DE102008037480A1 - Lean premixed dual-fuel annular tube combustion chamber with radial multi-ring stage nozzle - Google Patents

Abstract

A lean premixed radial multi-ring stage nozzle (120) is provided to provide three independent combustion zones in a dual-fuel tubular gas turbine combustor (100). The nozzle (120) comprises a pilot zone (Z1) fueled by a gas pilot nozzle (150) and the center cartridge (155); a flame holding zone (Z2) supplied by an inner main gas fuel; a main flame zone (Z3) supplied by an external main gas fuel; a main radial swirler (120) for mixing a portion of the air flowing to the nozzle (120) with the inner main gas fuel and the outer main gas fuel, and an end cover assembly having external means for controlling an inner main fuel gas and an outer main gas fuel supplied.

Description

BACKGROUND OF THE INVENTION

The This invention relates generally to gas turbine combustors and in particular to a lean premixed radial multi-ring stage nozzle for a dual-fuel annular tube combustion chamber, which dramatically reduces or even eliminates combustion dynamics.

1 shows a combustion chamber according to the prior art for a high-performance industrial gas turbine 10 that a compressor 12 (shown in part), a variety of combustion chambers 14 (for clarity, only one is shown) and a turbine 16 (represented by a single blade). Although not specifically illustrated, the turbine is 16 with the compressor 12 Drivetically connected along a common axis. The compressor 12 sets intake air under pressure, which then turns in the opposite direction to the combustion chamber 14 is directed where to cool the combustion chamber 14 and used as an air supply for the combustion process. Although only one combustion chamber 14 is shown, includes the gas turbine 10 a variety of combustion chambers 14 which are arranged around their periphery. A transition channel 18 connects the outlet end of each combustion chamber 14 with the inlet end of the turbine 16 to the turbine 16 to supply the hot combustion products.

Every combustion chamber 14 includes a substantially cylindrical combustion housing 24 at an open front end on a turbine housing 26 by means of screws 28 securely fastened. The rear end of the combustion housing 24 is through an end cover assembly 30 closed, the conventional supply pipes, manifolds and associated valves, etc. for feeding gas, liquid fuel and air (and water, if desired) into the combustion chamber 14 may include. The end cover assembly 30 takes a variety (for example, five) fuel nozzle assemblies 32 (For the sake of clarity, only one is shown), which in a circular arrangement about a longitudinal axis of the combustion chamber 14 are arranged. Each fuel nozzle assembly 32 is a substantially cylindrical body with a rear feed section 52 with inlets for receiving gas fuel, liquid fuel and air (and water if desired) and a front outlet section 54 ,

In the combustion housing 24 is substantially concentric with this, a substantially cylindrical flow sleeve 34 attached to the front wall with the outer wall 36 the transition channel 18 connected is. The flow sleeve 34 is at its rear end by means of a radial flange 35 with the combustion housing 24 at a butt joint 37 connected to the front and rear portions of the combustion chamber housing 24 are connected.

In the flow sleeve 34 there is a concentrically arranged flame tube 38 at the front end with the inner wall 40 the transition channel 18 connected is. The rear end of the flame tube 38 is through a flame tube cover assembly 42 held, in turn, in the combustion housing 24 through a variety of struts 39 is held. It can be seen that the outer wall 36 the transition channel 18 as well as the part of the flow sleeve 34 which extends from the point where the combustion housing 24 to the turbine housing 26 (by means of screws 28 ) is bolted to the front, with an array of holes 44 are formed in their respective peripheral surface to the flow of air in the reverse direction of the compressor 12 through the holes 44 in the annular space between the flow sleeve 34 and the flame tube 38 to the upstream or rear end of the combustion chamber 14 to allow (as indicated by the in 1 shown flow arrows shown).

The flame tube cover assembly 42 carries a variety of premix tubes 46 , one for each fuel nozzle assembly 32 , More precisely, each premix tube 46 in the flame tube cover assembly 42 at its front and rear end by a front or a rear plate 47 . 49 each of which is equipped with openings that end up with the premix tubes open at the end 46 aligned. The premix tubes 46 are held so that the front inlet sections 54 the respective fuel nozzle assemblies 32 are arranged concentrically in them.

The back wall 49 takes a multitude of floating floating bushes 48 (one for each premix tube 46 ), which essentially matches the openings in the back wall 49 aligned. Every floating bush 48 holds an annular air swirl body 50 that the respective fuel nozzle assembly 32 encloses. Radial fuel injectors 66 are downstream of the swirl body 50 for discharging gas fuel into a premixing zone 69 provided in the premix tube 46 located. In this arrangement, in the annular space between the flame tube 38 and the flow sleeve 34 flowing air to again reverse their flow direction at the rear end of the combustion chamber 14 (between the end cover assembly 30 and the sleeve cap ( 42 ) and must through the swirl body 50 and the premix tubes 46 flow before entering the combustion zone or combustion chamber 70 in the fire tube 38 , downstream of the premix tube 46 , entry. The ignition is in the different combustion chambers 14 by means of a spark plug 20 in connection with Durchzündrohren 22 (one of which is shown) achieved in the usual way.

In the construction of power plants, the reduction of harmful gas emissions, such as nitrogen oxides (NOx), into the atmosphere is a major concern. To address this problem, low-NOx combustors have been developed which employ lean premixed combustion with a plurality of burners mounted on a single combustor, such as those disclosed in US Pat 1 will be shown. Each burner includes a flow tube having a centrally located fuel nozzle that includes a cylindrical hub that carries fuel injectors and an air swirler and that has a flat surface at its downstream end. In addition to a premix injection stage for low NOX operation, each fuel nozzle may include a startup and emergency mode diffusion injection stage and a liquid fuel injection stage for liquid fuel operation.

Diffusion gas fuel and liquid fuel are typically through openings injected, which are located at the flat end of the fuel nozzle. While In low NOx (premix) operation, fuel is injected through the fuel nozzles and mixes with the swirl air in the flow tube. The diffusion and liquid fuel circuits typically during the Premixed operation flushed with air, to flame gases from the channels keep. The combustion flame is behind by baffle recirculation the fuel nozzle and - at Presence of spin - swirl degradation stabilized. In premixed systems are typically called Result of combustion instabilities strong pressure oscillations generated. It is assumed that the combustion instabilities with the replacement spanwise vortex from the blunt end of the fuel nozzle in conjunction stand. These pressure oscillations can affect the operation of the device severely restrict and in some cases even a physical damage cause the combustor hardware. Further, the flow of purge air through the diffusion and liquid fuel cycle injected directly into the recirculation zone. This direct injection reduces the local temperature and strength of the recirculation, which adversely affects the flame stability. Consequently, there is a need for a low NOx combustion chamber with reduced pressure oscillations, at the the adverse effects of injecting purge air directly be avoided in the recirculation zone.

As previously described, these modern industrial high performance DLN ring tube gas turbine combustors utilize (DLN = Dry Low NOx) usually a plurality (or "group") of premix nozzles that are connected to a tube combustion chamber flame tube, with a flat or angled lid / Dombaugruppe is provided. Several Nozzles are for mixing and grading of the fuel required to controllability (turndown) and performance in the total operating capacity envisaged. and design space. However, this method is obtained a complicated and expensive assembly.

Besides that is the even distribution of Air and fuel to the group of premix fuel nozzles at the head end difficult and leads generally to a non-ideal, non-uniform airflow to all nozzles or to a parasitic Pressure drop / pressure loss to a significant extent. Swirl stabilized, lean premixed combustion is compared to conventional Diffusion combustion tends to be very susceptible to combustion-induced vibrations (dynamic Instability).

Historical In the gas turbine engine industry, the flame temperature has been considered (or primary zone temperature) reduced in lean premixed systems to reduce NOx emissions to diminish. With the reduction of acceptable NOx emission levels down to single-digit ppm values (ppm = Parts per million) - caused mainly through new state regulations - became the flame temperature is very close to the lean limit (lean-blowout limit, LBO limit) pushed, at least as far as fuels with a high methane content are concerned. In such lean mixtures result in low periodic fluctuations the local fuel-air ratio to relatively large periodic variations in local heat release and heat release rates, which even includes a local, temporary flame extinction. The Amplitude of discrete vibration frequencies (or sounds) can increase when the fluctuations of the heat release in phase with the in the combustion chamber occurring acoustic pressure fluctuations.

There Today's lean premixed combustors become "leaner" and spatially more uniform to comply with ever lower emission targets, which are increasing Dimensions complied with need to be while combustors simultaneously with an ever-increasing bandwidth fueled by a given system the risk of having unacceptably high combustion dynamics levels occur.

Although DLN gas turbine ring tube combustion systems have been tested with a large single nozzle, most have failed of operational readiness, durability and emission problems. The lack of intelligent, adjustable operating parameters, as well as the lack of independent, tiered combustion zones, has led the industry to accept modular multi-nozzle configurations. Multi-nozzle designs enable stepped fuel distribution on nozzle subassemblies, not only to facilitate start-up and control, but also to provide an adjustable operability parameter to avoid dynamics (or vibrations) occurring during operation in the engine Design / operating range occur.

Of the Disadvantage of the graded fuel distribution in the combustion chamber is the emergence of hotter temperature zones, that drive NOx production. Is therefore too much gradation required, to eliminate the combustion dynamics or instability could be prescribed NOX emission limits exceeded be, whereby the plant except Operation could be set. Combustion dynamics in lean premixed combustion in industrial Gas turbines are typically passively reduced by several methods - usually in a trial and error procedure that expensive and unsafe. Some of these procedures are listed below: 1) shift the fuel injection points to the time for transportation to change the fuel from the injection point to the flame front, 2) change the size of the fuel injection holes to change the pressure drop and the acoustic impedance across the holes, and 3) modification the chamber or nozzle geometry (eg the diameter, angle, lengths), the vortex shedding, the Frequencies and amplitudes and the flame shape in the chamber too influence.

By These methods try to force that any disturbance of the heat release phase-shifted (destructive interference) with pressure or acoustic disorders takes place in the combustion chamber. The combustion chamber dynamics could also by acoustic damping (eg Helmholtz resonators or quarter wave tubes) of the combustion system can be reduced or eliminated. In the In the past, the above methods tend to be more likely backdated considered after the discovery of high combustion chamber dynamics and executed, instead of during the initial one Planning phase of the program with proactive planning in mind.

consequently there is a need a simpler, scalable, lower cost premixed leaner Combustion chamber available at any load within the design / operating range with much less probability discrete combustion oscillations arouses or drives while they are also above average Tolerance in terms of quality of the fuel mixture shows. Would the above solution and consequently the risk that in the given design operating range ever a discrete momentum occurs, significantly reduced, then would be the Efficiency and the probability of adjustment (Tuning) of a given system for minimum emissions significantly larger. in the It would be essential the momentum no longer such a significant and a problematic part of the entire combustor design process.

BRIEF DESCRIPTION OF THE INVENTION

The The present invention relates to a device and a Procedure for the creation of three independent Combustion zones in a gas turbine combustor with a lean premixed radial multi-ring stage nozzle, whereby for one stable combustion with low nitrogen oxide emissions (NOx emissions) is taken care of.

Short said, according to one Aspect of the present invention, a lean premixed, radial multi-ring stage nozzle provided to in a dual-fuel tubular gas turbine combustor, three independent combustion zones to accomplish. The lean premixed, radial multi-ring stage nozzle (hereafter as a big one Single radii nozzle includes) a pilot zone passing through a center cartridge is supplied with fuel; a flame retardant zone through an indoor main gas feeder is supplied; a main flame zone, which supplies by an outside main gas supply becomes; a main radial swirler for mixing a part of the air flowing into the nozzle with the inner main gas supply and the outside main gas supply; an end cover and arrangements for the regulation of the ratio supplied pilot gas fuel, Indoor home gas fuel and exterior home gas fuel.

According to another aspect of the present invention, there is provided a dual fuel annular tube combustor for a gas turbine engine. The combustor includes a radial multi-ring stage nozzle (hereinafter referred to as a large single-radial nozzle) that includes an outer burner tube and a main radial swirler mounted on an end cover of a combustor shell. A main combustion zone is located downstream of the outer burner tube of the large Einzelradialdüse. A compressor serves as a compressed air source. An air inlet plenum radially encloses the large single radial nozzle and is radially bounded by an outer wall of the combustion chamber. A diffuser for the compressed air picks up the compressed air in a reverse flow path from the compressor and releases the air at a restored pressure into the inlet plenum. A fairing mounted on the main radial swirler and enveloping a portion of the outer burner tube is provided for smoothing the flow of air from the diffuser to the air inlet plenum.

According to one Third aspect of the present invention is a method for the Use of a radial multi-ring stage nozzle (hereinafter referred to as large single radial nozzle) with independent Combustion zones available put, the big one Einzelradialdüse a pilot zone, a flame holding zone and a main zone in one Gas turbine combustor includes, for a stable combustion with low nitrogen oxide (NOx) emissions. The procedure includes the supply of a large Amount of air to the nozzle, one nozzle internal Gradation, the decomposition of heat release in a variety of discrete zones in space, distribution of heat release over the Time and ventilation a downstream central recirculation zone.

BRIEF DESCRIPTION OF THE DRAWINGS

These and other features, aspects and advantages of the present invention Invention are better understood, if the following detailed description with reference to the accompanying drawings, in which like reference numerals consistently refer to the same parts.

1 shows a combustion chamber of the prior art with a plurality of nozzles;

2 shows an embodiment of a combustion chamber according to the invention with a combustion chamber according to the invention with a large Einzelradialdüse;

3A Fig. 10 is a partial isometric view showing an internal structure of an embodiment of the large single-jet nozzle of the present invention;

3B Fig. 10 is an axial cross section showing an internal structure of an embodiment of the large single-jet nozzle according to the present invention;

4 Fig. 11 is a view of the feeding end of the end cover plate of one embodiment of the large single radial nozzle according to the present invention;

5 shows fuel distributions and feedthroughs in the end cover and rear wall of one embodiment of the large single radial nozzle according to the invention;

6A shows an isometry of a Hauptradialdrallkörpers an embodiment of the large single radial nozzle according to the invention;

6B shows details of main spin nozzles on the main radial swirl body of an embodiment of the large single radial nozzle according to the invention;

6C shows a view of the main radial swirler of an embodiment of the large single radial nozzle according to the invention;

6D shows a section through the main spin nozzles and the central hub of the Hauptradialdrallkörpers an embodiment of the large single radial nozzle according to the invention;

6E shows a section through the rear wall and the central hub of the Hauptradialdrallkörpers an embodiment of the large single radial nozzle according to the invention;

7 Fig. 12 is a cross-sectional view of the head end of the combustor of the present invention showing the air flow and the independent combustion zones of one embodiment of the large single radial nozzle of the present invention;

8th shows the central flame holder, the gas pilot annulus, and the center cartridge of one embodiment of the large single radial nozzle according to the invention;

9A and 9B show the nozzle body of the gas pilot nozzle of an embodiment of the large single radial nozzle according to the invention;

10 shows an axial section of a dual-fuel central cartridge of an embodiment of the large Einzelradialdüse invention and

11 shows an alternative embodiment of the flame holder cup of the large single radial nozzle according to the invention.

DETAILED DESCRIPTION THE INVENTION

The following embodiments of the present invention have many advantages, including some innovative, very particular features: (1) it is possible to have multiple (eg six) premix nozzles (per pipe) and one combustion chamber lid through a single large radial nozzle and a modification of the Flame tube can be replaced, whereby a significant reduction in the number of parts, a cost savings and a drastic simplification of the head end of the combustion chamber is achieved; (2) the use of a dome diffuser construction to the Cooling the flashback dome at the rear convection while simultaneously restoring the static pressure prior to the premixing of the fuel and air in the large single radial nozzle thereby reducing the parasitic pressure loss and making more air available to the premix; (3) Provide capacity for rapid (eg <3 ms) and thorough evaporation and mixing of large quantities of fuel (~ 2 lbm / sec, ie approx. 0.907 kg / sec) and air (~ 60 lbm / sec, ie about 27.21 kg / sec) with a relatively low pressure drop (eg <4%) and (4) using either gas fuel or liquid fuel, it is dynamically more robust and less prone to combustion-induced vibrations than today's lean premixed Gas turbine combustion systems in which both heat release (in time and space) and fuel transport time in the chamber are strategically distributed (smeared out) while still maintaining the required system control performance and low exhaust emissions.

The Effects of the construction are manifold: (1) the replacement of five or five more nozzles per pipe through one leads to a drastic reduction of the costs and the number of parts; (2) the drastic reduction or even complete elimination of combustion dynamics / combustion vibrations with discrete frequencies in combustion chambers of industrial gas turbines, while maintaining the prescribed emission levels; (3) flexibility in relation to gas and liquid fuels, associate with the successful improvement of combustion dynamics; (4) DLN with liquid fuels like diesel fuel (No. 2 diesel oil), with simultaneous elimination the need for water injection and the need for high pressure atomizing air and (5) low-single-emission (ppmv) emissions.

Of the successful transition from a multi-nozzle arrangement to a single nozzle requires a nozzle internal Increments. A zone of angled, v-shaped flame holders, such as used in this construction provides a range for fuel staging in the main premix nozzle. For example, can affect the fuel-air ratio - so it near the hub (or the central body) it is fatter - it enable, that a central flame holding zone in relation to the bypass current at burns at a higher equivalence ratio, which is beneficial (or even necessary) for the ignition and engine acceleration, low load operation or dealing with sudden load shifts can be. Influencing the fuel-air ratio in Connection with other staging features (for example, a premixed pilot) allows the Replacing multiple nozzles (eg, six) per tube in gas turbine combustion systems a big Einzelradialdüse, which is a significant reduction in the number of parts and the cost for the Combustion system and the engine would mean a total. A reduced combustion dynamics would achieved while at the same time exhaust emissions (eg unburned hydrocarbons (UHC), NOx and carbon monoxide (CO)) in relation to the firing temperatures maintained or even reduced in the design space.

at the lean premixed radial multi-ring stage nozzle (hereinafter referred to as large single radial nozzle) it is by design less likely that combustion-induced, discrete Vibration frequencies are excited when the specified proportion (eg, about 33% of the reactants in the die) of the well-mixed reactants is diverted upstream as an angled array of discrete v-shaped gutter zones to burn the main chamber. The arrangement of axial rays, the the conical bundle of v-shaped gutters happen, reduces discrete dynamics and improves emissions in different ways.

First decomposes the arrangement, the heat release into a multitude of discrete reaction zones in space, each one much smaller than the entire combustion chamber. This limits efficiently the amount of energy in the chamber at a given acoustic Resonant frequency for a constructive overlay to disposal stands.

Secondly Due to the angled v-grooves, a large number of fuel transport times is created causing the heat release distributed over time. That is, for each point along the length of the There is a v-gutter an associated transport time: the time between the Time / points of fuel injection and the time / the Timing of combustion. This also effectively limits the released amount of heat energy, in the chamber at a certain acoustic resonant frequency a positive feedback to disposal stands.

Third, the function of the Entdrall bundle is the "venting" of the downstream central recirculation zone (ZRZ), which results from vortex breakdown From the central cone, the expanding jet assembly injects a non-pulsing axial impulse directly into the ZRZ, causing the This reduces the nitrogen oxide (NOx) production by reducing the average residence time of the combustion product molecules at the primary zone temperature (flame temperature) in the combustion chamber in the NOx genera 1593.33 ° C (2900F), where the thermal NOx mechanism (or: Zeldovich mechanism) begins to accelerate and its contribution to the NOx levels of the overall system increases considerably.

The Nozzle points also an anti-coke construction (anti-coking construction) for the Operation with liquid Diesel fuel on which neither water nor atomizing air needed. Aspects of this construction prevent in the interest of a high reliability fuel channel coking through an insulated fuel channel wall. The liquid fuel is atomized very quickly and thoroughly distributed in the premixer airflow, being separated from hot surfaces of the Pre-mixer is kept off, so it evaporates and quickly mixed with the air. The liquid injection measure has an effect not detrimental to the gas operation. Furthermore, there is a Cost savings due to the fact that no more water injection and high-pressure atomizing air needed become.

The full Fuel-air mixing is very fast (approx 2 ms), thoroughly (greater than 97%) and requires a low pre-mixer differential pressure (~ 2%), whereby the required pre-mixer residence time is reduced, so that a shorter, more compact construction is created and one below the Selbstentzündungszeit diesel under "advanced" gas turbine conditions can stay.

Various Other aspects and advantages of the invention will be apparent in the Description clearly. The controllability (turndown capability) is determined by Improved fuel staging (3 pseudo-independent combustion zones). By using a back cooled Doms is not air for cooling the flame tube in the flame zone required.

In addition, sets the axisymmetric, radial Verbrennungsstufung the flame tube no asymmetric load, which increases the durability of the Flame tube is improved.

Further becomes the internal flame holding resistance / flame holding limit of the Pre-mixer improves: the flow through the entire premixer nozzle is accelerated; the volume velocity is above about 91.44 m / sec (300 ft / sec).

When the two parameters to be optimized became a v-groove tilt angle (Radial plane axial plane) and the Entdraller blade profile selected. Of the The v-groove inclination angle was varied between 30 ° and 60 ° to the angle of inclination to maximize while maintaining a well-defined, continuous v-gutter wake flow to generate an independent Combustion zone support. With unresponsive CFD, the 40 ° configuration was the largest angle the at constant other nozzle features nor a continuous v-trough wake flow generated. The Entdraller blade profile was successfully adjusted / optimized, by aligning the inlet vane angle with the incoming swirl flow and using the cascade geometry, the flow through the bundle was accelerated, thereby avoiding any flow separation in the bundle.

2 shows an embodiment of the large single radial nozzle according to the invention, which is used in a combustion chamber according to the invention. The combustion chamber 100 with a large single radial nozzle comprises a substantially cylindrical combustion chamber housing 105 which can be securely attached to a transition piece (not shown) at an open front end for connection to a turbine by inserting a fire tube into the transition piece. The transition piece may then be securely fastened in the usual manner by means of screws to an open front end of a turbine housing. The rear end of the combustor housing is replaced by an end cover assembly 130 closed, which can be adapted for conventional package supply pipes, manifolds, valves and fittings for gas fuel, liquid fuel, air, and electricity (not shown). The end cover assembly 130 is part of a large single radial nozzle assembly 120 and attaches them to the combustion chamber housing 105 ,

In the combustion chamber housing 105 is - essentially concentric to this - a flow sleeve 106 assembled. Inside the flow sleeve 106 is the fire tube 110 concentrically arranged and at its front end 112 connected to the inner wall of the transition part into which it is inserted. The rear end of the flame tube 110 forms a frustoconical dome 111 on a main combustion chamber 114 , wherein the frustoconical dome 111 in the middle is open for the flow of fuel and combustion products from the large single radial nozzle 120 and further engagement with the outer burner tube 113 the big single radial nozzle 120 ,

Air for the combustion process may be removed from the air compressor into the transition part (as previously described with reference to FIG 1 described), and from there through the annular space 115 be pulled between the flow sleeve and the outer wall of the flame tube. At the rear end of the annular space, a concentrically mounted diffuser stretches 116 the air in the inlet plenum 117 the big radial nozzle 120 out. The cathedral 111 serves as a concentric inner wall of the diffuser 116 , whereby the back cooling of the dome 111 through the through the diffuser 116 flowing air is made possible. At the same time, the diffuser 116 the static pressure of the air before the premix of fuel and air in the large radial jet 120 which causes the parasitic pressure loss to be reduced and more air available for the premix. A railing 118 around the center of the large radial jet 120 smoothes the air inlet into the inlet plenum 117 , which further reduces parasitic pressure loss.

The big radial nozzle 120 further comprises a main radial swirler 140 , a gas pilot nozzle 150 , a central flame holder with a v-gutter flame holder 160 , and an outer flame holder 170 , The central flame holder 160 and the outer flame holder 170 open at their front end to the main combustion chamber 114 ,

The end cover 130 may be a generally cylindrical flange designed for use with a combustor housing 105 mesh and the radial nozzle assembly 120 in the combustion chamber 100 to wear. The back surface 135 the end cover 130 is equipped with bushings for "dual-fuel" (gas and liquid fuel) and for the gas pilot nozzle 150 Mistake. An outdoor main gas supply 190 , an indoor main gas supply 190 and one of the many LPG connections 195 are in 3A shown. The arrangement of the fuel and air ducts allows connection to existing combustor configurations of the fuel, air and power lines (not shown).

3A Fig. 12 is a partial isometric view showing an internal structure of one embodiment of the large single-jet nozzle of the present invention. 3B FIG. 11 is an axial cross section showing an internal structure of one embodiment of the large single radial nozzle according to the present invention. The nozzle is axisymmetric to a central axis 200. ,

The end cover assembly 130 includes an end cover plate 205 with a rear section 201 , a front section 202 and a central cavity 203 , A main radial swirler 140 includes a back wall 240 , a variety of swirl blades 250 and a central hub 260 with a central cavity 265 in this. The back wall 240 is on the mounting surface 241 to the end cover plate 205 screwed.

A central flame holder 160 is on the central hub 260 assembled. A central hub 285 of the central flame holder 160 grabs the central hub 260 of the main radial swirler 140 into each other, around the central flame holder 160 to hold radially and axially. Radial blades 360 carry from the central hub 285 the inner burner tube 300 , A variety of v-grooves 290 runs between the inner burner tube 300 and the central hub 285 , A central cavity 278 is in the central hub 285 educated. On the swirl blades 250 of the main radial swirler 140 is an outer flame holder 170 with a cylindrical outer burner tube 175 mounted, with a base section 180 which widens radially outward and by means of screws 183 at the top of the swirl blades 250 is attached. The downstream end 178 of the outer burner tube 175 also widens outward and is reinforced to the conical dome 111 ( 2 ) of the combustion chamber to trim. The support bar 179 engages with the conical combustion chamber dome 111 each other. A fuel-air mixture flows from the main radial swirler 140 by 402 to a flame holding zone and through 405 to the main zone ( 7 ). The central cavities 203 . 265 and 278 allow insertion of a gas pilot nozzle 150 with a gas pilot and a center cartridge comprising a liquid fuel pilot and an ignition device.

4 shows a rear view of the Endabdeckungsplatte an embodiment of the large Einzelradialdüse according to the invention with respect to a combustion chamber in which it could be installed. The end cover plate 205 includes the integrated cylindrical rear section 201 and a cylindrical front portion 202 ( 3A ) with a smaller diameter, with both layers on the central axis 200. the nozzle are centered. The rear section 201 is radially dimensioned to mesh with a rear seating surface of the combustion chamber (not shown) and includes a plurality of screw holes 206 formed axially adjacent to the outer peripheral surface 207 of the outer section 201 located, and serve for attachment to the seating surface of the combustion chamber. The rear section 201 can also have a variety of pilot openings 208 (rectified) for the positioning of the rear section 201 with respect to the seating surface of the combustion chamber in preparation for screwing. The front ride-on flange 205 of the front section 202 can also have a variety of screw holes 209 in a circular, to the central axis 200. The nozzle concentric arrangement, which are adapted to screws from the mounting surface 241 the back wall 240 of the main radial swirler 250 ( 3A ).

Two independent gas fuel feeds can be attached to the end cover plate 205 be connected. The rear section 201 includes an outdoor main gas duct 215 to an egg an external main gas supply inlet pipe 216 with an external main gas inlet flange 217 is attached, for connection with the outer main gas fuel supply (not shown). The rear section 201 also includes an indoor main gas duct 220 with a fitting 219 for connection to an indoor main gas supply (not shown). The end cover plate 205 can also handle a variety of liquid fuel feed penetrants 243 which are concentric with the central axis 200. the nozzle are arranged.

4 also shows the rear end of the gas pilot nozzle 150 , The central cavity 203 is inside the end cover plate 205 defined and extends radially from the central axis 200. and through the back section 201 and the front section 202 - for inserting a gas pilot nozzle. The central cavity 203 includes a gas pilot nozzle seat 210 ( 3B ) with threaded connections for meshing with the rear flange 212 a gas pilot nozzle, around the gas pilot nozzle 150 to assemble

5 shows fuel galleries in the end cover and the rear wall of one embodiment of the nozzle according to the invention. The outer main gas passage 215 ( 4 ) is with an outer main gas channel 310 in the end cover plate 205 connected. The outer main gas channel 310 defines an annular chamber concentric with the central axis 200. the nozzle is. The inner wall 311 and the outer wall 312 the outer main gas channel 310 can in terms of the central axis 200. the nozzle be arranged radially, so that the open upper end 315 the outer main gas channel 310 with a plurality of corresponding outer main gas channels 665 ( 3B ) in the back wall 240 of the main spin body is connected.

The inner main gas penetration 220 is with an inner main gas channel 330 in the end cover plate 205 connected. The inner main gas channel 330 defines an annular chamber concentric with the central axis 200. the nozzle is. The inner one 317 and the outer wall 318 of the interior main gas channel 330 can go to the central axis 200. be concentric with the nozzle. The indoor main gas channel 330 is radially between the outer main gas channel 310 and the central cavity 203 arranged. The inner one 317 and the outer wall 318 of the inner main gas channel are arranged radially, so that the open upper end 319 of the interior main gas channel 330 with the corresponding indoor main gas channels 680 ( 7 ) in the back wall 240 of the main swirler is connected to the inner main gas injection points 695 on the base surface 242 between the swirl vanes 250 To supply indoor main gas.

The liquid fuel feed ducts 243 run axially through the rear section 201 the end cover 205 and are with a major liquid fuel channel 244 connected. The main liquid fuel channel 244 defines an annular chamber facing the central axis 200. the nozzle concentric and except for the liquid fuel feedthroughs 243 and the liquid fuel exit bushings 246 is sealed. The main liquid fuel channel 244 is radially arranged to communicate with the liquid fuel feed ducts rear 243 and the liquid fuel exit ducts 246 at the front on the end cover plate 205 to flee. The liquid fuel outlet bushings 246 pass through the front section 202 the end cover 205 to comply with appropriate liquid fuel outlet bushings 247 in the back wall 240 of the main radial swirler leading to the atomizers 248 for the liquid fuel in the back wall 240 lead the main spin body. The walls of the main liquid fuel channel 244 and the liquid fuel supply passage and the liquid fuel discharge passage 246 in the end cover 205 and the fuel outlet bushings 247 in the back wall 240 can with an insulated lining 249 to maintain the wall temperatures below approximately 143.33 ° C (290 ° F) since at that temperature the diesel liquid fuel begins to coke. The fittings 218 are provided outside the liquid fuel feed ducts for connection to the liquid fuel feed.

Because the end cover plate 205 and the back wall 240 of the main swirler in a metal-on-metal seating surface 241 Interlock is used to isolate potential leaks from the fuel cavities along the seating surfaces 204 . 241 taken care of. Three annular recesses ( 5 ), concentric with the central axis 200. the nozzle, can on the upper seating surface 204 the end cover plate 205 be provided. The first recess 381 is outside the outer main gas channel 310 intended. The second recess 382 is between the outer main gas channel 310 and the inner main gas channel 330 intended. The third recess 383 is at the inner main gas channel 330 intended. The recesses may be provided with C-rings or other suitable sealing material to prevent flow along the seating surfaces.

The 6A - 6E show views of a Hauptradialdrallkörpers an embodiment of the nozzle according to the invention. 6A shows an isometry of a Hauptradialdrallkörpers an embodiment of the nozzle according to the invention. 6B shows details of main swirl vanes on the main radial swirler of one embodiment of the invention proper nozzle. 6C shows a crack on the Hauptradialdrallkörpers an embodiment of the nozzle according to the invention. 6D shows a section through the main swirl vanes and the central hub of the Hauptradialdrallkörpers an embodiment of the nozzle according to the invention. 6E shows a section through the rear wall and the central hub of the Hauptradialdrallkörpers an embodiment of the nozzle according to the invention.

The main radial swirler 140 includes a back wall 240 with an integrated central hub 260 , a variety of main swirl blades 250 on the back wall 240 are mounted and orthogonal to the back wall 240 (downstream of the combustion zones) protrude, a central cavity 265 to the gas pilot nozzle 150 and accommodate a series of interior channels in the back wall, as well as main swirl vanes 250 to provide a flow of fuel and air.

The back wall 240 includes a cylindrical flange located on the central axis 200. the nozzle is centered. A base surface 241 the back wall 240 is dimensioned radially with the front surface 204 the end cover plate 205 mate. The mounting surface 242 the back wall includes a plurality of recesses 371 in which screw holes 372 around the periphery of the back wall 240 are housed. The screw holes 372 extend through the base surface 241 the back wall 240 and aligned with the screw holes 209 on the front 204 Surface of the end cover plate 205 , The mounting surface 242 the back wall 240 is used to mount a variety of main swirl blades 250 and housing housing injection points for the injection of fuel into an air stream in the main radial swirler 140 ,

The variety of main swirl blades 250 each of which is a solid metal airfoil 610 includes, may be orthogonal to the back wall 240 be mounted and protrude axially in the direction of the combustion zones. The main swirl blades 250 can be radially inward from the peripheral screw hole recesses 371 and radially outside of the central hub 260 be mounted. A leading edge 615 each airfoil projects generally radially outward, and a leading edge 620 generally projects radially inward. The axis 625 Each airfoil can be radiused 635 from the central axis 200. the nozzle a given acute angle α (about 15 °) 630 form. While the leading edge 615 of the airfoil 610 forms a curved surface, the side surfaces can 640 . 641 of the airfoil 610 in a straight line to the common linear leading edge 620 rejuvenate. The companies 645 and top 650 of the airfoil 610 form even surfaces. The bottom 645 Can be applied to the mounting surface by welding or other suitable method 242 the back wall 240 to be assembled.

A variety of injection points 655 for external main gas fuel are along one to the central axis 200. the nozzle concentric radius, on a side surface 640 of the airfoil 610 , slightly inward of the curved leading edge 615 intended. The injection of outer main gas fuel becomes approximately perpendicular to the air flow passing between the adjacent swirl vanes 660 performed. The injection points 655 however, may also be provided on both side surfaces of the airfoil and at other locations than in the present embodiment. The injection points may be approximately equally axial along the side surface 640 of the airfoil 610 be spaced to the even distribution of the outer main gas fuel in the air flow 660 between the blades 610 in a circumferential premixing room 605 to enable. The blades 610 further include an internal fuel cavity 665 that the injection holes 657 provided. The fuel cavity 665 may be a generally cylindrical opening extending from the pedestal surface 241 axially in the airfoil 610 extends, near the injection holes 657 is located and connected to these. The fuel cavity 665 conducts external main gas fuel out of the fuel cavity 310 in the end cover plate 205 , The injection holes 657 in every blade 610 extend with respect to the cylindrical fuel cavity 665 in the radial direction, around the injection points 655 To supply fuel. The top 650 each airfoil 610 can also have a threaded hole 670 for secure attachment of the outer burner tube 175 at the main swirl blades 250 include.

The indoor main gas ducts 680 ( 7 ) in the back wall 240 run from the inner main gas channel 330 in the end cover plate 205 axially to the mounting surface 242 the back wall 240 , An opening 685 can in any of the indoor main gas ducts 680 be provided to regulate the gas release. The injection points 690 are on the mounting surface 242 approximately equidistant from the side surfaces 640 . 642 neighboring blades 610 and a point approximately in the middle of the side surfaces 640 . 642 the adjacent blades 610 intended. For exemplary 24 blades 610 , are 24 injection points 690 intended. A nozzle tip 695 at every injection point 690 slightly above the mounting surface 242 the back wall 240 protrudes, causing the gas above the laminar air flow is injected on the mounting surface.

In the above-described gas operation, gas fuel becomes the air flow of the main radial swirler 140 from a variety of injection points 655 injected from the axially along the side walls 640 the blades 610 and the injection points 695 on the mounting surface 242 the back wall 240 are arranged. The main gas fuel is supplied from two independent supply sources, as in 4 shown in the radial profile of the fuel-air mixture in an annular swirl volume (premixer annulus) 255 to influence. That is, the mixture near the central hub 260 which eventually flows through the central flame holder may relative to the mixture in the vicinity of the swirl vanes 250 (bypassing the central flame holder) may be made firmer or leaner by varying the ratio of the fuel supply from the two sources. External means may be provided for the regulation of this ratio of an input main internal fuel gas and a supplied external main gas fuel. This may include control throttling, pressure control, or other known means that may be used outside the nozzle.

A variety of liquid fuel injection points 245 is also on the mounting surface for operation with liquid fuel 242 the back wall 240 intended. The liquid fuel injection points 245 are on the liquid fuel exit channels 246 in the back wall 240 arranged. The liquid fuel channels 246 in the back wall 240 can be a thermally insulating layer 249 include. The liquid fuel injection points 245 lie concentric to the central axis 200. and may be used to inject liquid fuel into the annular swirl volume 255 approximately at the place of the trailing edges 620 the blades 610 be positioned. In an exemplary arrangement, six liquid fuel injection points are 245 circumferentially equidistant about the mounting surface 242 intended. Each liquid fuel injection point 245 is with a tip 252 provided a cone shaped atomizer 248 that covers the thread 253 of the liquid fuel exit channel 247 is screwed. The atomizer 248 sprays liquid fuel in an axial direction perpendicular to the mounting surface 242 in the airflow.

7 Figure 10 is a cross-section of the head end of the combustor of the present invention showing the airflow and the fuel-air stream producing the independent combustion zones of one embodiment of the nozzle of the present invention. As previously described (s. 5 - 7 ) provides the combustion chamber according to the invention with the large Einzelradialdüse three independent combustion zones. The gas pilot nozzle 150 creates a pilot combustion zone Z1. The flame holder combustion zone Z2 is replaced by the axial flow from the Entdraller 280 created over the v-grooves 290 in the central flame holder 160 flows. The main combustion zone Z3 is created by the fuel-air mixture between the inner burner tube 300 of the central flame holder 160 and the outer Bren nerrohr 175 the outer flame holder 170 into the main combustion chamber 114 flows.

An airflow from the diffuser 116 flows into the inlet plenum 117 , The main swirl blades 250 make a flow path 660 for from the inlet plenum 117 inflowing air for the combustion chamber ago. About 95% of the air entering the nozzle flows between the main swirl vanes 250 by. After outside main gas from the airfoils 610 and indoor main gas from the injection points 690 on the mounting surface 242 and / or liquid fuel from the atomizers 248 injected into the incoming air, this is through the blades 610 steered so that they counterclockwise (seen from the end of the combustion) through the annular swirl volume 255 (the volume between the swirl vanes and the central hub) swirls. In the annular swirl volume 255 the continuous turbulence further mixes the fuel with the air.

The central hub 260 includes an outer frusto-conical surface located on the central axis 200. the nozzle is centered to minimize the flow resistance to a circumferentially flowing fuel-air mixture from the main swirl vanes, while in the central flame holder 160 rises. The central hub 260 Forms a smooth surface resulting from the mounting surface 242 the back wall 240 rises and concavely inwardly sloping to a radial and axial support for the central flame holder 160 to build. In its frustoconical upper area is the central hub 260 with an outer annular support bar 273 for the central flame holder 160 Mistake. The inner surface 263 the central hub 260 defines a cavity 265 , a gas pilot nozzle 150 and an inner flow path for air to the Gaspilotdüse 150 includes. The inner surface 263 the central hub further includes an inner annular mounting bar 274 for the central flame holder 160 ,

The series of inner channels in the rear wall includes outer main gas channels from the outer main gas channel in the end cover to the swirl vanes; for the inner main gas passage in the end cover to the gas injection nozzles on the mounting surface of the rear wall; for liquid fuel from the liquid fuel outlet bushings in the end cover to the atomizers on the assembly surface of the rear wall and air ducts from the peripheral outer edge of the rear wall to the central cavity for cooling and pilot premixed air to the radial nozzle centers / cores.

The inner channel 680 for indoor home gas to indoor home gas injector tips 695 on the mounting surface 242 the back wall 240 can have openings 685 for controlling the gas flow rates to the gas injector tips 695 in each channel. The outer peripheral surface 257 the back wall 240 includes a plurality of radial feed openings 275 going inward to the central cavity 265 are directed to the central cavity 265 to supply a flow of cooling air and pilot premix air. The axial channels in the back wall for outside main gas 270 , Indoor main gas 680 and liquid fuel 247 are located at circumferential locations between the various radial feed ports 275 ,

The central flame holder 160 Can a central hub 285 , a central cavity 278 , a derangement 280 , a variety of v-gutters 290 , an inner burner tube 300 and a carrying tower 295 include.

Because the air flow from the area between the main swirl vanes 250 in the annular swirl volume 255 is forced into a rotational flow, the only exit path is downstream. Circa 30 in the main radial swirler 240 turbulent fuel-air mixture enters the central flame holder 160 one. The central flame holder 160 includes the carrying tower 350 who is on the central hub 260 of the main radial swirler 240 sitting. The carrying tower 350 engages with the outer support bar 273 and the inner support bar 274 the cylindrical bearing hub of the central hub 260 into each other, around the central flame holder 160 to support axially and radially. The support arm 355 of the carrying tower 300 lies on the outer support bar 273 and the inner support bar 274 on. A central cavity 280 in the tower 295 and the central hub 285 can the gas pilot nozzle 150 take up.

In 8th sit on the support tower 295 the derangler 280 and the concentric, hub-mounted, conical, v-groove flameholder bundles. The Entdraller 280 includes a plurality of annular compartments 345 between the central hub 285 and the inner burner tube 295 , The annular compartments 345 are at the upstream entrance 347 and the downstream exit 348 open to the fuel-air mixture. A radial blade 360 is in each case between the individual annular compartments 345 provided, with the radial blade extending from the central hub 285 to the inner burner tube 295 extends.

Every radial blade 360 arched from a rather flat slope at the upstream entrance 347 to a steep slope at the downstream exit 348 the annular section 345 , The shallow axial slope at the upstream inlet allows the swirling circumferential flow of the fuel-air mixture to be captured by the main swirl vanes 250 of the main radial swirler 140 , Approximately 30% of the fuel-air mixture from the annular swirl volume 255 of the main radial swirler 140 flow into the annular compartments 345 the Entdrallers 280 , The changing slope of the radial blades 360 deflects the circumferential flow into an axially directed flow, which is each individual annular compartment 360 excited. The deflected axial flow, as previously described, provides for the ventilation of the central return zone (ZRZ) as previously described.

In 3B and 8th defines an annular tip 380 the central hub 285 a flat surface I. An annular tip of the inner burner tube 295 defines a flat surface II. The flat surface I lies downstream of the flat surface II. The radial blades 360 the Entdrallers 280 Form at their downstream ends a sloped edge between the tip 380 the central hub 285 and the top 385 of the inner burner tube 300 which has a slope of about 30%.

A v-gutter 290 is at the downstream end of each radial blade 360 intended. The v-gutter 290 includes a v-shaped element 375 , its open end 376 is aligned downstream. A vertex 377 of the V-shaped element 376 is at the annular top 380 attached to the central hub and extends therethrough, along the downstream edge of the radial wall 360 and through the top 385 of the inner burner tube 300 ,

An outer flame holder 170 includes a generally cylindrical outer burner tube 175 expanding at an upstream end to form an annular seating surface for engagement with the main swirler. The cylindrical tube radially encloses the combustion chamber and extends beyond the central flame holder 160 out. The downstream end 190 of the outer burner tube 175 is reinforced. The bar 195 provides a seating surface for engagement with the conical dome 111 ( 2 ) of the combustion chamber. An annular seating surface 180 of the outer burner tube 175 widens at its upstream end radially outward. The seating surface 180 forms a roof over the main swirl bodies 250 of the main radial swirler 140 and thereby limits the exit path for the fuel-air mixture from the Hauptradialdrallkörper 140 on the downstream Strö mung routes 402 and 405 , The seating surface 180 For example, the main swirl vanes at the head of each airfoil may be secured to the airfoil by a plurality of bolts, one screw for each threaded hole. The annular space between the inner burner tube 295 of the central flame holder 160 and the outer burner tube 175 the outer flame holder 170 serves the stream 405 the remaining 70% of the fuel-air mixture from the main radial swirler 140 to the combustion chamber.

8th shows the central flame holder, the Gaspilotringraum and the central cartridge of an embodiment of the large Einzelradialdüse according to the invention.

An air flow path for the remaining 5% of incoming air from the intake plenum feeds the central cavity 260 the nozzle 140 through a variety of radial feedthroughs 275 (12 in this embodiment) from the peripheral edge 257 the back wall 240 ,

As a device for starting, for combustion chamber control, and to improve stability is a central Gaspilotdüse 150 in the conical flame holder volume at the smallest diameter upstream end. The gas pilot nozzle 150 is with a center cartridge 155 which may include an igniter / flame detector and a LPG pilot.

The approximately 5% of the air flow to the radial nozzle, through radial flow openings 275 in the peripheral surface 257 the back wall 240 of the main radial swirler 140 enter, are divided internally. About 80% of this air flows through an air supply annulus between the inner wall of the central cavity 265 the central hub and an outer surface 812 an annular housing 810 the gas pilot nozzle 150 forward to an annular axial spiral gas pilot premixer 855 , The remaining air flows through a plurality of radial feed openings 875 in the annular housing 810 in the center cartridge and is used for the liquid pilot atomization and cooling as well as the flushing of the center cartridge tip.

9A and 9B show the nozzle body of the gas pilot nozzle of an embodiment of the large single radial nozzle according to the invention.

The gas pilot nozzle 150 includes a body 805 with an annular housing 810 from the rear into the central cavity 203 the nozzle 140 through the end cover plate 205 can be used. The annular housing 810 includes at its rear end the rear flange 815 with a variety of screw holes 816 for mounting its front surface 817 to the seating surface 210 in the central cavity 203 the end cover 205 , The rear flange 815 is also with a middle opening 818 for inserting the center cartridge 155 provided and includes a raised surface 819 on the back surface 820 around the central cavity, with threaded holes 821 for screwing the center cartridge 155 to the rear flange 815 the gas pilot. The rear flange 815 is also with an implementation 230 provided for connection to a pilot gas fuel supply for the operation of the gas pilot.

The gas pilot nozzle body 805 extends through the central cavities 203 . 265 . 278 the nozzle 120 and in the cylindrical hub 370 of the central flame holder 160 , The annular housing 810 The gas pilot gradually tapers from the rear end to the front end. The annular housing 810 includes a lower housing 835 , a tapered housing 840 , a central housing 845 and a rejuvenating head 850 ,

An annular gas pilot airflow space 864 is also between the inner wall 368 the cylindrical hub 370 and the inner wall 296 of the carrying tower 295 with the outer surfaces 842 . 847 the tapered housing 840 and the central housing 845 Are defined. Air from the inner radial ends 277 the central radial access openings 275 in the back wall 240 enters the gas pilot airflow space 864 and flows axially forward to the axial swirl gas pilot premixer 855 ,

The penetration 230 for pilot gas fuel in the rear flange 815 supplies the inner pilot gas fuel cavities 862 in the annular housing 810 , The inner pilot gas fuel cavities 842 in the lower case 835 supply the annular pilot gas space 866 between the inner wall of the annular housing 810 and the outer surface 872 the central cartridge 155 with pilot gas fuel. The rejuvenating head 850 extends in close proximity to the cylindrical hub 370 and thereby forms a gas pilot burner ring space 825 between the outer surface 830 the tapered annular head 850 and the inner surface 368 the cylindrical hub. A variety of pilot gas fuel holes 860 extends radially through the annular housing at the upstream entrance between adjacent axial mixing vanes 857 and provides injection points for pilot gas fuel. The front part of the central housing 845 takes a variety of axial mixing blades 857 having a substantially blade blade shape on the outer surface 847 which serve to mix gas pilot fuel and air downstream in the air flow space 864 move, whereby the annular axially-twisted Gaspi lot premixer 855 arises.

The middle cartridge 155 includes the cylindrical body 405 standing on a rear flange 224 is mounted. The middle cartridge 155 is in the central cavity 203 of the gas pilot nozzle body 805 inserted and through the rear flange 224 on the raised rear surface 820 screwed. The rear flange 224 has an axial penetration for connections to an igniter and a flame detector 236 and on its peripheral surfaces a radial penetration 232 for pilot liquid fuel and a radial penetration 234 for a flow of air. The middle cartridge 155 Aligns with the central axis 200. the nozzle.

10 shows an axial head end portion of the center cartridge 155 for an embodiment of the nozzle according to the invention. The middle cartridge 155 is radial from a cartridge wall 872 and at the downstream end of a tip end 885 enclosed. The ignition device 875 extends axially from the center cartridge flange 224 to the end point 885 , The liquid fuel pilot 880 extends from the center cartridge flange 224 to the end point 885 , The air cavity 873 takes in air for use inside the center cartridge. Air for the center cartridge emerges from the radial feed ports 275 in the back wall 240 in and through the openings 277 in the room 864 between the pilot nozzle 150 and the inner surface 368 of the carrying tower 270 out. Part of the room 864 incoming air enters the center cartridge 155 through cartridge feed openings 870 a, fills the air cavity around the ignition device 875 and the liquid fuel pilot 880 and extends forward to a peak baffle 865 , The lace baffle 865 seals the top of the cavity and includes a plurality of tip openings 867 (18 openings in the present embodiment). Air is from the peak baffle 865 to an annular air duct 876 at the downstream end of the ignition device 875 directed to assist the ignition. Air from the peak baffle 865 is also the conical annulus 881 around a heat shield 882 on the liquid fuel pilot 880 fed. A variety of offset compressed air openings 883 are in the air atomizer housing 884 intended. The liquid pilot fuel is passed through a cylindrical cavity 890 in the body of the liquid fuel pilot 891 fed. A frustoconical annulus of a swirl chamber wall 892 at the top defines a swirl chamber 893 for the liquid fuel. An annular air gap 894 is for thermal insulation around the body 891 provided the liquid fuel pilot. Around the annular air gap 894 is an air support annulus 895 provided with the air assist feeder in the flange 224 the central cartridge 155 connected is. In the air support annulus 895 There is an air assist swirler 896 (The embodiment includes 8 swirl vanes 897 ). The swirl blades 897 cause a swirling movement of the swirl chamber 893 introduced support air.

11 shows an alternative embodiment of the central flame holder of the large Einzelradialdüse 900 , The flame holder 905 consists of a perforated cup 910 , The perforated cup 910 includes a variety of holes 920 around the central axis 915 , by the 30% (circa) of the air-fuel mixture coming from the ring region 950 flow, in part with that of the pilot nozzle 960 upcoming pilot air-fuel mixture 955 mixed and partly at the exit of the holes 920 burns. The holes 920 are with fillets 930 provided to minimize the corner separation. A ring band 940 is around the cup 910 provided around to direct the current in the cup. The lower convex end 945 the cup 920 is open and adapted to the pilot air-fuel mixture 955 from the gas pilot nozzle 960 take. Therefore, in this case, the heat release takes place in three stages. The first stage is the pilot zone. The second stage is the air-fuel mixture at the exit of the holes 920 burns, and the third stage is the stream, which is the perforated cup 920 bypasses.

In the foregoing, a large single radial nozzle for a gas turbine combustor has been described that provides substantial improvements in operation over multi-nozzle designs. First, nozzle-internal combustion staging through the design of the premixer of the nozzle, and in particular the conical, de-vorticated, V-shaped flame holders in conjunction with external controllable main gas and indoor main gas fuel injection paths, is a unique aspect of this design. This aspect allows the replacement of multiple nozzles (by combustion chamber) by a single, resulting in a considerable cost savings and part reduction. Secondly, a reduction in combustion dynamics / combustion vibrations is achieved in a novel way by the distribution of the fuel transport times and the heat release in the chamber. This unique feature could also allow the combustion of a wider range of fuels without having to modify or replace the hardware. Finally, the design of the combustor head end and the manner in which the nozzle is integrated into the combustor dome provide an annular dome diffuser which restores pressure while at the same time cooling the back of the fume tube dome, without the introduction a separate source of cooling air - for functionality and increased Simplicity.

Present is the nozzle according to the invention for the GE 9FB rated high performance industrial engine; she can, however enlarged or be scaled down to fit almost any annular combustor design to operate (e.g., 7H, 9H, 7FB, 7FA, 9FA, 6C, etc.). The construction could retrofitted to an existing package or as a new product Tobe offered.

While here only certain features of the invention are shown and described professionals will find many modifications and changes come to mind. It is therefore to be understood that the appended claims all such modifications and changes to cover the true spirit of the invention.

It is a lean premixed, radial multi-ring stage nozzle 120 provided in a dual-fuel tubular gas turbine combustor 100 create three independent combustion zones. The nozzle 120 includes a pilot zone Z1 passing through a gas pilot nozzle 150 and the center cartridge 155 is supplied with fuel; a flame holding zone Z2 supplied by an inner main gas fuel; a main flame zone Z3 supplied by an outside main gas fuel; a radial main spin body 120 for mixing a part of the nozzle to the nozzle 120 inflow air with the inner main gas fuel and the outer main gas fuel and a Endabdeckungseinheit with external means for the control of a supplied Innenhauptgasbrunstoffs and a supplied outer main gas fuel.

10

gas turbine

12

compressor

14

combustion chamber

16

turbine blade

18

Transition duct

20

spark plug

22

Durchzündrohre

24

combustion chamber housing

26

turbine housing

28

screw

30

end cover

32

Fuel nozzle assembly

34

flow sleeve

36

outer wall the transition channel

38

flame tube

39

pursuit

42

Liner cap assembly

44

holes

46

premix

47

front panel

48

floating bushing

49

rear wall

50

Fuel swirler

52

rear feeding

54

front exit section

66

radial fuel injectors

69

premixing

70

combustion chamber

100

Dual fuel pipe annular combustion chamber

105

combustion chamber housing

106

flow sleeve

110

flame tube

111

conical cathedral

112

extension part

113

outer burner tube

114

main combustion chamber

115

annulus

116

diffuser

117

inlet plenum

118

paneling

120

skinny Premixed radial multi-ring stage nozzle (large single radial nozzle)

130

end cover

135

rear surface

138

front

140

Main radial swirler

150

Gaspilotdüse

155

agent cartridge

160

centrally flame holder

170

outer flame holder

175

outer burner tube

178

downstream lying end of the burner tube

179

Support ledge

180

base section

183

screw

185

Outside the main gas supply

190

Inside the main gas supply

195

LPG supply

200

central axis

201

rear section

202

front section

203

centrally cavity

204

front surface

205

end cap plate

206

Combustor screw hole

207

outer peripheral surface

208

pilot hole

209

screw hole

210

Gas pilot nozzle seat

212

Gaspilotdüsenflansch

214

screw for rear Gaspilotdüsenflansch

215

Outside the main gas-carrying

220

Inside the main gas-carrying

223

agent cartridge

224

Mittelpatronenflansch

225

Mittelpatronenflansch

230

Gas pilot port

232

Liquid fuel pilot port

234

Air Support Connection

236

Igniter / flame detector port

240

rear wall

241

base surface

242

mounting surface

243

rear Liquid fuel supply penetration

244

Main liquid fuel passage

245

Liquid fuel injection point

246

Liquid fuel spill pass-end cover

247

Liquid fuel outlet bushing rear wall

248

atomizer

249

isolated lining

250

swirl blade

252

nozzle tip

255

annular swirl volume

257

circumferential edge the back wall

260

center hub

263

inner surface

265

centrally cavity

270

cylindrical carrier

273

outer support bar

274

inner Support ledge

275

radial air duct

277

exit

278

centrally cavity

280

Entdraller

285

center hub

290

v-gutters bundle

295

supporting tower

296

inner wall of the carrying tower

300

inner burner tube

310

Outside main gas passage

311

inner wall

312

outer wall

315

upper The End

317

inner wall

318

outer wall

319

upper The End

330

Inside main gas passage

345

annular department

347

entry the inner department

348

downstream lying outlet of the annular compartment

350

cylindrical support tower

355

Beam

360

radial shovel

365

wall of the inner burner tube

366

inner wall

368

inner wall the cylindrical one hub

370

cylindrical hub

371

recesses

372

screw holes

375

V-shaped element

376

Restricted The End

377

vertex

380

top of the annulus

381

first recess

382

second recess

383

third recess

385

top of the inner burner tube

390

inclined edge

400

airflow from the diffuser

401

airflow from the inlet plenum in the Hauptradialdrallkör by

402

electricity to the central flame holding zone

405

electricity to the main zone

605

Peripheral premix

610

airfoil

615

leading edge

620

trailing edge

625

axis

630

Sharpener angle

635

radius

640

Side surface with Injection point

642

Side surface without Injection point

645

lower area

650

top

655

Outer main gas fuel injection points

657

Outer main gas fuel injection holes

660

airflow

665

fuel cavity

670

threaded hole

680

Inside main gas injection bushings

685

opening

690

Inside main gas injection point

695

nozzle tip

805

body

810

annular housing

815

rear flange

816

screw holes

817

front seating surface

818

center hole

819

increased surface

820

rear surface

821

threaded holes

825

Gas pilot annulus

830

outer surface

835

lower casing

836

Outside surface of the lower housing

840

yourself tapered casing

842

Outside surface of the rejuvenating housing

845

average casing

847

outer axial surface

850

yourself tapered head

852

Outside surface of the rejuvenating head

855

Gas pilot premixer

857

mixing blades

860

Pilot gas opening

862

Inner Pilot gas fuel cavities

864

Gas pilot airspace

865

Top baffle plate

866

lace holes

870

Cartridge feed ports

872

Outer surface of the agent cartridge

873

cavity

875

detonator

880

Liquid fuel pilot

881

strangely annulus

882

heat shield

883

Offset air openings

884

Luftzerstäuberringgehäuse

885

end tip

890

cylindrical fuel cavity

891

Liquid fuel pilot body

892

Swirl chamber wall

893

swirl chamber

894

Air annulus gap

895

Air assist annulus

896

Air Support swirler

900

large single radial nozzle

905

centrally flame holder

910

perforated Cup

915

central axis

920

holes

930

fillets

940

ring band

945

wall of the inner burner tube

950

entry a 30% fuel-air mixture into the central flame holder

955

Pilot air-fuel mixture

960

pilot nozzle

Claims (10)

Lean premixed, radial multi-ring stage nozzle ( 120 ) for the creation of three independent combustion zones in a dual-fuel pipe-ring gas turbine combustor ( 100 ), the nozzle comprising: a pilot zone (Z1) passing through a center cartridge during liquid fuel operation ( 223 ) is supplied with fuel and during gas operation by a central gas pilot nozzle ( 150 ) is supplied with fuel; a central flame holding zone (Z2) supplied by an internal main gas fuel supply; a main flame zone (Z3) supplied by an outside main gas fuel supply; a main radial swirler ( 140 ) for the mixing of a part of the nozzle into the nozzle ( 120 ) with the inner main gas fuel supply and the outer main gas fuel supply, with a rear wall ( 240 ), which are axially connected to an end cover ( 130 ) is aligned, to which it is mechanically fixed; a variety of swirl vanes ( 250 ) spaced approximately equidistantly in a circular array about a central axis of the nozzle; a premix volume ( 205 ) in a circumferential space between the individual swirl blades ( 250 ); a central hub ( 260 ), which has a central cavity ( 278 ), and an annular swirl volume ( 255 ) between the plurality of swirl vanes ( 250 ) and the central hub ( 260 ) and means for controlling the ratio of an indoor main gas fuel supply ( 220 ) and an external main gas fuel supply ( 215 ) and an end cover ( 130 ). Jet ( 120 ) according to claim 1, wherein the main radial swirl body ( 140 ) comprises: a cylindrical back wall ( 240 ); a central hub ( 260 ) axially downstream from a downstream surface ( 242 ) of the back wall ( 240 ), wherein the central hub ( 260 ) has a smooth conical surface ( 270 ) which is frusto-conical at a downstream end; a cavity ( 665 ) containing an outer main gas fuel supply from the end cover ( 205 ) with the plurality of swirl vanes ( 250 ) connects; a variety of injectors ( 690 ) located on the downstream surface ( 242 ) of the back wall ( 240 ) is mounted; a cavity ( 680 ) containing an internal main gas fuel supply from the end cover ( 205 ) with the plurality of injectors ( 690 ) connects; a variety of liquid fuel atomizers ( 248 ) located on the downstream surface ( 242 ) of the back wall ( 240 ) are attached; a cavity ( 247 ) containing a liquid fuel feed from the end cap ( 205 ) connects to the plurality of liquid fuel atomizers, and a central cavity ( 278 ) along the central axis ( 200. ) of the nozzle ( 120 ) and a plurality of radially aligned cavities ( 250 ) having an outer peripheral surface ( 275 ) of the rear wall with the central cavity ( 278 ) connects to the middle cartridge ( 223 ) and the gas pilot nozzle ( 150 ) To supply air. Jet ( 120 ) according to claim 2, wherein each of the plurality of swirl vanes ( 250 ) comprises: an airfoil ( 610 ) located axially downstream from a downstream surface ( 242 ) of the back wall ( 240 ) towards a combustion end of the nozzle ( 120 ), wherein a center line ( 225 ) of the airfoil ( 610 ) a predetermined angle ( 630 ) with a radius ( 635 ) from the central axis ( 200. ) of the nozzle ( 120 ) and thereby the circumferential premix space ( 605 ) for an air flow from outside the main spin body ( 250 ) to an annular swirl volume ( 255 ) between the main swirl blades ( 250 ) and the central hub ( 270 ) Are defined; an internal cavity ( 665 ) in each airfoil ( 610 ) for the outer main gas fuel supply in the rear wall; a plurality of gas fuel injection holes ( 657 ) for the distribution of the outer main gas fuel supply from the inner cavity ( 665 ) to the premix space ( 605 ). Jet ( 120 ) according to claim 1, wherein the end cover comprises: a cylindrical plate ( 205 ) with an outer radial mounting surface ( 207 ) for mechanical mounting to a combustion chamber ( 100 ) and an inner radial mounting surface ( 204 ) for mounting on the rear wall ( 240 ); a cavity containing an outer main gas fuel supply ( 185 ) with the rear wall ( 240 ) connects; a cavity containing an internal main gas fuel supply ( 190 ) with the rear wall ( 240 ) connects; a variety of cavities ( 246 ) containing a liquid fuel feed ( 195 ) with the rear wall ( 240 ), and a central cavity ( 203 ) with a mounting flange ( 210 ) for receiving and mounting a gas pilot nozzle ( 150 ). Jet ( 120 ) according to claim 1, wherein the central flame holding zone (Z2) comprises: a central hub ( 285 ); an inner burner tube wall ( 365 ); a deswister ( 280 ) for the conversion of a circumferentially moving flow of a fuel-air mixture in the annular swirl volume ( 255 ) of the main radial swirl body ( 250 ) and the deflection of the air flow in an axial downstream direction, with a plurality of segmented radial compartments ( 345 ), wherein each section is formed as an annular segment, which at an outer radius through the inner burner tube wall ( 365 ) and at an inner radius through an outer wall of the central hub ( 385 ), with adjacent departments ( 345 ) by radial blades ( 360 ) are separated with circumferentially inclined radial walls, wherein the inclination of an upstream inlet ( 347 ) in the compartment ( 345 ) to a downstream outlet ( 348 ) from the compartment ( 345 ) increases progressively to a portion of the fuel-air mixture in the annular swirl volume ( 255 ) and a V-shaped flame bundle holder ( 290 ) with a plurality of radially aligned arms ( 360 ), which in the circumferential direction around the wall of the inner burner tube ( 365 ) are approximately equidistant, with the arms ( 360 ) at a downstream end of the central hub ( 285 ) and from there to a downstream axial end of the inner burner tube ( 300 ), with an attachment point on the wall ( 365 ) of the inner burner tube is located downstream of an attachment point on a hub extension and thereby a predetermined radial-axial angle ( 630 ) of the radially aligned arms ( 360 ) and a convex depression in the radially aligned arms (FIG. 360 ), and a vertex pointing in the upward direction ( 377 ) of the convex depression ( 375 ). Nozzle according to claim 5, wherein the central hub ( 285 ) comprises: a cylindrical tube ( 295 ) with a central cavity ( 278 ), which has an irregular shape of an inner surface ( 296 ) of the cylindrical tube ( 296 ) to the central gas pilot nozzle ( 150 ), arranged at an upstream end with the central hub ( 260 ) of the main radial swirl body ( 140 ) and also a hub extension ( 380 ) at a downstream axial end of the cylindrical tube ( 295 ), whereby the hub extension ( 380 ) all around at regular intervals through v-shaped grooves ( 290 ) is interrupted. Jet ( 120 ) according to claim 1, wherein the central gas pilot nozzle ( 150 ) comprises: a generally cylindrical body ( 805 ) with a central cavity and a radially widened screw flange ( 815 ) at an upstream end, wherein the nozzle body ( 805 ) is arranged in a central cavity ( 203 . 270 . 278 ) of the end cover ( 205 ), the back wall ( 240 ) and a central hub ( 285 ) of the flame retainer zone; a plurality of radial air inlets ( 870 ), which are axially on the body ( 805 ) to direct airflow from the rear wall (FIG. 240 ); a central cartridge ( 155 ) in the central cavity ( 203 . 270 . 278 ); an annulus ( 864 ), which is adapted to supply pilot gas fuel from a gas pilot nozzle to the gas pilot ( 150 ) at the downstream end of the central cartridge ( 155 ); a large number of pilot mixing blades ( 857 ), which are designed for the mixing of air with pilot gas fuel; a plurality of radially extending holes ( 860 ) through a wall ( 872 ) of the central cartridge ( 155 ), upstream between adjacent pilot mixing blades ( 857 ), and an annulus ( 825 ) located downstream of the pilot mixing blades ( 857 ) and adapted to supply a pilot gas-air mixture to the pilot zone (Z1). The nozzle of claim 7, wherein the center cartridge comprises: a liquid fuel pilot ( 880 ); an air assist feeder ( 873 ) for the liquid fuel pilot ( 880 ) and an ignition device ( 875 ). Jet ( 120 ) according to claim 1, wherein the main flame zone (Z3) further comprises: a cylindrical wall ( 365 ) of the inner burner tube, which on a central axis ( 200. ) of the nozzle ( 120 ) is centered; a cylindrical outer burner tube ( 175 ) located on the central axis ( 200. ) of the nozzle ( 120 ) is centered, wherein the outer burner tube ( 175 ) downstream of the main radial swirl body ( 140 ) protrudes axially and has a larger diameter than the wall ( 365 ) of the inner burner tube; a base section ( 180 ) of the outer burner tube ( 175 ) extending radially outwardly at its upstream end, a peripheral surface and a roof over the plurality of main swirl vanes (US Pat. 250 ) and directs the fuel and air into the annular mixing zone. Dual-fuel annular tube combustion chamber ( 100 ) for a gas turbine engine, comprising: a lean premixed radial multi-ring stage nozzle ( 120 ) with an inner burner tube ( 300 ), an outer burner tube ( 113 ) and a main radial swirl body ( 240 ) on an end cover ( 130 ) of a combustion chamber housing ( 105 ) is mounted; a main combustion zone (Z1) located downstream of the outer burner tube (Z1) 113 ) of the nozzle is located; compressed air from a compressor; an air intake plenum ( 117 ), which is the nozzle ( 120 ) radially encloses and through a housing wall ( 105 ) is limited radially of the combustion chamber; a diffuser ( 116 ) for the compressed air, the diffuser ( 116 ) receives the compressed air on a reverse flow path from the compressor and the compressed air at a restored pressure to the inlet plenum ( 117 ), whereby the diffuser ( 116 ) comprises an inner wall which is connected to the back of a dome ( 111 ) on the main combustion zone, whereby cooling of the dome ( 111 ) from the back through which the diffuser ( 116 ) passing compressed air, and one on the Hauptradialdrallkörper ( 240 ) mounted cladding ( 118 ), which forms part of the outer burner tube ( 113 ) and for smoothing the air flow from the diffuser ( 116 ) to the air intake plenum ( 117 ) is provided.