CN104566468A - Turbomachine combustor having an externally fueled late lean injection (LLI) system - Google Patents
Turbomachine combustor having an externally fueled late lean injection (LLI) system Download PDFInfo
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- CN104566468A CN104566468A CN201410556421.2A CN201410556421A CN104566468A CN 104566468 A CN104566468 A CN 104566468A CN 201410556421 A CN201410556421 A CN 201410556421A CN 104566468 A CN104566468 A CN 104566468A
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- lli
- fluid
- incendivity
- fluidly connected
- delivery catheter
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/346—Feeding into different combustion zones for staged combustion
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- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A turbomachine (3) combustor assembly (20) includes a combustor (22) including a combustor body (52) extending from a head end (54) to a second end (56) through a combustion zone (58). At least one injector (60) is configured and disposed to introduce a first combustible fluid into the combustion zone (58) at the head end (54) of the combustor body (52). At least one late lean injector (LLI) (90-92) is configured and disposed to introduce a second combustible fluid downstream of the first combustible fluid. An external fluid delivery system (40) is fluidically connected to the at least one LLI (90-92). The external fluid delivery system (40) includes at least one combustible fluid delivery conduit (110) that extends from a first end (112) fluidically connected to the LLI (90-92) to a second end (113) external to the turbomachine (3) combustor assembly (20). The second end (113) is configured and disposed to deliver the second combustible mixture to the LLI (90-92).
Description
Technical field
Theme disclosed herein relates to turbines, and more specifically, relates to the turbomachine combustor of late lean injection (late lean injection) (LLI) system with outside supply fuel.
Background technique
Turbo machine comprises compressor section and burner assembly, and compressor section is attached to turbine portion by common compressor/turbine shaft.Intake air stream towards compressor section through air inlet.In compressor section, intake air stream is compressed towards burner assembly by multiple order levels.In burner assembly, pressurized air stream and fuel mix are to form combustible mixture, and it imports in the firing chamber of burner.Combustible mixture burns to form hot gas in a combustion chamber.Hot gas is expanded by multiple turbine stage, thus acts on acting on the turbine rotor blade that is arranged on impeller, and this merit output example is as being generator, pump energy supply or to vehicle energy supply.Waste gas from turbine portion usually passes to heat recovery steam generator, and it produces the vapor stream passing to steamturbine part.
In general, pressurized air and fuel are introduced via the cephalic par of one or more fuel nozzle by burner.Combustible mixture burns in the zone of combustion of burner, and flow to turbine portion by transition piece.In some cases, extra incendivity fluid is introduced in burner in the downstream of zone of combustion.In other situations, extra incendivity fluid can be introduced in transition piece.When burnt, extra incendivity fluid can consume the unburnt ingredient of combustible mixture to improve the discharge from turbo machine.
Summary of the invention
According to an aspect of exemplary embodiment, turbomachine combustor assembly comprises burner, and burner comprises burner body, and it extends to the second end from cephalic par by zone of combustion.At least one ejector arrangements and being arranged to the first incendivity fluid in the introducing zone of combustion, cephalic par place of burner body.At least one late lean injection device (LLI), it constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid.External fluid transporting system is fluidly connected at least one LLI.External fluid transporting system comprises at least one incendivity fluid delivery catheter, and it extends to the second end of turbomachine combustor component external from the first end being fluidly connected to LLI.The second end constructs and is arranged to the second combustible mixture to be transported to LLI.
According to the another aspect of exemplary embodiment, turbine system comprises compressor section, is operatively coupled to the turbine portion of compressor section and burner assembly, and it is fluidly connected to compressor section and turbine portion.Burner assembly comprises burner, and it has the burner body being extended to the second end from cephalic par by zone of combustion.At least one ejector arrangements and being arranged to the first incendivity fluid in the introducing zone of combustion, cephalic par place of burner body.At least one late lean injection device (LLI) constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid.External fluid transporting system is fluidly connected at least one LLI.External fluid transporting system comprises at least one incendivity fluid delivery catheter, and it extends to the second end of turbomachine combustor component external from the first end being fluidly connected to LLI.The second end constructs and is arranged to the second combustible mixture to be transported to LLI.
According to the another aspect of exemplary embodiment, the mechanical load that turbine system comprises compressor section, is operatively coupled to the turbine portion of compressor section, is connected to the one in compressor section and turbine portion with driving, and be fluidly connected to the gas handling system of compressor section.Gas handling system constructs and is arranged to regulate the fluid of the entrance entering compressor section.Burner assembly is fluidly connected to compressor section and turbine portion.Burner assembly comprises burner, and it has the burner body being extended to the second end from cephalic par by zone of combustion.At least one ejector arrangements and being arranged to the first incendivity fluid in the introducing zone of combustion, cephalic par place of burner body.At least one late lean injection device (LLI) constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid.External fluid transporting system is fluidly connected at least one LLI.External fluid transporting system comprises at least one incendivity fluid delivery catheter, and it extends to the second end of turbomachine combustor component external from the first end being fluidly connected to LLI.The second end constructs and is arranged to the second combustible mixture to be transported to LLI.
A kind of turbo machine (3) burner assembly (20), comprising:
Burner (22), it comprises the burner body (52) being extended to the second end (56) from cephalic par (54) by zone of combustion (58);
At least one sparger (60), it constructs and is arranged to the first incendivity fluid in cephalic par (54) place introducing zone of combustion (58) of burner body (52);
At least one late lean injection device (LLI) (90-92), it constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid; And
External fluid transporting system (40), it is fluidly connected at least one LLI (90-92), external fluid transporting system (40) comprises at least one incendivity fluid delivery catheter (110), it extends to the outside the second end (113) of turbo machine (3) burner assembly (20) from the first end (112) being fluidly connected to LLI (90-92), and the second end (113) constructs and is arranged to the second incendivity fluid to be transported to LLI (90-92).
Preferably, also comprise: fuel feed line (120), it extends to the second end part (124) from the first end part (123) of the second end (113) being fluidly connected at least one incendivity fluid delivery catheter (110) by intermediate portion (125), and the second end part (124) is fluidly connected to the outside supply department of incendivity fluid.
Preferably, also comprise: valve (130), it is configured in the intermediate portion (125) of fuel feed line (120).
Preferably, also comprise: incombustible fluid feed line (140), it extends to the second end part (144) from the first end part (143) of the second end (113) being fluidly connected at least one incendivity fluid delivery catheter (110) by intermediate portion (145), and the second end part (144) is fluidly connected to the supply department of incombustible fluid.
Preferably, also comprise: valve (150), it is configured in the intermediate portion (145) of incombustible fluid feed line (140).
Preferably, the second end part (144) of incombustible fluid feed line (140) is fluidly connected to compressor and discharges shell (63).
Preferably, at least one incendivity fluid delivery catheter (110) comprise be fluidly connected to a LLI (90) the first incendivity fluid delivery catheter (160), be fluidly connected to the second incendivity fluid delivery catheter (163) of the 2nd LLI (91) and be fluidly connected to the 3rd incendivity fluid delivery catheter (165) of the 3rd LLI (92), first, second and the 3rd incendivity fluid delivery catheter (160,163,165) each in is fluidly connected to mating part (168).
A kind of turbo machine (3), comprising:
Compressor section (4);
Turbine portion (8), it is operatively connected to compressor section (4); And
Burner assembly (20), it is fluidly connected to compressor section (4) and turbine portion (8), and burner assembly (20) comprising:
Burner (22), it comprises the burner body (52) being extended to the second end (56) from cephalic par (54) by zone of combustion (58);
At least one sparger (60), it constructs and is arranged to the first incendivity fluid in cephalic par (54) place introducing zone of combustion (58) of burner body (52);
At least one late lean injection device (LLI) (90-92), it constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid; And
External fluid transporting system (40), it is fluidly connected at least one LLI (90-92), external fluid transporting system (40) comprises at least one incendivity fluid delivery catheter (110), it extends to the outside the second end (113) of turbo machine (3) burner assembly (20) from the first end (112) being fluidly connected to LLI (90-92), and the second end (113) constructs and is arranged to the second incendivity fluid to be transported to LLI (90-92).
Preferably, also comprise: fuel feed line (120), it extends to the second end part (124) from the first end part (123) of the second end (113) being fluidly connected at least one incendivity fluid delivery catheter (110) by intermediate portion (125), and the second end part (124) is fluidly connected to the outside supply department of incendivity fluid.
Preferably, also comprise: valve (130), it is configured in the intermediate portion (125) of fuel feed line (120).
Preferably, also comprise: incombustible fluid feed line (140), it extends to the second end part (144) from the first end part (143) of the second end (113) being fluidly connected at least one incendivity fluid delivery catheter (110) by intermediate portion (145), and the second end part (144) is fluidly connected to the supply department of incombustible fluid.
Preferably, also comprise: valve (150), it is configured in the intermediate portion (145) of incombustible fluid feed line (140).
Preferably, the second end part (144) of incombustible fluid feed line (140) is fluidly connected to compressor and discharges shell (63).
Preferably, at least one incendivity fluid delivery catheter (110) comprise be fluidly connected to a LLI (90) the first incendivity fluid delivery catheter (160), be fluidly connected to the second incendivity fluid delivery catheter (163) of the 2nd LLI (91) and be fluidly connected to the 3rd incendivity fluid delivery catheter (165) of the 3rd LLI (92), first, second and the 3rd incendivity fluid delivery catheter (160,163,165) each in is fluidly connected to mating part (168).
A kind of turbine system (2), comprising:
Compressor section (4);
Turbine portion (8), it is operatively coupled to compressor section (4);
Mechanical load (30), it is connected to the one in compressor section (4) and turbine portion (8) with driving;
Gas handling system (24), it is fluidly connected to compressor section (4), and gas handling system (24) constructs and is arranged to the fluid that adjustment enters the entrance (26) of compressor section (4); And
Burner assembly (20), it is fluidly connected to compressor section (4) and turbine portion (8), and burner assembly (20) comprising:
Burner (22), it comprises the burner body (52) being extended to the second end (56) from cephalic par (54) by zone of combustion (58);
At least one sparger (60), it constructs and is arranged to the first incendivity fluid in cephalic par (54) place introducing zone of combustion (58) of burner body (52);
At least one late lean injection device (LLI) (90-92), it constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid; And
External fluid transporting system (40), it is fluidly connected at least one LLI (90-92), external fluid transporting system (40) comprises at least one incendivity fluid delivery catheter (110), it extends to the outside the second end (113) of turbo machine (3) burner assembly (20) from the first end (112) being fluidly connected to LLI (90-92), and the second end (113) constructs and is arranged to the second incendivity fluid to be transported to LLI (90-92).
A kind of turbomachine combustor assembly, comprising:
Burner, it comprises the burner body being extended to the second end from cephalic par by zone of combustion;
At least one sparger, it constructs and is arranged to the first incendivity fluid in the introducing zone of combustion, cephalic par place of burner body;
At least one late lean injection device (LLI), it constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid; And
External fluid transporting system, it is fluidly connected at least one LLI, external fluid transporting system comprises at least one incendivity fluid delivery catheter, it extends to the second end of turbomachine combustor component external from the first end being fluidly connected to LLI, and the second end constructs and is arranged to the second incendivity fluid to be transported to LLI.
Preferably, also comprise: fuel feed line, it extends to the second end part from the first end part of the second end being fluidly connected at least one incendivity fluid delivery catheter by intermediate portion, is connected to the outside supply department of incendivity fluid the second end segment fluid flow.
Preferably, also comprise: valve, it is configured in the intermediate portion of fuel feed line.
Preferably, also comprise: incombustible fluid feed line, it extends to the second end part from the first end part of the second end being fluidly connected at least one incendivity fluid delivery catheter by intermediate portion, is connected to the supply department of incombustible fluid the second end segment fluid flow.
Preferably, also comprise: valve, it is configured in the intermediate portion of incombustible fluid feed line.
Preferably, incombustible fluid feed line the second end segment fluid flow be connected to compressor discharge shell.
Preferably, at least one incendivity fluid delivery catheter comprise be fluidly connected to a LLI the first incendivity fluid delivery catheter, be fluidly connected to the second incendivity fluid delivery catheter of the 2nd LLI and be fluidly connected to the 3rd incendivity fluid delivery catheter of the 3rd LLI, each in first, second and the 3rd incendivity fluid delivery catheter is fluidly connected to mating part.
A kind of turbo machine, comprising:
Compressor section;
Turbine portion, it is operatively connected to compressor section; And
Burner assembly, it is fluidly connected to compressor section and turbine portion, and burner assembly comprises:
Burner, it comprises the burner body being extended to the second end from cephalic par by zone of combustion;
At least one sparger, it constructs and is arranged to the first incendivity fluid in the introducing zone of combustion, cephalic par place of burner body;
At least one late lean injection device (LLI), it constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid; And
External fluid transporting system, it is fluidly connected at least one LLI, external fluid transporting system comprises at least one incendivity fluid delivery catheter, it extends to the second end of turbomachine combustor component external from the first end being fluidly connected to LLI, and the second end constructs and is arranged to the second incendivity fluid to be transported to LLI.
Preferably, also comprise: fuel feed line, it extends to the second end part from the first end part of the second end being fluidly connected at least one incendivity fluid delivery catheter by intermediate portion, is connected to the outside supply department of incendivity fluid the second end segment fluid flow.
Preferably, also comprise: valve, it is configured in the intermediate portion of fuel feed line.
Preferably, also comprise: incombustible fluid feed line, it extends to the second end part from the first end part of the second end being fluidly connected at least one incendivity fluid delivery catheter by intermediate portion, is connected to the supply department of incombustible fluid the second end segment fluid flow.
Preferably, also comprise: valve, it is configured in the intermediate portion of incombustible fluid feed line.
Preferably, incombustible fluid feed line the second end segment fluid flow be connected to compressor discharge shell.
Preferably, at least one incendivity fluid delivery catheter comprise be fluidly connected to a LLI the first incendivity fluid delivery catheter, be fluidly connected to the second incendivity fluid delivery catheter of the 2nd LLI and be fluidly connected to the 3rd incendivity fluid delivery catheter of the 3rd LLI, each in first, second and the 3rd incendivity fluid delivery catheter is fluidly connected to mating part.
A kind of turbine system, comprising:
Compressor section;
Turbine portion, it is operatively coupled to compressor section;
Mechanical load, it is connected to the one in compressor section and turbine portion with driving;
Gas handling system, it is fluidly connected to compressor section, and gas handling system constructs and is arranged to regulate the fluid of the entrance entering compressor section; And
Burner assembly, it is fluidly connected to compressor section and turbine portion, and burner assembly comprises:
Burner, it comprises the burner body being extended to the second end from cephalic par by zone of combustion;
At least one sparger, it constructs and is arranged to the first incendivity fluid in the introducing zone of combustion, cephalic par place of burner body;
At least one late lean injection device (LLI), it constructs and is arranged to introduce the second incendivity fluid in the downstream of the first incendivity fluid; And
External fluid transporting system, it is fluidly connected at least one LLI, external fluid transporting system comprises at least one incendivity fluid delivery catheter, it extends to the second end of turbomachine combustor component external from the first end being fluidly connected to LLI, and the second end constructs and is arranged to the second incendivity fluid to be transported to LLI.
Preferably, also comprise: fuel feed line, it extends to the second end part from the first end part of the second end being fluidly connected at least one incendivity fluid delivery catheter by intermediate portion, is connected to the outside supply department of incendivity fluid the second end segment fluid flow.
Preferably, also comprise: valve, it is configured in the intermediate portion of fuel feed line.
Preferably, also comprise: incombustible fluid feed line, it extends to the second end part from the first end part of the second end being fluidly connected at least one incendivity fluid delivery catheter by intermediate portion, is connected to the supply department of incombustible fluid the second end segment fluid flow.
Preferably, also comprise: valve, it is configured in the intermediate portion of incombustible fluid feed line.
Preferably, at least one incendivity fluid delivery catheter comprise be fluidly connected to a LLI the first incendivity fluid delivery catheter, be fluidly connected to the second incendivity fluid delivery catheter of the 2nd LLI and be fluidly connected to the 3rd incendivity fluid delivery catheter of the 3rd LLI, each in first, second and the 3rd incendivity fluid delivery catheter is fluidly connected to mating part.
These and other advantages and feature become more apparent by from following description by reference to the accompanying drawings.
Accompanying drawing explanation
Be considered as of the present invention theme to point out especially in claims of the summary as specification and claimed clearly.Foregoing and other feature of the present invention and advantage are apparent from following detailed description by reference to the accompanying drawings, in the accompanying drawings:
Fig. 1 is according to exemplary embodiment, comprises the schematic diagram of the turbo machine of turbomachine combustor, and turbomachine combustor has late lean injection (LLI) system of outside supply fuel;
Fig. 2 is the diagrammatic side view of the turbomachine combustor of Fig. 1; And
Fig. 3 is an aspect according to exemplary embodiment, has the axial end portion view of the turbomachine combustor of late lean injection (LLI) system of outside supply fuel.
Describe the mode by reference to the example of accompanying drawing in detail, explain embodiments of the invention, together with its advantage and feature.
List of parts
2 turbine systems
3 turbo machines
4 compressor section
6 compressor cases
8 turbine portion
10 turbine case
12 housings
16 common compressor/turbine shafts
20 burner assemblies
22 burners
24 gas handling systems
26 entrances
30 mechanical loads
40 external fluid transporting systems
52 burner bodies
54 cephalic pars
56 the second ends
58 zone of combustion
More than 60 sparger
62 fuel delivery systems
63 discharge shell
65 transition pieces
68 first end parts
70 the second end parts
72 intermediate portions
90 first late lean injection devices (LLI)
91 the 2nd LLI
92 the 3rd LLI
93 second zone of combustion
96 incendivity fluid inputs
97 incendivity fluid inputs
98 incendivity fluid inputs
110 incendivity fluid delivery catheter
112 first ends
113 the second ends
120 fuel feed lines
123 first end parts
124 the second end parts
125 intermediate portions
126 fuel supplies
130 valves
140 incombustible fluid feed lines
143 first end parts
144 the second end parts
145 intermediate portions
148 compressors extract
150 valves
160 incendivity fluid delivery catheter
163 second incendivity fluid delivery catheter
165 the 3rd incendivity fluid delivery catheter
168 mating part.
Embodiment
Turbine system according to exemplary embodiment illustrates with 2 in FIG.Turbine system 2 comprises turbo machine 3, and it comprises the compressor section 4 with compressor case 6 and the turbine portion 8 with turbine case 10.Compressor case 6 and turbine case 10 combine to form housing 12 (Fig. 2).Compressor section 4 is operatively coupled to turbine portion 8 by common compressor/turbine shaft 16.Turbo machine 3 also comprises burner assembly 20, and it has the one or more burners 22 fluidly connecting compressor section 4 and turbine portion 8.Gas handling system 24 is fluidly connected to the entrance 26 of compressor section 4.Turbo machine 3 is connected to mechanical load 30 with being also depicted as driving.Mechanical load 30 can take various ways, comprises the mechanical drive system of pumping system, power generating system and other types.Turbo machine 3 also comprises the external fluid transporting system 40 being fluidly connected to burner 22, as hereinafter will described in detail more comprehensively.
In the illustrated exemplary embodiment, burner 22 comprises burner body 52, and it extends to the second end 56 from cephalic par 54 by zone of combustion 58.Multiple sparger 60 is configured in cephalic par 54 place.Sparger 60 receives fuel by fuel delivery system 62, and discharges shell 63 admission of air from the compressor being formed in housing 12 inside.Fuel and air mixing are to form combustible mixture, and it burns in zone of combustion 58, thus forms hot gas.Hot gas passes through transition piece 65 from burner 22, and is expanded by turbine portion 8.Transition piece 65 extends to the second end part 70 from first end part 68 by intermediate portion 72.First end part 68 is mechanically coupled to the second end 56 of burner 22, and the second end part 70 is fluidly connected to turbine portion 8.
Further according to shown exemplary embodiment, burner 22 comprises the first late lean injection device (LLI) the 90, the 2nd LLI 91 (Fig. 3) and the 3rd LLI 92 (Fig. 3) that are installed to burner body 52.Certainly, quantity and the variable position of LLI is to be understood that.LLI 90-92 extends through burner body 54 at the second zone of combustion 93 place.Second zone of combustion 93 is configured in the downstream of zone of combustion 58.Each LLI 90-92 comprises corresponding incendivity fluid input 96-98, and it receives incendivity fluid by external fluid transporting system 40.Second combustible mixture is introduced in burner 22 by LLI 90-92, and it burns in the second zone of combustion 93.In full load operation period, LLI 90-92 reduces the time spent by the products of combustion at final burner outlet temperature, reduces NOx.In part load operation, the fuel leading to LLI 90-92 roughly can be reduced or is closed completely.In this condition, at cephalic par 54, place provides additional fuel, is oxidized CO with poppet end region temperature.By this way, turbo machine maintains discharge and closes rule during full load and part load operation.
Further according to exemplary embodiment, external fluid transporting system 40 comprises incendivity fluid delivery catheter 110, and it extends to the second end 113 of burner 22 outside from the first end 112 being fluidly connected to incendivity fluid input 96.Fuel feed line 120 is fluidly connected to incendivity fluid delivery catheter 110.More particularly, fuel feed line 120 extends to the second end part 124 from the first end part 123 of the second end 113 being fluidly connected to incendivity fluid delivery catheter 110 by intermediate portion 125.The second end part 124 is fluidly connected to fuel supplies 126.Fuel supplies 126 provides fuel source, and it can comprise incendivity fluid, combustible gas, thinner etc.Valve 130 configures along intermediate portion 125.Valve 130 controls incendivity fluid from fuel supplies 126 to the path of one or more LLI 90-92.
Further according to exemplary embodiment, external fluid transporting system 40 comprises incombustible fluid feed line 140.Incombustible fluid feed line 140 extends to the second end part 144 from first end part 143 by intermediate portion 145.First end part 143 is fluidly connected to the second end 113 of incendivity fluid delivery catheter 110.The second end part 144 of incombustible fluid feed line 140 is fluidly connected to the compressor arranged at housing 12 and discharges shell 63.Shell 63 discharged by compressor provides incombustible fluid to the supply of LLI 90-92.About this point, should be appreciated that incombustible fluid serves as the oxygenant to fuel, and air, oxygen, thinner etc. can be comprised.In addition, valve 150 configures along the intermediate portion 145 of incombustible fluid feed line 140.
Utilize this configuration, fuel and air can in burner 22 external mix, and can forward to LLI 90-92 what introduce burner body 52.By at burner 22 external mix fuel and air, the pressure in incendivity fluid delivery catheter 110 is less than the compressor of discharging shell 63 place at compressor and discharges air pressure.Therefore, if leaked, then compressor discharge shell 63 will be isolated with fuel.That is, fuel will not be passed in housing 12 by compressor discharge shell 63.In addition, the fuel/air mixture through incendivity fluid delivery catheter 110 will have pressure drop, and this pressure drop roughly meets the overall presure drop in burner body 52.Therefore, the flame made at LLI 90-92 place keeps being reduced by the output speed of fuel/air mixture.And, as shown in FIG. 3, external fluid transporting system 40 can comprise the incendivity fluid delivery catheter 160 and the second incendivity fluid delivery catheter 163 and the 3rd incendivity fluid delivery catheter 165 that are fluidly connected to incendivity fluid delivery catheter 110, and it makes LLI 90-92 interconnect by mating part 168.And, should be appreciated that each LLI can comprise special incombustible and incendivity fluid supply.
Although the present invention only describes in detail in conjunction with the embodiment of limited quantity, should easy understand, the present invention is not limited to described disclosed embodiment.But but the present invention can revise to merge and not describe above the modification of any amount corresponding to the spirit and scope of the present invention, change, to substitute or equivalent arrangements.In addition, although described multiple embodiment of the present invention, some that aspect of the present invention can only comprise in described embodiment have been should be appreciated that.Therefore, the present invention is not considered as being limited by aforementioned description, but is only limited by the scope of appended claims.
Claims (10)
1. a turbo machine (3) burner assembly (20), comprising:
Burner (22), it comprises the burner body (52) being extended to the second end (56) from cephalic par (54) by zone of combustion (58);
At least one sparger (60), it constructs and is arranged to the first incendivity fluid to introduce in described zone of combustion (58) at described cephalic par (54) place of described burner body (52);
At least one late lean injection device (LLI) (90-92), it constructs and is arranged to introduce the second incendivity fluid in the downstream of described first incendivity fluid; And
External fluid transporting system (40), it is fluidly connected to described at least one LLI (90-92), described external fluid transporting system (40) comprises at least one incendivity fluid delivery catheter (110), it extends to the outside the second end (113) of described turbo machine (3) burner assembly (20) from the first end (112) being fluidly connected to described LLI (90-92), and described the second end (113) constructs and is arranged to described second incendivity fluid to be transported to described LLI (90-92).
2. turbo machine according to claim 1 (3) burner assembly (20), it is characterized in that, also comprise: fuel feed line (120), it extends to the second end part (124) from the first end part (123) of the described the second end (113) being fluidly connected at least one incendivity fluid delivery catheter (110) described by intermediate portion (125), and described the second end part (124) is fluidly connected to the outside supply department of incendivity fluid.
3. turbo machine according to claim 2 (3) burner assembly (20), it is characterized in that, also comprise: valve (130), it is configured in the described intermediate portion (125) of described fuel feed line (120).
4. turbo machine according to claim 2 (3) burner assembly (20), it is characterized in that, also comprise: incombustible fluid feed line (140), it extends to the second end part (144) from the first end part (143) of the described the second end (113) being fluidly connected at least one incendivity fluid delivery catheter (110) described by intermediate portion (145), and described the second end part (144) is fluidly connected to the supply department of incombustible fluid.
5. turbo machine according to claim 4 (3) burner assembly (20), it is characterized in that, also comprise: valve (150), it is configured in the described intermediate portion (145) of described incombustible fluid feed line (140).
6. turbo machine according to claim 4 (3) burner assembly (20), it is characterized in that, the described the second end part (144) of described incombustible fluid feed line (140) is fluidly connected to compressor and discharges shell (63).
7. turbo machine according to claim 1 (3) burner assembly (20), it is characterized in that, at least one incendivity fluid delivery catheter (110) described comprises the first incendivity fluid delivery catheter (160) being fluidly connected to a LLI (90), be fluidly connected to the second incendivity fluid delivery catheter (163) of the 2nd LLI (91) and be fluidly connected to the 3rd incendivity fluid delivery catheter (165) of the 3rd LLI (92), described first, second and the 3rd incendivity fluid delivery catheter (160, 163, 165) each in is fluidly connected to mating part (168).
8. a turbo machine (3), comprising:
Compressor section (4);
Turbine portion (8), it is operatively connected to described compressor section (4); And
Burner assembly (20), it is fluidly connected to described compressor section (4) and described turbine portion (8), and described burner assembly (20) comprising:
Burner (22), it comprises the burner body (52) being extended to the second end (56) from cephalic par (54) by zone of combustion (58);
At least one sparger (60), it constructs and is arranged to the first incendivity fluid to introduce in described zone of combustion (58) at described cephalic par (54) place of described burner body (52);
At least one late lean injection device (LLI) (90-92), it constructs and is arranged to introduce the second incendivity fluid in the downstream of described first incendivity fluid; And
External fluid transporting system (40), it is fluidly connected to described at least one LLI (90-92), described external fluid transporting system (40) comprises at least one incendivity fluid delivery catheter (110), it extends to the outside the second end (113) of described turbo machine (3) burner assembly (20) from the first end (112) being fluidly connected to described LLI (90-92), and described the second end (113) constructs and is arranged to described second incendivity fluid to be transported to described LLI (90-92).
9. turbo machine according to claim 8 (3), it is characterized in that, also comprise: fuel feed line (120), it extends to the second end part (124) from the first end part (123) of the described the second end (113) being fluidly connected at least one incendivity fluid delivery catheter (110) described by intermediate portion (125), and described the second end part (124) is fluidly connected to the outside supply department of incendivity fluid.
10. turbo machine according to claim 9 (3), is characterized in that, also comprise: valve (130), and it is configured in the described intermediate portion (125) of described fuel feed line (120).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/057,458 US20150107255A1 (en) | 2013-10-18 | 2013-10-18 | Turbomachine combustor having an externally fueled late lean injection (lli) system |
| US14/057,458 | 2013-10-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104566468A true CN104566468A (en) | 2015-04-29 |
Family
ID=52775312
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410556421.2A Pending CN104566468A (en) | 2013-10-18 | 2014-10-20 | Turbomachine combustor having an externally fueled late lean injection (LLI) system |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150107255A1 (en) |
| JP (1) | JP2015078831A (en) |
| CN (1) | CN104566468A (en) |
| CH (1) | CH708788A2 (en) |
| DE (1) | DE102014114554A1 (en) |
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Also Published As
| Publication number | Publication date |
|---|---|
| US20150107255A1 (en) | 2015-04-23 |
| DE102014114554A1 (en) | 2015-04-23 |
| CH708788A2 (en) | 2015-04-30 |
| JP2015078831A (en) | 2015-04-23 |
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