Described premixed directional nozzle further is provided with a plurality of axially extended hollow premixed pipelines, each premixed pipeline has upstream extremity, described upstream extremity is arranged near the described downstream of described centerbody and defines the ingate be communicated with the described internal path fluid of described centerbody, each premixed pipeline is provided with at least one teasehole, and described teasehole is communicated with the described downstream fluid of described fuel feed pipe; Each premixed pipeline has downstream, described downstream is provided with the outlet opening that fluid is discharged from described hollow premixed pipeline, at least each upstream extremity of each premixed pipeline is provided with central shaft, and described central shaft is configured and arranges so that enter the fluid stream of the described ingate of each premixed pipeline and guided by the direction of the described central shaft along being parallel to described centerbody; And

Circular passage, described circular passage radially outward arranges from described premixed pipeline, and described circular passage is configured with the described internal path fluid of described centerbody and is communicated with.

21. fuel/air mixture nozzle according to claim 20, wherein the described upstream extremity of at least one premixed pipeline is provided with central shaft, and the described central shaft of the described downstream of described central shaft and described at least one premixed pipeline is not parallel.

22. fuel/air mixture nozzle according to claim 20, wherein said circular passage is provided with a plurality of air ports in its downstream.

23. fuel/air mixture nozzle according to claim 22, wherein at least one described air port is arranged near a described outlet opening of at least one described premixed pipeline and has the acutangulate central shaft of described central shaft shape with described centerbody.

24. fuel/air mixture nozzle according to claim 23, wherein the described central shaft guiding of at least one described air port is left the air stream court of described air port away from flowing on the direction of the described central shaft of described centerbody.

25. fuel/air mixture nozzle according to claim 20, wherein said circular passage is configured to be tapered on the downstream direction advanced towards described air port.

26. the combustion chamber for gas-turbine unit, described combustion chamber comprises:

Head portion;

Described premixed directional nozzle further defines axially extended a plurality of hollow premixed pipeline, each premixed pipeline has upstream extremity, described upstream extremity is arranged near the described downstream of described centerbody and defines the ingate be communicated with the described internal path fluid of described centerbody, each premixed pipeline is communicated with the described downstream fluid of described fuel feed pipe, each premixed pipeline has downstream, described downstream is provided with the outlet opening that fluid is discharged from described hollow premixed pipeline, each downstream of each premixed pipeline is provided with central shaft, the fluid stream that described central shaft is configured and arranges so that discharges from outlet opening is guided by the direction of the described central shaft along being parallel to each premixed pipeline, and

Circular passage, it radially outward arranges from described premixed pipeline, and described circular passage is configured with the described internal path fluid of described centerbody and is communicated with.

27. combustion chamber according to claim 26, wherein said circular passage is provided with a plurality of air ports in its downstream.

28. combustion chamber according to claim 27, wherein at least one described air port is arranged near a described outlet opening of at least one described premixed pipeline and has the acutangulate central shaft of described central shaft shape with described centerbody.

29. combustion chamber according to claim 28, wherein the described central shaft guiding of at least one described air port is left the air-flow court of described air port away from flowing on the direction of the described central shaft of described centerbody.

30. combustion chamber according to claim 26, wherein said circular passage is configured to along with it is tapered on the downstream direction advanced towards described air port.

31. the method for the nozzle of the fuel/air mixture for operating gas turbine engine, described fuel/air mixture nozzle defines by following: peripheral wall; Be arranged in described peripheral wall and define the hollow central body of central shaft; Swirl nozzle, described swirl nozzle is from the outside extension of the described upstream extremity of described centerbody and radially towards described peripheral wall; And, at the premixed directional nozzle of the described downstream of centerbody, described premixed directional nozzle comprises having a plurality of premixed pipelines of outlet opening, said method comprising the steps of:

In a plurality of axially extended hollow premixed pipelines, described pilot fuel is mixed with described secondary air stream, described premixed pipeline is discharged described fuel/air mixture from the described downstream of described premixed directional nozzle;

By the described secondary air of the part circular passage that circulates, described circular passage is radially outward arranged from the described premixed pipeline of described premixed directional nozzle; And

32. method according to claim 31 is further comprising the steps: from the described premixed pipeline of described premixed directional nozzle, described fuel/air mixture is discharged towards the direction that is parallel to the described central shaft of described centerbody.

33. method according to claim 31 is further comprising the steps: from the described premixed pipeline of described premixed directional nozzle, described fuel/air mixture is discharged towards the direction away from the described central shaft of described centerbody radially.

34. method according to claim 31, the pressure of the described air of wherein discharging from described circular passage surpasses the pressure of the described air that enters described circular passage.

35. method according to claim 31, wherein said circular passage along with it before downstream direction and then be tapered.

36. method according to claim 31 is further comprising the steps: from the described circular passage of described premixed directional nozzle, air is discharged towards the direction of the described outlet opening away from described premixed pipeline.