EP3063472A1 - Dual-nozzle lance injector for gas turbine, gas turbine plant and method of supplying a gas turbine - Google Patents

Dual-nozzle lance injector for gas turbine, gas turbine plant and method of supplying a gas turbine

Info

Publication number
EP3063472A1
EP3063472A1 EP14809708.2A EP14809708A EP3063472A1 EP 3063472 A1 EP3063472 A1 EP 3063472A1 EP 14809708 A EP14809708 A EP 14809708A EP 3063472 A1 EP3063472 A1 EP 3063472A1
Authority
EP
European Patent Office
Prior art keywords
branch
nozzle
supply conduit
along
supply
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP14809708.2A
Other languages
German (de)
French (fr)
Other versions
EP3063472B1 (en
Inventor
Rocco Galella
Roberta Gatti
Pierpaolo Pastorino
Paolo Pesce
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP3063472A1 publication Critical patent/EP3063472A1/en
Application granted granted Critical
Publication of EP3063472B1 publication Critical patent/EP3063472B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11002—Liquid fuel burners with more than one nozzle

Definitions

  • the present invention relates to a dual-nozzle lance injector for injecting fuel oil into a gas turbine combustion chamber, to a gas turbine plant and to a method of supplying a gas turbine.
  • gas turbines especially if used in plants for the production of electricity, may be supplied with different types of fuel.
  • gas turbines especially gaseous fuels of different nature and characteristics (natural gas, syngas) or with fuel oils such as diesel fuel.
  • gas turbines are provided with burner assemblies which include injectors, normally of the lance type, specifically designed to supply a controlled flow of diffusion fuel oil.
  • Lance injectors generally comprise a plurality of coaxial tubular bodies, at one end of which a terminal provided with a nozzle is fitted.
  • the tubular bodies define therebetween at least one delivery line between an inlet and the nozzle, and a return line, which allows the recovery of the excess fuel supplied to the nozzle.
  • a line for supplying water may also be provided .
  • the delivery line receives a flow of fuel oil at a pressure much higher than the combustion chamber and the injection flow is imposed by regulating a control valve of the return line.
  • the control valve When the control valve is fully closed, the flow rate injected into the combustion chamber is maximum. Conversely, when the control valve is completely open there is maximum recovery of fuel through the return line and the flow rate injected into the combustion chamber is minimal.
  • the structure of the power supply system of the fuel oil in known plants is complex, requires a large number of components and has a negative impact on times and costs both in design and in the construction and maintenance .
  • the object of the present invention therefore is to provide a lance injector for injecting fuel oil into a gas turbine combustion chamber, a gas turbine plant and a method of supplying a gas turbine which allow overcoming or at least limiting the above drawbacks.
  • a lance injector for injecting fuel oil into a gas turbine combustion chamber, a gas turbine plant and a method of supplying a gas turbine combustion chamber as defined in claims 1, 10 and 18, respectively.
  • FIG. 1 shows a simplified block diagram of a plant for the production of electricity
  • FIG. 2 shows a lateral sectional view according to an axial longitudinal plane, with parts removed for clarity, of a burner of a gas turbine incorporating a lance injector according to an embodiment of the present invention, incorporated in the plant in figure 1 ;
  • figure 3 shows an enlarged detail of the lance injector in figure 1 ;
  • figure 4 shows a more detailed block diagram of a part of the plant in figure 1 ;
  • FIG. 5 shows a more detailed block diagram of a part of the plant in figure 1, according to a different embodiment of the present invention.
  • figure 6 shows a graph showing quantities related to the plant in figure 1.
  • reference numeral 1 indicates as a whole a gas turbine plant 1, in particular a plant for the production of electricity.
  • Plant 1 is selectively connectable to a known distribution network 2 and includes a gas turbine assembly 3 and a control device 5.
  • Plant 1 further comprises an alternator 4 of known type, which is mechanically connected to a shaft 7 of the gas turbine assembly 3 and actuated thereby.
  • the control device 5 uses measured plant quantities (here not shown in detail) and set reference values to generate control signals, in order to control the operation of plant 1.
  • the gas turbine assembly 3 comprises a compressor 8, a combustion chamber 9 and a gas turbine 10.
  • Compressor 8 is of the multistage axial type and is provided with an inlet adjustable vane stage or IGV (Inlet Guide Vane) stage 11, driven by an IGV actuator 12 and respective control signals (not shown) provided by the control device 5.
  • IGV Inlet Guide Vane
  • the combustion chamber 9 receives the fuel from a supply system 15, which is controlled by the control device 5, as explained in more detail hereafter.
  • the combustion chamber 9 comprises a plurality of burner assemblies 20, one of which is shown in figure 2, meaning that the others have an identical structure.
  • the burner assembly 20 extends along a main axis A and comprises a peripheral main burner 21, a central pilot burner 22 and a lance injector 23 for injecting fuel oil into the combustion chamber 9.
  • the main burner 21 is of the premixing type, is arranged around the pilot burner 22 and is provided with a diagonal swirler 25, which comprises a plurality of vanes 26, defining therebetween respective flow channels for conveying, with an oblique pattern with respect to the main axis A, a flow of combustion air and fuel gas towards the combustion chamber 9.
  • the fuel is supplied through nozzles 27 placed on vanes 26.
  • the pilot burner 22 is arranged coaxial to the main burner 21 and is provided with an axial swirler 30, which comprises a plurality of vanes 31, defining therebetween respective flow channels for conveying, substantially along the main axis A, a further flow of combustion air towards the combustion chamber 9.
  • the lance injector 23 extends along the main axis A and has one end inserted inside the pilot burner 22.
  • the lance injector 23 comprises a tubular casing 33, a first inner supply conduit 35, a second inner supply conduit 36 and a terminal element 38 provided with a first nozzle 40 and a second nozzle 41 for the first inner supply conduit 35 and the second inner supply conduit 36, respectively. Moreover, the lance injector 23 is provided with a mounting flange 42.
  • the tubular housing 33 extends from the mounting flange 42 along the main axis A of the injector and therein houses both the first inner supply conduit 35 and the second inner supply conduit 36.
  • the first inner supply conduit 35 and the second inner supply conduit 36 in turn extend along the main axis A, about which they are twisted.
  • the first inner supply conduit 35 and the second inner supply conduit 36 extend along respective coiled paths having the main axis A as coil axis and have equal length and equal flow cross-section.
  • a supply end 35a of the first inner supply conduit 35 is coupled to a first supply inlet 44 formed in the mounting flange 42, while an injection end 35b is coupled to the first nozzle 40.
  • a supply end 36a of the second inner supply conduit 36 is coupled to a second supply inlet 45 formed in the mounting flange 42, while an injection end 36b is coupled to the second nozzle 41.
  • the second supply inlet 45 is accessible from the outside independently of the first supply inlet 44.
  • the two inner supply conduits 35, 36 and the relative nozzles 40, 41 can thus be supplied independently, since there are no reciprocal fluid couplings inside the lance injector 23.
  • the terminal element 38 in which the first nozzle 40 and second nozzle 41 are formed, is fitted on the injection ends 35b, 36b of the first inner supply conduit 35 and the second inner supply conduit 36 and is attached to one end of the terminal casing by a fixing bush 47.
  • the fixing is obtained by a threaded coupling or by hot fitting on the side of the tubular casing 33 and through opposed circumferential projections 48, 49 on the side of the terminal element 33.
  • a guide bush 50 inserted by a stretch inside the tubular casing 33 and welded therein, is accommodated into respective seats and holds in place the injection ends 35b, 36b of the first inner supply conduit 35 and the second inner supply conduit 36.
  • the guide bush 50 acts as a spacer element between the end of the tubular casing 33 and the terminal element 38. The latter is retained in abutment against the guide bush 50 by the fixing bush 47.
  • the injection ends 35b, 36b of the first inner supply conduit 35 and the second inner supply conduit 36 communicate with the first nozzle 40 and the second nozzle 41, respectively, through a first outlet passage 51 and a second outlet passage 52 substantially straight, extending parallel inside the terminal element 38 and arranged symmetrically with respect to the main axis A.
  • the first nozzle 40 and the second nozzle 41 are identical and arranged symmetrically with respect to the main axis A and, moreover, they have respective injection axes Bi, B 2 parallel to the main axis A.
  • a first swirler 51a and a second swirler 52a are arranged inside the first outlet passage 51 and the second outlet passage 52, respectively.
  • the first swirler 51a and the second swirler 52a are configured so as to generate a strong turbulence and rotate in-transit flows about the injection axes Bi, B 2 of nozzles 40, 41.
  • FIG. 4 schematically shows the supply system 15, some of the burner assemblies 20 and the control device 5. Moreover, there is shown a water supply line 53 with a respective supply pump 54, used in certain operating conditions for flushing or cooling.
  • the supply system 15 comprises a premix supply line 55 and a diffusion supply line 56, both connected to a fuel pump assembly 57 to receive respective flow rates of fuel oil .
  • the premix supply line 55 is further connected to the premixing portion of the burner assembly 20, i.e. to the main burner 21 and the pilot burner 22 through a premix manifold 58 and premix fittings 59.
  • a stop valve 60 and a premix control valve 61 allow adjusting a fuel flow rate Q F p to the main burner 21 and the pilot burner 22.
  • the stop valve 60 and the premix control valve 61 are provided with respective actuators 60a, 61a, which are controlled by the control device 5 through a premix stop signal S S p and a premix control signal S RP , respectively.
  • the premix supply line 55 is shown here as a single line. It is however understood that independent control lines and/or members may be provided for the main burner 21 and the pilot burner 22.
  • the premix portion of the burner assembly 20 receives fuel gas instead of fuel oil and is thus supplied by separate and independent lines with respect to the diffusion supply line 56.
  • the diffusion supply line 56 has a first branch 56a, which supply the first nozzles 40 through a first diffusion manifold 63, respective first diffusion fittings 64 and the respective first inner supply conduits 35, and a second branch 56b, which supplies the second nozzle 41 through a second diffusion manifold 65, respective second diffusion fittings 66 and the respective second inner supply conduits 36.
  • the adjustment of the first flow rate of fuel oil QFDI to the first nozzle 40 is independent of the adjustment of the second flow rate of fuel oil QFD2 ⁇
  • the stop valve 68 and the first diffusion control valve 69 are arranged along the diffusion supply line 56 upstream of the bifurcation between the first branch 56a and the second branch 56b, while the second diffusion control valve 70 is arranged along the second branch 56b.
  • the first diffusion control valve 69 is arranged along the first branch 56a and the second diffusion control valve 70 is arranged along the second branch 56b.
  • the stop valve 68, the first diffusion control valve 69 and the second diffusion control valve 70 are provided with respective actuators 68a, 69a, 70a, which are controlled by the control device 5 through a diffusion stop signal S SO , a first diffusion control signal S RD i and a second diffusion control signal S RD 2, respectively.
  • control device 5 is configured for continuously supplying the first nozzle 40 of the lance injectors 23 during the whole operating period of the gas turbine 10 and for supplying the second nozzles 41 selectively in a condition of intermediate load between a low load condition, for example upon startup or in premixed operation, and a high load condition, in which the gas turbine 10 substantially delivers the nominal power.
  • the intermediate load condition corresponds for example to a load range between 30% and 55% of the maximum load that can be delivered by the gas turbine 10.
  • the graphs in figure 6 show the flow rates of fuel supplied to the lance injectors 23 according to the load.
  • the upper portion of figure 6 shows the overall fuel flow rate QFDI+QFD2 ; the lower portion separately shows the first flow rate of fuel oil Q F DI supplied to the first nozzles 40 and the second flow rate of fuel oil Q F D2 supplied to the second nozzles 41.
  • the control device 5 stops supplying fuel oil to the second nozzles 41 under low load conditions and high load conditions, when the system is in premix operation.
  • the injection conditions are always optimal for both the first nozzles 40 and for the second nozzles 41, when they are used, and the required flow rates can be correctly atomized even in the absence of a return line or atomization air.
  • the lance injectors 23 always work in an effective manner, while allowing obtaining an overall range of flows wide enough to meet all load conditions.
  • the plant is simplified thanks to the structure of the lance injectors 23, since there is no need to provide a dedicated manifold and fittings.
  • the water supply line 53 is connected to the second branch 56a of the diffusion supply line 56, for example to the second diffusion manifold 65.
  • a stop valve 71 and a water control valve 72 arranged along the water supply line and provided with respective actuators 71a, 72a, are used to supply a water flow to the second nozzles 41 of the burners.
  • Actuators 71a, 72a are controlled by the control device 5 through a water stop signal S S w and a water control signal S RW .
  • the water flow is supplied when the supply of fuel oil to the second nozzles 41 is deactivated, i.e. in the low load condition or in the high load condition.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Spray Control Apparatus (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

A lance injector for injecting fuel oil into a gas turbine combustion chamber includes: a tubular casing (33), extending along a main axis (A); a first inner supply conduit (35) housed in the casing (33) and coupled, at a respective supply end (35a), to a first supply inlet (44); a first nozzle (40), at a respective injection end (35b) of the first inner supply conduit (35); a second inner supply conduit (36) housed in the casing (33) and coupled, at a respective supply end (36a), to a second supply inlet (45), accessible from the outside independently of the first supply inlet (44); and a second nozzle (41), at a respective injection end (36a) of the second inner supply conduit (36).

Description

DUAL -NOZZLE LANCE INJECTOR FOR GAS TURBINE , GAS TURBINE PLANT AND ME THOD OF SUPPLYING A GAS TURBINE
TECHNICAL FIELD
The present invention relates to a dual-nozzle lance injector for injecting fuel oil into a gas turbine combustion chamber, to a gas turbine plant and to a method of supplying a gas turbine.
BACKGROUND ART
As is known, gas turbines, especially if used in plants for the production of electricity, may be supplied with different types of fuel. In particular, it is known to operate gas turbines with gaseous fuels of different nature and characteristics (natural gas, syngas) or with fuel oils such as diesel fuel. For this reason, gas turbines are provided with burner assemblies which include injectors, normally of the lance type, specifically designed to supply a controlled flow of diffusion fuel oil.
Lance injectors generally comprise a plurality of coaxial tubular bodies, at one end of which a terminal provided with a nozzle is fitted. The tubular bodies define therebetween at least one delivery line between an inlet and the nozzle, and a return line, which allows the recovery of the excess fuel supplied to the nozzle. Optionally, a line for supplying water may also be provided .
The use of the return line allows correctly supplying the injectors on a very wide range of flows, as required in the normal operation of gas turbines. In practice, the delivery line receives a flow of fuel oil at a pressure much higher than the combustion chamber and the injection flow is imposed by regulating a control valve of the return line. When the control valve is fully closed, the flow rate injected into the combustion chamber is maximum. Conversely, when the control valve is completely open there is maximum recovery of fuel through the return line and the flow rate injected into the combustion chamber is minimal.
This type of solutions, as said, allows obtaining acceptable supply conditions, both with regard to the pressure and the atomization of the fuel, on a range of flow wide enough to meet the demand of the machinery in all load conditions. In fact, the flow rate of diffusion fuel oil grows substantially linearly at low loads, has a high peak at intermediate loads, during the transition to the premixed mode supply, and then decreases at high loads, where the premixed supply mode is prevalent. The difference in flow rate between the peak at intermediate loads and minimum flows is remarkable and requires measures such as, precisely, the supply in high overpressure and the use of a return line. However, from the constructive point of view, an additional line is a considerable complication, since it is necessary to provide piping on the machine, a distribution manifold and interconnecting piping.
Other solutions require complex atomization systems with air.
In any case, the structure of the power supply system of the fuel oil in known plants is complex, requires a large number of components and has a negative impact on times and costs both in design and in the construction and maintenance .
DISCLOSURE OF INVENTION
The object of the present invention therefore is to provide a lance injector for injecting fuel oil into a gas turbine combustion chamber, a gas turbine plant and a method of supplying a gas turbine which allow overcoming or at least limiting the above drawbacks.
According to the present invention there are provided a lance injector for injecting fuel oil into a gas turbine combustion chamber, a gas turbine plant and a method of supplying a gas turbine combustion chamber as defined in claims 1, 10 and 18, respectively.
BRIEF DESCRIPTION OF THE DRAWINGS
The present invention will now be described with reference to the accompanying drawings, which show some non-limiting embodiment examples thereof, in which:
- figure 1 shows a simplified block diagram of a plant for the production of electricity;
- figure 2 shows a lateral sectional view according to an axial longitudinal plane, with parts removed for clarity, of a burner of a gas turbine incorporating a lance injector according to an embodiment of the present invention, incorporated in the plant in figure 1 ;
figure 3 shows an enlarged detail of the lance injector in figure 1 ;
- figure 4 shows a more detailed block diagram of a part of the plant in figure 1 ;
- figure 5 shows a more detailed block diagram of a part of the plant in figure 1, according to a different embodiment of the present invention; and
- figure 6 shows a graph showing quantities related to the plant in figure 1.
BEST MODE FOR CARRYING OUT THE INVENTION
In figure 1, reference numeral 1 indicates as a whole a gas turbine plant 1, in particular a plant for the production of electricity. Plant 1 is selectively connectable to a known distribution network 2 and includes a gas turbine assembly 3 and a control device 5. Plant 1 further comprises an alternator 4 of known type, which is mechanically connected to a shaft 7 of the gas turbine assembly 3 and actuated thereby.
The control device 5 uses measured plant quantities (here not shown in detail) and set reference values to generate control signals, in order to control the operation of plant 1.
The gas turbine assembly 3 comprises a compressor 8, a combustion chamber 9 and a gas turbine 10.
Compressor 8 is of the multistage axial type and is provided with an inlet adjustable vane stage or IGV (Inlet Guide Vane) stage 11, driven by an IGV actuator 12 and respective control signals (not shown) provided by the control device 5.
The combustion chamber 9 receives the fuel from a supply system 15, which is controlled by the control device 5, as explained in more detail hereafter.
The combustion chamber 9 comprises a plurality of burner assemblies 20, one of which is shown in figure 2, meaning that the others have an identical structure.
The burner assembly 20 extends along a main axis A and comprises a peripheral main burner 21, a central pilot burner 22 and a lance injector 23 for injecting fuel oil into the combustion chamber 9.
The main burner 21 is of the premixing type, is arranged around the pilot burner 22 and is provided with a diagonal swirler 25, which comprises a plurality of vanes 26, defining therebetween respective flow channels for conveying, with an oblique pattern with respect to the main axis A, a flow of combustion air and fuel gas towards the combustion chamber 9. In one embodiment, the fuel is supplied through nozzles 27 placed on vanes 26.
The pilot burner 22 is arranged coaxial to the main burner 21 and is provided with an axial swirler 30, which comprises a plurality of vanes 31, defining therebetween respective flow channels for conveying, substantially along the main axis A, a further flow of combustion air towards the combustion chamber 9.
The lance injector 23 extends along the main axis A and has one end inserted inside the pilot burner 22.
The lance injector 23 comprises a tubular casing 33, a first inner supply conduit 35, a second inner supply conduit 36 and a terminal element 38 provided with a first nozzle 40 and a second nozzle 41 for the first inner supply conduit 35 and the second inner supply conduit 36, respectively. Moreover, the lance injector 23 is provided with a mounting flange 42.
The tubular housing 33 extends from the mounting flange 42 along the main axis A of the injector and therein houses both the first inner supply conduit 35 and the second inner supply conduit 36.
The first inner supply conduit 35 and the second inner supply conduit 36 in turn extend along the main axis A, about which they are twisted. In one embodiment, in particular, the first inner supply conduit 35 and the second inner supply conduit 36 extend along respective coiled paths having the main axis A as coil axis and have equal length and equal flow cross-section.
A supply end 35a of the first inner supply conduit 35 is coupled to a first supply inlet 44 formed in the mounting flange 42, while an injection end 35b is coupled to the first nozzle 40.
Likewise, a supply end 36a of the second inner supply conduit 36 is coupled to a second supply inlet 45 formed in the mounting flange 42, while an injection end 36b is coupled to the second nozzle 41. The second supply inlet 45 is accessible from the outside independently of the first supply inlet 44. The two inner supply conduits 35, 36 and the relative nozzles 40, 41 can thus be supplied independently, since there are no reciprocal fluid couplings inside the lance injector 23.
As shown in more detail in figure 3, the terminal element 38, in which the first nozzle 40 and second nozzle 41 are formed, is fitted on the injection ends 35b, 36b of the first inner supply conduit 35 and the second inner supply conduit 36 and is attached to one end of the terminal casing by a fixing bush 47. The fixing is obtained by a threaded coupling or by hot fitting on the side of the tubular casing 33 and through opposed circumferential projections 48, 49 on the side of the terminal element 33. A guide bush 50, inserted by a stretch inside the tubular casing 33 and welded therein, is accommodated into respective seats and holds in place the injection ends 35b, 36b of the first inner supply conduit 35 and the second inner supply conduit 36. Moreover, the guide bush 50 acts as a spacer element between the end of the tubular casing 33 and the terminal element 38. The latter is retained in abutment against the guide bush 50 by the fixing bush 47.
The injection ends 35b, 36b of the first inner supply conduit 35 and the second inner supply conduit 36 communicate with the first nozzle 40 and the second nozzle 41, respectively, through a first outlet passage 51 and a second outlet passage 52 substantially straight, extending parallel inside the terminal element 38 and arranged symmetrically with respect to the main axis A.
The first nozzle 40 and the second nozzle 41 are identical and arranged symmetrically with respect to the main axis A and, moreover, they have respective injection axes Bi, B2 parallel to the main axis A.
A first swirler 51a and a second swirler 52a are arranged inside the first outlet passage 51 and the second outlet passage 52, respectively. The first swirler 51a and the second swirler 52a are configured so as to generate a strong turbulence and rotate in-transit flows about the injection axes Bi, B2 of nozzles 40, 41.
Figure 4 schematically shows the supply system 15, some of the burner assemblies 20 and the control device 5. Moreover, there is shown a water supply line 53 with a respective supply pump 54, used in certain operating conditions for flushing or cooling.
The supply system 15 comprises a premix supply line 55 and a diffusion supply line 56, both connected to a fuel pump assembly 57 to receive respective flow rates of fuel oil .
The premix supply line 55 is further connected to the premixing portion of the burner assembly 20, i.e. to the main burner 21 and the pilot burner 22 through a premix manifold 58 and premix fittings 59. A stop valve 60 and a premix control valve 61 allow adjusting a fuel flow rate QFp to the main burner 21 and the pilot burner 22. The stop valve 60 and the premix control valve 61 are provided with respective actuators 60a, 61a, which are controlled by the control device 5 through a premix stop signal SSp and a premix control signal SRP, respectively. For simplicity, the premix supply line 55 is shown here as a single line. It is however understood that independent control lines and/or members may be provided for the main burner 21 and the pilot burner 22. In a different embodiment, not shown herein, the premix portion of the burner assembly 20 receives fuel gas instead of fuel oil and is thus supplied by separate and independent lines with respect to the diffusion supply line 56.
The diffusion supply line 56 has a first branch 56a, which supply the first nozzles 40 through a first diffusion manifold 63, respective first diffusion fittings 64 and the respective first inner supply conduits 35, and a second branch 56b, which supplies the second nozzle 41 through a second diffusion manifold 65, respective second diffusion fittings 66 and the respective second inner supply conduits 36.
A stop valve 68, a first diffusion control valve 69 and a second diffusion control valve 70, controlled by the control device 5 as described hereafter, allow adjusting a first flow rate of fuel oil QFDI to the first nozzle 40 and a second flow rate of fuel oil QFD2 to the second nozzle 41 of each lance injector 23 as a function of the operating conditions. The adjustment of the first flow rate of fuel oil QFDI to the first nozzle 40 is independent of the adjustment of the second flow rate of fuel oil QFD2 ·
The stop valve 68 and the first diffusion control valve 69 are arranged along the diffusion supply line 56 upstream of the bifurcation between the first branch 56a and the second branch 56b, while the second diffusion control valve 70 is arranged along the second branch 56b.
In a different embodiment, shown in figure 5, the first diffusion control valve 69 is arranged along the first branch 56a and the second diffusion control valve 70 is arranged along the second branch 56b.
The stop valve 68, the first diffusion control valve 69 and the second diffusion control valve 70 are provided with respective actuators 68a, 69a, 70a, which are controlled by the control device 5 through a diffusion stop signal SSO, a first diffusion control signal SRDi and a second diffusion control signal SRD2, respectively.
In particular, the control device 5 is configured for continuously supplying the first nozzle 40 of the lance injectors 23 during the whole operating period of the gas turbine 10 and for supplying the second nozzles 41 selectively in a condition of intermediate load between a low load condition, for example upon startup or in premixed operation, and a high load condition, in which the gas turbine 10 substantially delivers the nominal power. The intermediate load condition corresponds for example to a load range between 30% and 55% of the maximum load that can be delivered by the gas turbine 10.
The graphs in figure 6 show the flow rates of fuel supplied to the lance injectors 23 according to the load. The upper portion of figure 6 shows the overall fuel flow rate QFDI+QFD2 ; the lower portion separately shows the first flow rate of fuel oil QFDI supplied to the first nozzles 40 and the second flow rate of fuel oil QFD2 supplied to the second nozzles 41. As can be seen, the control device 5 stops supplying fuel oil to the second nozzles 41 under low load conditions and high load conditions, when the system is in premix operation.
In this way, the injection conditions are always optimal for both the first nozzles 40 and for the second nozzles 41, when they are used, and the required flow rates can be correctly atomized even in the absence of a return line or atomization air. The lance injectors 23 always work in an effective manner, while allowing obtaining an overall range of flows wide enough to meet all load conditions. The plant is simplified thanks to the structure of the lance injectors 23, since there is no need to provide a dedicated manifold and fittings.
With reference again to figure 4, in one embodiment, the water supply line 53 is connected to the second branch 56a of the diffusion supply line 56, for example to the second diffusion manifold 65. A stop valve 71 and a water control valve 72, arranged along the water supply line and provided with respective actuators 71a, 72a, are used to supply a water flow to the second nozzles 41 of the burners. Actuators 71a, 72a are controlled by the control device 5 through a water stop signal SSw and a water control signal SRW. In particular, the water flow is supplied when the supply of fuel oil to the second nozzles 41 is deactivated, i.e. in the low load condition or in the high load condition.
Finally, it is clear that changes and variations may be made to the lance injector, plant and method described without departing from the scope of the present invention, as defined in the appended claims.

Claims

1. A lance injector for injecting fuel oil into a gas turbine combustion chamber, the lance injector comprising: a tubular casing (33) extending along a main axis (A); a first inner supply conduit (35) housed inside the casing (33) and coupled, at a respective supply end (35a), to a first supply inlet (44);
a first nozzle (40) at a respective injection end (35b) of the first inner supply conduit (35);
a second inner supply conduit (36) housed inside the casing (33) and coupled, at a respective supply end (36a), to a second supply inlet (45) accessible from the outside independently of the first supply inlet (44); and
a second nozzle (41) at a respective injection end (36a) of the second inner supply conduit (36) .
2. An injector as claimed in Claim 1, wherein the first inner supply conduit (35) and the second inner supply conduit (36) are twisted about the main axis (A) .
3. An injector as claimed in Claim 1 or 2, wherein the first inner supply conduit (35) and the second inner supply conduit (36) extend along respective coiled paths about the main axis (A) .
4. An injector as claimed in any one of the foregoing Claims, wherein the first inner supply conduit (35) and the second inner supply conduit (36) are of the same length and cross section.
5. An injector as claimed in any one of the foregoing Claims, wherein the first nozzle (40) and second nozzle (41) have respective injection axes (Bi, B2) parallel to the main axis (A) .
6. An injector as claimed in any one of the foregoing Claims, wherein the first nozzle (40) and second nozzle (41) are formed in a terminal element (38) fitted to the injection ends (35b, 36b) of the first inner supply conduit (35) and second inner supply conduit (36) .
7. An injector as claimed in any one of the foregoing Claims, wherein the first nozzle (40) and second nozzle (41) are arranged symmetrically with respect to the main axis (A) .
8. An injector as claimed in any one of the foregoing Claims, comprising a first outlet passage (51) between the first inner supply conduit (35) and the first nozzle (40); and a second outlet passage (52) between the second inner supply conduit (36) and the second nozzle (41); and wherein the first outlet passage (51) and second outlet passage (52) are straight, parallel to the main axis (A), and arranged symmetrically with respect to the main axis (A) .
9. An injector as claimed in Claim 8, comprising a first swirler (51a) in the first outlet passage (51), and a second swirler (52a) in the second outlet passage (52); and wherein the first swirler (51a) and second swirler (52a) are configured to rotate in-transit flow.
10. A gas turbine plant comprising at least one burner assembly (20) having a lance injector (23) as claimed in any one of the foregoing Claims.
11. A system as claimed in Claim 10, comprising:
a fuel supply line (56) having a first branch (56a) fluidly coupled to the first inner supply conduit (35), and a second branch (56b) fluidly coupled to the second inner supply conduit (36); and
regulating elements (68, 69, 70) configured to independently regulate a first fuel oil flow ( QN ) supplied to the first inner supply conduit (35) along the first branch (56a) of the fuel supply line (56), and a second fuel oil flow ( QF2 ) supplied to the second inner supply conduit (36) along the second branch (56b) of the fuel supply line (56) .
12. A system as claimed in Claim 11, comprising a control device (5) for controlling the regulating elements (68, 69, 70) and configured to supply the first fuel oil flow to the first nozzle (40) along the first branch (56a) of the fuel supply line (56), and, selectively in a first operating condition, to supply the second fuel oil flow to the second nozzle (41) along the second branch (56b) of the fuel supply line (56) .
13. A system as claimed in Claim 12, wherein the control device (5) is configured to cut off the second fuel oil flow ( QF2 ) selectively in a second operating condition.
14. A system as claimed in any one of Claims 11 to 13, wherein the regulating elements (68, 69, 70) comprise a first diffusion regulating valve (69) along the fuel supply line (56), upstream from the first branch (56a) and second branch (56b); and a second diffusion regulating valve (70) along the second branch (56b) .
15. A system as claimed in any one of Claims 11 to 13, wherein the regulating elements (68, 69, 70) comprise a first diffusion regulating valve (69) along the first branch (56a) and a second diffusion regulating valve (70) along the second branch (56b) .
16. A system as claimed in any one of Claims 11 to 15, comprising a water supply line (53) connected to the second branch (56b) and configured to supply water to the second branch (56b); and a water regulating valve (72) along the water supply line (53) .
17. A system as claimed in Claim 16 dependent on Claim 13, wherein the water regulating valve (72) is controlled by the control device (5), and the control device (5) is configured to supply water in the second operating condition .
18. A method of supplying gas turbine, comprising: supplying a first fuel oil flow (Qn) along a first branch (56a) of a fuel supply line (56) to first nozzles
(40) of lance injectors (23); and
supplying a second fuel oil flow (QF2 ) along a second branch (56b) of the fuel supply line (56) to second nozzles
(41) of the lance injectors (23) selectively in a first operating condition.
19. A method as claimed in Claim 18, comprising cutting off the second fuel oil flow (QF2) selectively in a second operating condition.
20. A method as claimed in Claim 19, comprising supplying water along the second branch (56b) of the fuel supply line (56) in the second operating condition.
21. A method as claimed in any one of Claims 18 to 20, comprising regulating the second fuel oil flow (QF2) independently of the first fuel oil flow (QF1) .
22. A method as claimed in any one of Claims 18 to 21, wherein the first operating condition comprises current gas turbine output load values ranging between 30% and 55% of a maximum load value.
EP14809708.2A 2013-10-31 2014-10-31 Dual-nozzle lance injector for gas turbine, gas turbine plant and method of supplying a gas turbine Active EP3063472B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
IT001816A ITMI20131816A1 (en) 2013-10-31 2013-10-31 INJECTOR WITH A DOUBLE NOZZLE SPEAR GAS TURBINE SYSTEM, GAS TURBINE SYSTEM AND A GAS TURBINE FEEDING METHOD
PCT/IB2014/065743 WO2015063733A1 (en) 2013-10-31 2014-10-31 Dual-nozzle lance injector for gas turbine, gas turbine plant and method of supplying a gas turbine

Publications (2)

Publication Number Publication Date
EP3063472A1 true EP3063472A1 (en) 2016-09-07
EP3063472B1 EP3063472B1 (en) 2018-12-26

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EP14809708.2A Active EP3063472B1 (en) 2013-10-31 2014-10-31 Dual-nozzle lance injector for gas turbine, gas turbine plant and method of supplying a gas turbine

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EP (1) EP3063472B1 (en)
CN (1) CN105829801B (en)
IT (1) ITMI20131816A1 (en)
RU (1) RU2672009C2 (en)
WO (1) WO2015063733A1 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3068113B1 (en) * 2017-06-27 2019-08-23 Safran Helicopter Engines FLAT JET FUEL INJECTOR FOR AN AIRCRAFT TURBOMACHINE

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5836164A (en) * 1995-01-30 1998-11-17 Hitachi, Ltd. Gas turbine combustor
GB9709205D0 (en) * 1997-05-07 1997-06-25 Boc Group Plc Oxy/oil swirl burner
US6598383B1 (en) * 1999-12-08 2003-07-29 General Electric Co. Fuel system configuration and method for staging fuel for gas turbines utilizing both gaseous and liquid fuels
US6715295B2 (en) * 2002-05-22 2004-04-06 Siemens Westinghouse Power Corporation Gas turbine pilot burner water injection and method of operation
US7143583B2 (en) * 2002-08-22 2006-12-05 Hitachi, Ltd. Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor
US6802178B2 (en) * 2002-09-12 2004-10-12 The Boeing Company Fluid injection and injection method
US8443608B2 (en) * 2008-02-26 2013-05-21 Delavan Inc Feed arm for a multiple circuit fuel injector
WO2010070692A1 (en) * 2008-12-19 2010-06-24 Ansaldo Energia S.P.A. Method for supplying a gas turbine plant and gas turbine plant
EP2208927B1 (en) * 2009-01-15 2016-03-23 Alstom Technology Ltd Burner of a gas turbine
US8584467B2 (en) * 2010-02-12 2013-11-19 General Electric Company Method of controlling a combustor for a gas turbine
JP6018714B2 (en) * 2012-11-21 2016-11-02 ゼネラル・エレクトリック・カンパニイ Anti-coking liquid fuel cartridge

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RU2016120851A3 (en) 2018-06-18
WO2015063733A1 (en) 2015-05-07
CN105829801B (en) 2018-05-18
RU2672009C2 (en) 2018-11-08
EP3063472B1 (en) 2018-12-26
ITMI20131816A1 (en) 2015-05-01
CN105829801A (en) 2016-08-03
RU2016120851A (en) 2017-12-05

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