CN1676902A - Controlled pressure fuel nozzle system - Google Patents
Controlled pressure fuel nozzle system Download PDFInfo
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- CN1676902A CN1676902A CN 200510054199 CN200510054199A CN1676902A CN 1676902 A CN1676902 A CN 1676902A CN 200510054199 CN200510054199 CN 200510054199 CN 200510054199 A CN200510054199 A CN 200510054199A CN 1676902 A CN1676902 A CN 1676902A
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- fuel
- nozzle
- fuel injection
- injection pipe
- pipe road
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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
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
A multi-staged gas turbine engine fuel supply fuel injector includes at least first and second staged fuel injection circuits having first and second fuel injection points. At least first and second fuel nozzle valves operable to open at different first and second crack open pressures are controllably connected to the first and second staged fuel injection circuits, respectively. A single fuel supply manifold is connected to all of the fuel nozzle valves. A single fuel signal manifold is controllably connected to all of the first and second fuel nozzle valves. The fuel injector includes a valve housing containing the fuel nozzle valves.
Description
Technical field
The present invention relates generally to the fuel injector of gas-turbine combustion chamber, especially relate to the fuel injector of the fuel supply system that is used for classification.
Background technique
In order to reduce discharge amount, gas turbine adopts the burner of lean combustion, and this burner need open and close independently fuel conduit under the operating conditions of certain limit, and this operating conditions comprises engine power level and environmental factor.This is commonly referred to local air fuel ratio that fuel staging and it need keep motor in a narrower scope, and the upper limit of this scope is by NO
xDischarging determines that lower limit is determined by flame-out border.
Existing motor has adopted the concentrated partialization valves (centralized staging valves) of a plurality of independent controls of many fuel supply menifolds, and this fuel supply menifold transfer the fuel is in fuel nozzle.Every grade is used a fuel supply menifold, and therefore, each fuel nozzle has a plurality of fuel supply interfaces, and every grade has been adopted an interface.In order to prevent coking, the circulation that fuel must be discharged or continue in this menifold from unassorted menifold.The fuel system of this many menifolds is complicated and ring-type or crooked fuel feed pipe that need multiple shape and size, to supply the fuel in the fuel nozzle not at the same level.It is desirable to adopt a kind of fuel system, it has single fuel menifold and comprises the fuel injector of fuel nozzle not at the same level.
Fuel system with a plurality of concentrated partialization valves is expensive, and engine designer always is devoted to design a kind of have better operation responsiveness and more reliable fuel system.Concentrate the classification fuel system to reduce in boost phase speed, this is because in this system, and flowing into before the fuel unassorted fuel menifold in pipeline must be pressurized and void volume filled.It is desirable to very much make the reduction of speed to reduce.
For example the fuel injector in the gas turbine will import in one or more the firing chamber from the fuel that pressurizes in the menifold.Fuel injector is also prepared fuel is mixed mutually with air before burning.Each sparger has the inlet device that links to each other with menifold usually, installs atubular extension part or the bar that an end links to each other therewith, and one or more jet nozzles that links to each other with the other end of bar is used for burner oil is imported to the firing chamber.Fuel pipe or passage (for example, flexible pipe, conduit, perhaps cylindric passage) extend through bar, thereby fuel is supplied in the nozzle from inlet device.Provide suitable valve and/or shunt to flow with the fuel that guides and control by nozzle.Fuel injector is arranged in the even isolated ring device usually, thereby can distribute (injection) fuel in the firing chamber in uniform mode.
Summary of the invention
The fuel injector of multistage gas turbine fuel supply system comprises at least the first and second grades of fuel injection pipe roads.Each first and second grades of fuel injection pipe road has first and second fuel injection point and at least the first and second fuel nozzle valves respectively, and these fuel nozzle valves link to each other respectively with first and second grades of fuel injection pipe roads controllably.The first and second fuel nozzle valves are opened to move under the condition of pressure different first and second respectively and are opened.The first and second fuel nozzle valves are arranged in the valve pocket of sparger, this sparger comprises the single fuel supply connector that links to each other with first and second nozzle group valves with the fuel supply relation, and concerns the single fuel signal connector that links to each other with the first and second fuel nozzle valves with pressure feed.
In an embodiment of fuel injector, first fuel injection point of first order fuel injector pipeline is the top spray orifice in the fuel injector tip of pilot burner of fuel injector.Second fuel injection point of second level fuel injector pipeline is the spray orifice of fuel injector main nozzle.System also is included in the third level fuel injection pipe road that has the 3rd fuel injection point in the fuel injector.The 3rd fuel injection point also is arranged in the main nozzle of fuel injector.
Description of drawings
Fig. 1 represents only to have the schematic representation of fuel supply system of the multistage gas turbine of single fuel supply menifold and single fuel signal manifold.
Fig. 2 represents only to have the schematic representation of fuel supply system of three grades of gas turbines of single fuel supply menifold and single fuel signal manifold.
Fig. 3 represents only to have the schematic representation of fuel supply system of gas turbine of the dual secondary fuel sparger of single fuel supply menifold.
Fig. 4 represents only to have the schematic representation of fuel supply system of gas turbine of dual three grades of fuel injectors of single fuel supply menifold.
Fig. 5 represents to have the cross-sectional view of gas-turbine combustion chamber of three grades of fuel injectors of one exemplary embodiment of the present invention.
Fig. 6 represents to have the cross-sectional view of amplification of the fuel injector of fuel nozzle assembly shown in Figure 5.
Fig. 7 is illustrated in the cross-sectional view of the amplification of the fuel nozzle assembly shown in Fig. 6.
Fig. 8 is illustrated in the perspective view of the fuel injector shown in Fig. 6.
Fig. 9 represents the cross-sectional view of the fuel tape cut open along the 9-9 shown in Fig. 6.
Figure 10 is illustrated in the top view that being used for shown in Fig. 5 forms the flat board of fuel tape.
Figure 11 is illustrated in the schematic representation of the fuel conduit of the fuel injector shown in Fig. 5.
Figure 12 is illustrated in the perspective view of the fuel tape with fuel conduit shown in Figure 11.
Figure 13-16 is the schematic representation of two valves, and it shows the runnability that the expression of being adopted only has three grades of gas turbine fuel supply systems of two valves of single supply of fuel menifold and single fuel signal manifold.
Embodiment
What represent in Fig. 1 is an one exemplary embodiment of multistage gas turbine fuel supply system 8, and this fuel supply system provides fuel in the first order fuel injection pipe road 411 and fuel injection pipe road, the second level 412 in each of a plurality of fuel injectors 10.In first order fuel injection pipe road 411 and the fuel injection pipe road, the second level 412 each all has first fuel injection point 413 and second fuel injection point 414.The first fuel nozzle valve 415 controllably links to each other with fuel injection pipe road, the second level 412 with first order fuel injection pipe road 411 respectively with the second fuel nozzle valve 416.Fuel feed line 431 comprises the single fuel supply menifold 409 that links to each other with 416 with fuel supply relation and all fuel nozzle valve 415.The first fuel nozzle valve 415 and the second fuel nozzle valve 416 are opened pressure 419 and second different first respectively and are opened to move under the situation of pressure 420 and open, shown in the different different arrow length of opening pressure of expression.The first all fuel nozzle valves 415 and the second fuel nozzle valve 416 all controllably link to each other with single fuel signal menifold 16 in signal pipeline 433.
Represented one of fuel injector 10 more specifically one exemplary embodiment among Fig. 1, it comprises first fuel injection point 413 on first order fuel injection pipe road 411, and wherein first fuel injection point 413 is the top spray orifice 55 in the fuel injector top 57 of the pilot burner 58 of Fig. 5 and fuel injector illustrated in fig. 7 10.Second fuel injection point 414 on fuel injection pipe road, the second level 412 is the spray orifice 106 in the main nozzle 59 of Fig. 5 and fuel injector illustrated in fig. 7 10.As shown in Figure 2, system 8 also comprises the third level fuel injection pipe road 460 with the 3rd fuel injection point 462 that is arranged in fuel injector 10.Have the 3rd the 3rd fuel nozzle valve 480 of opening pressure 482 and be arranged in third level fuel injection pipe road 460.System can have fuel injection pipe road 460 above three grades that is arranged in fuel injector 10 and the fuel injection point 462 that surpasses three grades.
The one exemplary embodiment of system 8 as depicted in figs. 1 and 2 also comprises differential pressure measurement device 418, and this device is to be used for signal pressure 417 in the testing signal pipeline 433 and the pressure reduction DCPFN between the fuel-supplying pressure 427 in the fuel feed line 431.Controlling pressure regulator 422 with the fuel-control unit 421 of 418 one-tenth feedback signal relations of differential pressure measurement device, and this pressure regulator links to each other controllably with fuel-control unit 421.Pressure by signal pipeline 433 is controlled and adjusted to fuel-control unit 421 by pilot pressure regulator 422, thereby send into the pressure of opening of fuel nozzle valve in the single fuel signal manifold 16 of control from signal pipeline 433.When the pressure in the signal pipeline 433 equals or exceeds first when opening pressure 419, state is opened and stayed open to the first fuel nozzle valve 415.When the pressure in the signal pipeline 433 equals or exceeds second when opening pressure 420, state is opened and stayed open to the second fuel nozzle valve 416.The many fuel of each sparger of being used for every grade and the needs of signal pipeline have been eliminated like this.
Petrolift 441 links to each other with fuel metering valve 437 with the fuel supply relation, and this fuel metering valve 437 links to each other with fuel supply menifold 409 with the fuel supply relation.Fuel metering valve 437 controllably links to each other with fuel-control unit 421.The first pressure incoming line 435 and leads to differential pressure measurement device 418 between pressure regulator 422 and signal pipeline 433.The second pressure incoming line 436 leads to differential pressure measurement device 418 from certain point on the fuel feed line 431 between fuel metering valve 437 and the fuel supply menifold 409.Differential pressure measurement device 418 is generally pressure transducer.This pressure transducer can be machinery or electric.
Petrolift 441 has a pump discharge 443, and this outlet links to each other with pressure regulator 422 and also links to each other with fuel metering valve 437 with the fuel supply relation with the fuel pressure the relation between supply and demand.Pressure regulator 422 uses at transient working condition or in service, and the relation that it also falls with pressure links to each other with suction booster 451 by pressure regulator return line 450 and suction booster inlet 452.Pressure regulator 422 is threeway servomechanisms and cuts out or during off position, pressure regulator can be opened pressure regulator return line 450 when pressure regulator 422 is in with turning round.Note be pressure regulator 422 close or off position is not the path of fuel signal menifold 16 of having finished contract fully.Pump bypass road inlet 440 and petrolift 441 are led to from pump discharge 443 in pump bypass road 439, and have bypass valve 445 betwixt.Fuel signal return line 447 leads to fuel signal from fuel signal manifold 16 and returns inlet 442 and petrolift 441.The return line mouth of pipe 449 is arranged in the fuel signal return line 447.In engine operation process, the return line mouth of pipe 449 allows fuel to keep flowing in signal menifold 409, and avoids the coking in nozzle, and has reduced the Pressure gain by pressure regulator 422.Petrolift 441 comprises suction booster 451, and this suction booster is in the upstream of main pump 453 and become the relation of continuous-flow with main pump.Pump bypass road inlet 440 is arranged between suction booster 451 and the main pump 453.Fuel signal return line 447 leads to fuel signal from fuel signal menifold 16 and returns inlet 442 and be positioned at enter the mouth 452 petrolift 441 of suction booster, and then leads on the suction booster 451.
Fig. 3 and shown in Figure 4 be an one exemplary embodiment of the controlled pressurized fuel supply system 8 of multistage gas turbine, this fuel supply system has two groups or organize fuel injector 10 more.Illustrated system 8 provides fuel to respectively in the first order fuel injection pipe road 411 and fuel injection pipe road, the second level 412 in first group (pluralities) 406 and second group 408 every group of fuel injector 10.Each group in first and second groups, if or more words are provided, can under the situation that other group or other many groups are opened, open or close.This can be used for the classification (circumferential staging) on the circumference.System 8 shown in Figure 3 is used for dual level two, and system 8 shown in Figure 4 is used for dual three-level system.As shown in Fig. 3 and Fig. 4, the fuel supply pipe 431 that can be used for dual secondary and three-level system comprises single fuel supply menifold 409, this menifold concerns with all fuel nozzle valves 415 with fuel supply and links to each other with 416 that this fuel nozzle valve is first fuel injection point 413 and second fuel injection point 414 that is used to control first group 406 and second groups 408 fuel injectors 10.First group of 406 fuel injector 10 intersects mutually with second group of 408 fuel injector 10 so that circumferentially the fuel injector 10 of adjacency by first group 406 with second group of 408 fuel injector 10 in different fuel injector 10 form.
The first fuel nozzle valve 415 and the second fuel nozzle valve 416 are opened pressure 419 and second different first respectively and are opened pressure 420 operations and open, and wherein different opens pressure as being represented by the different arrow length in dual level two shown in Fig. 3.Being used for first group of 406 pressure of opening with first nozzle group valve 415 of second group of 408 fuel injector 10 and second nozzle group valve 416 can be identical or different.Interchangeable, with regard to first and second group 406 and 408, can open it and the shut-in time is arranged to identical or different.
In first group of 406 fuel injector 10, the first fuel nozzle valve 415 that is used for first group of 406 fuel injector 10 controllably links to each other with second fuel injection point 414 with first fuel injection point 413 respectively with the fuel supply relation with the second fuel nozzle valve 416.The first fuel nozzle valve 415 of first group of 406 fuel injector 10 controllably links to each other with the first fuel signal menifold 456 of the second fuel nozzle valve 416 with first signal pipeline 464 that is used for first group of 406 fuel injector 10.First Fuelinjection nozzle 415 of second group of 408 fuel injector 10 and second Fuelinjection nozzle 416 with the fuel supply relation respectively with second group 408 of fuel injector 10 in first fuel injection point 413 controllably link to each other with second fuel injection point 414.First Fuelinjection nozzle 415 that is used for second group of 408 fuel injector 10 controllably links to each other with the second fuel signal menifold 458 of second Fuelinjection nozzle 416 with the secondary signal pipeline 478 of second group of 408 fuel injector 10.Petrolift 441 links to each other with fuel metering valve 437 with the fuel supply relation, and this fuel metering valve 437 links to each other with fuel supply menifold 409 with the fuel supply relation.Fuel metering valve 437 among this embodiment is arranged in the fuel-control unit 421, and by fuel-control unit 421 controls.This fuel-control unit 421 also comprises and is controlling valve bypass valve 445 in the pump bypass road 439, and this pump bypass road 439 is to lead to pump bypass road inlet 440 and petrolift 441 from pump discharge 443.The first signal fuel return line 347 and secondary signal fuel return line 348 return on inlet 442 and the petrolift 441 from the fuel signal that the first fuel signal menifold 456 and the second fuel signal menifold 458 lead to petrolift 441 respectively.The first return line hole 349 and the second return line hole 350 are separately positioned in the first signal fuel return line 347 and the secondary signal fuel return line 348.
Also comprise the first differential pressure measurement device 468 at Fig. 3 and system 8 shown in Figure 4, this device is used for detecting first signal pressure 472 in first signal line 464 and the first pressure reduction DCPFN1 between the fuel-supplying pressure 427 in the fuel feed line 431.The second differential pressure measurement device 470 is used for detecting secondary signal pressure 474 in the secondary signal circuit 478 and the second pressure reduction DCPFN2 between the fuel-supplying pressure 427 in the fuel feed line 431.Controlling first pressure regulator 492 and second pressure regulator 494 respectively with the fuel nozzle controller 423 of 470 one-tenth feedback signal relations of the first differential pressure measurement device 468 and the second differential pressure measurement device, and these pressure regulators and controllably combination of fuel nozzle controller 423.Pressure by first signal line 464 and secondary signal circuit 478 is controlled and adjusted to fuel nozzle controller 423 by controlling first pressure regulator 492 and second pressure regulator 494, therefore the pressure of fuel nozzle valve is sent in control, thereby makes it to open and close.When the pressure in the signal pipeline 433 equals or exceeds first when opening pressure 419, state is opened and stayed open to the first fuel nozzle valve 415.When the pressure in the signal pipeline 433 equals or exceeds second when opening pressure 420, state is opened and stayed open to the second fuel nozzle valve 416.System 8 shown in Figure 4 comprises third level fuel injection pipe road 460, and this injection line has the 3rd fuel injection point 462 in fuel injector 10.Have the 3rd the 3rd fuel nozzle valve 480 of opening pressure 482 and be arranged in third level fuel injection pipe road 460.System can have three grades of fuel injection pipe roads 460 of surpassing and have three grades of fuel injection point 462 of surpassing in fuel injector 10.
Shown in Figure 5 is an one exemplary embodiment of burner 15, and this burner comprises that is defined in a combustion zone 18 annular, between radially outer lining 20 and the inner radial lining 22 respectively.Outer liner 20 and inner liner 22 are positioned at the inner radial of an annular burner housing 26, and this burner shell circumferentially extends round outer liner 20 and inner liner 22.Burner 15 also comprises the ring cover 34 that is arranged on outer liner 20 and inner liner 22 upstreams.This lid 34 has defined the upstream extremity 36 of combustion zone 18, and some mixer apparatus 40 (only showing among the figure) along the circumferential direction are provided with round lid 34.Each mixer apparatus 40 is being supported the pilot burner 58 and the main nozzle 59 of a fuel injector 10 respectively.Mixer apparatus 40 with pilot burner and main nozzle transfer the fuel and AIR MIXTURES in combustion zone 18.Each mixer apparatus 40 has nozzle-axis 52, and pilot burner 58 and main nozzle 59 are around this axis is positioned at it.
Exemplary fuel injection device 10 as shown in Figure 5, it has three fuel valve seats 19, this seat design becomes to be used to hold the first fuel nozzle valve, 415, the second fuel nozzle valves 416 and the 3rd fuel nozzle valve 480, and these three fuel nozzle valves are positioned at the valve pocket 43 of fuel injector 10.First, second and third level fuel injection pipe road 411,412,460 more specifically is can be respectively as Fig. 5, pilot fuel line that is used for pilot burner 58 288 shown in Fig. 6 and Fig. 7 and first and second fuel conduits 280 and 282 that are used for the main nozzle 59 of fuel injector 10.First, the second and the 3rd fuel nozzle valve 415,416 and 480 (not shown in Fig. 5-7) controllably supplies the fuel to respectively pilot fuel line 288, main nozzle first fuel conduit 280 and main nozzle second fuel conduit 282 from single fuel supply menifold 409.First fuel injection point 413 on first order fuel injection pipe road 411 is the top spray orifice 55 in the fuel injector tip 57 of the pilot burner 58 in fuel injector 10.The second and the 3rd fuel injection point 414 and 462 is the spray orifice 106 in main nozzle first and second fuel conduits 280 and 282 in the main nozzle 59 of fuel injector 10.
What Figure 13-16 represented is the schematic representation of three grades of gas turbine fuel supply systems 8 of two valves.The first and second fuel nozzle valves 415 and 416 are used for controllably supplying the fuel to respectively in the spray orifice 106 in the main nozzle 59 of top spray orifice 55 in the fuel injector tip 57 of pilot burner 58 and fuel injector 10.The second fuel nozzle valve 416 comprises main fuel inlet 502 and the auxiliary inlet 500 that ignites, and wherein the main fuel inlet links to each other with main fuel outlet 506 with the fuel supply relation, and the auxiliary inlet that ignites links to each other with the auxiliary outlet 504 of igniting with the fuel supply relation.What second coil 508 slided is arranged in the second fuel nozzle valve 416, and comprises top peripheral channel 509 and bottom peripheral channel 511 round second coil 508.
Single fuel supply menifold 409 links to each other with the auxiliary inlet 500 that ignites with main fuel inlet 502 with the fuel supply relation.Main fuel inlet 502 links to each other with main fuel outlet 506 by the bottom peripheral channel 511 round second coil 508 with the fuel supply relation.Auxiliary fuel inlet 500 links to each other with auxiliary fuel outlet 504 by the top peripheral channel 509 round second coil 508 with the fuel supply relation.The auxiliary inlet 500 that ignites provides the function (pilot cutback) of igniting and reducing on second valve 416, thereby has reduced to the fuel flow rate of first valve and the fuel flow rate that arrives pilot burner 58 subsequently.Second coil 508 is by second spring, 507 bias voltages, and generation is moved under the effect of the pressure reduction DCPFN between the fuel-supplying pressure 427 in signal pressure in signal pipeline 433 417 and the fuel feed line 431.
Figure 13 represents is the first and second fuel nozzle valves 415 and 416 all in the closed position, and this is because signal pressure 417 in the signal pipeline 433 and the pressure reduction DCPFN between the fuel-supplying pressure 427 in the fuel feed line 431 are 0.Return port in the signal line 433 between the first fuel nozzle valve 415 and fuel signal manifold 16 (cutback orifice) 524 can prevent impact or the vibration of undesirable high pressure in signal line 433 and the fuel signal manifold 16.Second coil 508 in the second fuel nozzle valve 416 stops flow through main fuel inlet 502 and flowing on the main nozzle 59 of fuel.First coil 514 in the first fuel nozzle valve 415 stops flow through pilot fuel inlet 510 and flowing on the pilot burner 58 of fuel.
Figure 14 represents the first and second fuel nozzle valves 415 and 416, and it is set to not have main fuel spray nozzle fuel inflow main nozzle 59 and flows in pilot burner 58 with relative high or sufficient pilot fuel.Thereby being arranged in the second fuel nozzle valve 416, second coil 508 can stop flow through main fuel inlet 502 and flowing on the main nozzle 59 of fuel.This position of second coil 508 allows fuel by the auxiliary inlet 500 and round the peripheral channel 509 of second coil 508 of igniting, and flows in auxiliary ignite outlet 504 and the pilot jet 58 again.First coil 514 in the first fuel nozzle valve 415 is set to allow fuel directly to flow into the pilot burner 58 from the auxiliary outlet 504 of igniting from single fuel signal pipe 16 and by auxiliary fuel inlet 510 by return port 524.This operating mode or stage make flow through pilot burner 58 and do not have the fuel main nozzle 59 of flowing through of sufficient fuel.
Figure 15 represents the first and second fuel nozzle valves 415 and 416, and it is set to flow in the pilot burner 58 with relative high pilot fuel in the sufficient main nozzle fuel inflow main nozzle 59.Second coil 508 is arranged in the second fuel nozzle valve 416, thereby can allow the fuel main fuel inlet 502 of flowing through to flow into again in the main nozzle 59, and, flow in auxiliary ignite outlet 504 and the pilot burner 58 by peripheral channel 509 again round second coil 508 by the auxiliary inlet 500 that ignites.First coil 514 in the first fuel nozzle valve 415 is set to allow fuel directly to flow into the pilot burner 58 from auxiliary pilot fuel outlet 504 from single fuel signal pipe 16 and by auxiliary pilot fuel inlet 510 by return port 524.This operating mode or stage make the sufficient fuel pilot burner 58 of flowing through, and the sufficient fuel main nozzle 59 of also flowing through.
Figure 16 represents the first and second fuel nozzle valves 415 and 416, and it is set to flow into pilot burner 58 with relative pilot fuel low or part in the sufficient main nozzle fuel inflow main nozzle 59.This pattern is also referred to as the minimizing pattern of igniting.Thereby second coil 511 is arranged in the second fuel nozzle valve 416 and allows fuel by main fuel inlet 502 and flow in the main nozzle 59.The position of second coil 511 in the second fuel nozzle valve 416 also can stop fuel to flow in the auxiliary outlet 504 of igniting by the auxiliary inlet 500 that ignites and finally flow to pilot burner 58.The position of first coil 515 in the first fuel nozzle valve 415 can allow fuel directly to flow to pilot burner 58 from single fuel signal pipe 16 and by auxiliary fuel inlet 510 by return port 524.Therefore, pilot burner 58 can not reach that 8 of systems are getable may the most sufficient fuel flow rate.
The one exemplary embodiment of fuel injector 10 as shown in Figure 5 and Figure 6, it has fuel nozzle assembly 12 (may adopt and surpass one the nozzle assembly that radially separates), this fuel nozzle assembly comprises pilot burner 58 and main nozzle 59, and they can import to fuel in the combustion zone of gas-turbine combustion chamber respectively.Fuel injector 10 comprises a nozzle bearing or flange 30, and nozzle bearing or flange are applicable to fixing and are sealed to burner shell 26.Hollow stem 32 and flange 30 are in aggregates or be fixed to (for example by soldering or welding) on the flange, and are supporting fuel nozzle device 12 and mixer apparatus 40.
As Fig. 6 and shown in Figure 8, hollow stem 32 has intake assembly 41, and this intake assembly is arranged on the top or the inside of the open upper end of chamber 39, and in aggregates or be fixed on the flange 30 in the mode such as soldering with flange.Intake assembly 41 is parts of valve pocket 43, and hollow stem 32 hangs from above on valve pocket.Valve pocket 43 comprises single fuel signal connector 484, and this connector is used to connect single supply of fuel pipeline 409 and the first, the second and the 3rd fuel nozzle valve 415,416 and 480.As Fig. 2 and shown in Figure 11, valve pocket 43 also comprises single supply of fuel connector 486, and this connector is used to connect single fuel signal manifold 16 and the first, the second, the 3rd fuel nozzle valve 415,416 and 480.
As Fig. 9 and shown in Figure 10, supply with 62 and have first and second dull and stereotyped 76 and 78 of a pair of that combine and longitudinal extension.In first and second dull and stereotyped 76 and 78 each has that a row 80 is spaced laterally apart and the parallel slot 84 of longitudinal extension.Flat board combines and makes relative groove 84 alignment in each flat board, thus can form from a supply with 62 entry ends 66 to outlet end 69 and by supply with 62 inner fuel circulation passage 90.Also show as Fig. 6 and Fig. 7, pilot burner extension 54 extends back from main nozzle 59, and links to each other with the fuel injector tip 57 fluid ground of pilot burner 58 by the supplying pipe 56 that ignites.Fuel injector tip 57 has top spray orifice 55, and this spray orifice is the fuel injection point of pilot fuel line 288.Pilot fuel line 288, main nozzle first fuel conduit 280 and main nozzle second fuel conduit 282 are by forming with 62 inner fuel circulation passage 90 by supply.As shown in Figure 6 and Figure 7, supply is with 62 to supply the fuel in main nozzle 59 and the pilot burner 58.
As shown in Figure 6, supply has a straight substantially and intermediate portion 64 that radially extend with 62, and this intermediate portion is between entry end 66 and outlet end 69.Straight collector 104 horizontal expansions of fuel injector pipeline 60 (with axial backward direction), and away from the outlet end 69 of intermediate portion 64 and lead to the main nozzle 59 of an annular, this main nozzle is fixed, thereby has prevented that it is shifted.Entry end 66 is fixed on the inside of valve pocket 43.Top cover 104 is parallel with nozzle-axis 52 usually and lead to main nozzle 59.As shown in Figure 9, supply with 62 for stretch and be essentially plane shape, and have the first and second fully parallel sides 70 and 71 and rectangular cross-sectional shape 74.
As Fig. 6 and shown in Figure 12, fluidly communicate with 47 fluids with first and second fuel inlets 46 respectively with the inlet 63 at 62 entry end 66 places or fluid ground links to each other in supply, in intake assembly 41, directly import fuel in main nozzle pipeline 102 and pilot fuel line 288.Inlet supplies the fuel in the pilot burner 58 and main nozzle 59 in the spray nozzle device 12 with a plurality of inner fuel circulation passages 90 in 62 by supply, also provides cooling line to be used for the heat control of nozzle assembly simultaneously.As Figure 11 and shown in Figure 12, the top cover 104 of spray nozzle device 12 is with 62 from supply and is received fuel and transmission fuel in main nozzle 59, and in the junction, by main nozzle fuel conduit 102 transfer the fuels in pilot burner 58.
Shown in Fig. 5,6 and 12, supply with 62, main nozzle 59 and therebetween collector 104 integrally made by first and second dull and stereotyped 76 and 78 of longitudinal extension.Main nozzle 59 and collector 104 can be considered to supply with the element with 62.The fuel flow channel 90 of main nozzle fuel conduit 102 extend through supply be with 62, collector 104 and main nozzle 59.The fuel channel 90 of main nozzle fuel conduit 102 leads in the spray orifice 106 and the extension 54 by pilot burner supplies fuel in the pilot burner 58, wherein the pilot burner extension is connected on the supply pipeline 56 that ignites, as shown in Figures 9 and 10 with being in operation fluid.Parallel groove 84 in the fuel flow channel 90 of main nozzle fuel feed line 102 is etched in first and second dull and stereotyped 76 and 78 adjacently situated surfaces 210.
Shown in Fig. 9-12, in main nozzle 59, the annular arm (legs) 284 and 286 that each in first and second fuel conduits 280 and 282 of main nozzle all comprises respectively clockwise and the inverse time needle ring extends.Spray orifice 106 pass first and second dull and stereotyped 76 and 78 one or two and extend from annular arm 284 and 286.Spray orifice 106 extends radially outwardly by first flat board 76 of main nozzle 59, and main nozzle is at first and second dull and stereotyped 76 and 78 one of them the radially outers.Have parallel first Wavelet piece (wave) 290 and second Wavelet piece 292 respectively with the annular arm 284 and 286 that the inverse time needle ring extends clockwise.Spray orifice 106 alternately is arranged on first and second Wavelet pieces 290 and 292 one, so that arrange along circle 300 general toroidal ground.The first and second fuel nozzle valves 415 and 416 controlling in first and second fuel conduits 280 and 282 of the main nozzle in main nozzle 59 clockwise and the annular arm 284 of inverse time needle ring extension and 286 fuel supply.Therefore, when being arranged in first and second Wavelet pieces 290 and 292 another spray orifice 106 burner oils, can close the spray orifice 106 that is arranged in first and second Wavelet pieces 290 and 292 1, thereby the spray orifice 106 that makes the spray orifice 106 around the circle 300 that is positioned at another Wavelet piece or be positioned at two Wavelet pieces is supplied with alternately and is used for burnt fuel.Main nozzle fuel conduit 102 also comprises the pilot fuel line 288 of annular, and this pipeline fueling is given pilot burner extension 54.Annular pilot fuel line 288 be included in respectively in the main nozzle 59 clockwise and the annular of inverse time needle ring extension ignite arm 294 and 296.U.S. Patent No. 6,321 provides the spray nozzle device between adhesive plate and the information of fuel conduit in 541.
Shown in Figure 11 and 12, the inner fuel circulation passage 90 that extends downwards with 62 length along supply is used for supplying the fuel to main nozzle fuel conduit 102.Enter supply with 62 and top cover 104 in each inner fuel circulation passage 90 and flow into pilot burner 58 and main nozzle 59 in fuel by the first, the second and the 3rd fuel nozzle valve 415,416 and 480 controls.The top cover 104 of spray nozzle device 12 is with from supply and is received fuel 62, and transmits fuel in main nozzle 59.Main nozzle 59 for annular and have drum or a structure.
As Fig. 9 and shown in Figure 10, the flow channel of the injection apparatus in dull and stereotyped 76 and 78, opening and various assembly can be formed by the mode of any appropriate, etching for example, more specifically, the chemical erosion method.The chemical erosion method of this flat board is known to those skilled in the art, and for example in U.S. Patent No. 5,435, also is described in 884.That dull and stereotyped etching can form is very fine, sharp outline and complicated opening and passage, so just can allow in the small cross section of these parts of maintenance, supply be with 62 and main nozzle 59 in many fuel conduits are provided.Flat board 76 combines with 78 cohesive process with the face-to-face mode that contacts and employing such as soldering or diffusion bonding.These cohesive process are known to those skilled in the art, and a connection as safe as a house is provided between different flat boards.Diffusion bonding is effective especially, because it has caused border crossover (atom exchange) between adjacent layer.
As Fig. 5 and shown in Figure 7, each mixer assembly 40 comprises the mixer 142 that ignites, main mixer 144 and a centerbody 143 that extends between the two at ignite mixer and main mixer.Centerbody 143 has defined chamber 150, and this chamber fluidly links to each other with the mixer 142 that ignites and is positioned at its downstream.Pilot burner 58 is supported by the centerbody 143 of 150 inside in the chamber.Pilot burner 58 design is used for fuel droplet from the downstream injection to the chamber in 150.Main mixer 144 comprises the main shaft that is positioned at main radially swirler 182 upstreams to swirler 180, and this main radially swirler 182 is positioned at the upstream position from spray orifice 106.The mixer 142 that ignites comprises the swirler 160 that ignites of a pair of concentric setting.The swirler 160 that ignites is illustrated as axial swirler and comprises inside swirler 162 and the outside swirler 164 that ignites that ignites.Inside ignite swirler 162 be the annular and circumferentially be arranged on pilot burner 58 around.Ignite swirler 162 and the outside swirler 164 that ignites of each inside comprises many inside swirler blade 166 and the outside swirler blade 168 that ignites that ignites respectively, and these blades are arranged on the upstream position of pilot burner 58.
More specifically be as shown in Figure 7, the annular shunt 170 that ignites radially is arranged on inside and outside igniting between swirler 162 and 164, and extends downstream from the inside and outside swirler 162 and 164 that ignites.Shunt 170 design of igniting is used for making inside the ignite air-flow of swirler 164 of ignite combined air flow 154 and the outside of flowing through of swirler 162 that ignites of flowing through to be separated.Shunt 170 has the inner surface 174 of convergent-divergent shape, and this inner surface provides the fuel film surface when the motor low-power.Shunt 170 has also reduced the axial velocity of the mixer air-flow 154 that ignites of mixer 142 of igniting of flowing through, thereby can allow the recirculation of hot combustion gas.The inside swirler blade 166 that ignites is configured such that air flows produces vortex betwixt, and it is consistent with the ignite airflow direction of swirler blade 168 of the outside of flowing through, perhaps flow with first circumferencial direction, this direction makes second circumferencial direction of the mobile betwixt generation vortex of air opposite with the outside swirler blade 168 that ignites.
More specifically be as shown in Figure 5, main mixer 144 comprises the main nozzle shell 190 of annular, and this main nozzle shell has defined toroidal cavity 192.The mixer of main mixer 144 for radially becoming a mandarin, the alignment that it is concentric with respect to the mixer 142 of igniting, and around the mixer 142 that ignites, along the circumferential direction extend.Main mixer 144 produces the main mixer air-flow 156 of vortex along nozzle housing 190.Annular main nozzle 59 is arranged on along circumferencial direction and ignites between mixer 142 and the main mixer 144.More specifically be that main nozzle 59 extends along circumferential direction around the mixer 142 that ignites, and the inside of the annular chamber 192 of outside that is positioned at centerbody 143 radially and nozzle housing 190.
More specifically be as shown in Figure 7, nozzle housing 190 comprises injection wellhole 220, is ejected into the main mixer air-flow 156 by the spray orifice 106 of this injection wellhole fuel from main nozzle 59.Between the inside and outside heat shield 194 and 196 of the annular radial main nozzle that is arranged on nozzle housing 190 59 and outside annular nozzle wall 172 radially.Inside and outside heat shield 194 and 196 comprises inner radial wall 202 and outer wall 204 respectively, and the annular space 200 of 360 degree is arranged betwixt.Inside and outside heat shield 194 and 196 each all comprise some and spray orifice 106 and spray the openings 206 that wellhole 220 is alignd.Inside and outside heat shield 194 and 196 suitable manner with for example welding or soldering are fixed on the hollow stem 32.
Referring on June 4th, 2002 application, title is the U.S. Patent application No.10/161 of " the lamination type fuel tape of fuel injector ", 911; On April 24th, 2003 applied for, title is the U.S. Patent application 10/422,265 of " pressure reduction with asymmetric cyclone separator is induced the purge fuel sparger ".And on January 31st, 2003 application, title is the U.S. Patent application No.10/356 of " the purge fuel sparger that is cooled ", 009, apply for the spray nozzle device between bonding flat board and the background information of fuel conduit a bit.
As described herein is preferred and one exemplary embodiment of the present invention; other that draws from instruction of the present invention revise for those skilled in the art be conspicuous; therefore, claimed in the appended claims these all modifications all drop within true spirit of the present invention and the scope.Therefore, the present invention who defines and distinguish in the claimed content of the U. S. Patent claim below.
Claims (10)
1. fuel injector (10), it comprises:
Valve pocket (43),
Hang on the hollow stem (32) on the described valve pocket (43),
The fuel nozzle assembly (12) that at least one is supported by described bar,
At least the first and second grades of fuel injection pipe roads (411 and 412) in fuel injector (10),
Each of described first and second grades of fuel injection pipe roads (411 and 412) all has first and second fuel injection point (413 and 414),
At least the first and second fuel nozzle valves (415 and 416) that controllably link to each other with described first and second grades of fuel injection pipe roads (411 and 412) respectively,
The described first and second fuel nozzle valves (415 and 416) can be respectively opened under the pressure (419 and 420) operation different first and second and are opened,
Described valve pocket (43) comprises single fuel supply connector (484) and single fuel signal connector (486), described fuel supply connector (484) links to each other with the described first and second fuel nozzle valves (415 and 416) with the fuel supply relation, and described fuel signal connector (486) links to each other with the described first and second fuel nozzle valves (415 and 416) with the pressure feed relation.
2. fuel injector as claimed in claim 1 (10) also comprises: first fuel injection point (413) of described first order fuel injector pipeline (411) is the top spray orifice (55) on the fuel injector top (57) of the pilot burner (58) of described fuel injector (10), and second fuel injection point (414) on fuel injection pipe road, the described second level (412) is arranged in the main nozzle (59) of each fuel injector (10).
3. fuel injector as claimed in claim 2 (10), wherein said main nozzle (50) are for annular and have and be positioned at the spray orifice (106) that radially extends that fuel injection pipe road, the second level (412) locates.
4. fuel injector as claimed in claim 3 (10) also comprises:
Extend through the inner fuel circulation passage (90) on first and second grades of fuel injection pipe roads (411 and 412) of described annular main nozzle (59),
Circumferentially from the described inner fuel circulation passage (90) that passes described main nozzle (59) at least first extend clockwise and the ring-type leg (284 and 286) that extends counterclockwise, and
First spray site (413) on described first order fuel injection pipe road (411) is positioned at the spray orifice (106) that extends through at least one flat board (76 and 78) from annular leg.
5. fuel injector as claimed in claim 4 (10), wherein said annular arm (284 and 286) has the first and second parallel ripples (290 and 292), and described spray orifice (106) alternately is arranged on of first and second Wavelet pieces (290 and 292), so that come into line along circle (300) basically.
6. fuel injector as claimed in claim 2 (10) also comprises:
Described first and second grades of fuel injection pipe roads (411 and 412) extend through fuel injector pipeline (60) at least in part,
Described fuel injection pipe road (60) extends through described bar (32) to described nozzle assembly (12) between valve pocket (43),
Described fuel injection pipe road (60) also comprises at least one supply band (62), and this supplies with band and has at least one pair of lengthwise that combines extension flat board (76 and 78),
Each flat board has parallel groove (84) spaced and that extend in the longitudinal direction, and
Described flat board combines and makes that relative groove (84) aligns in each flat board, thereby forms from entry end (66) to outlet end (69) the inner fuel circulation passage (90) by described first and second grades of fuel injection pipe roads (411 and 412) of described supply band (62) length.
7. fuel injector as claimed in claim 6 (10) also comprises:
Described inner fuel circulation passage (90) extends through described supply band (62) and described annular main nozzle (59),
Circumferentially first the clockwise and counterclockwise annular of extending at least from the described inner fuel passage (90) that passes described main nozzle (59) extend arm (284 and 286) and
First spray site (413) on described first order fuel injection pipe road (411) is arranged at least one the spray orifice (106) that extends through flat board (76 and 78) from described annular arm.
8. fuel injector (10), it comprises:
Valve pocket (43),
Hang on the hollow stem (32) of described valve pocket (43),
The fuel nozzle assembly (12) that at least one is supported by described bar,
First, second, third grade of fuel injection pipe road (411,412 and 460) in fuel injector (10),
Described first, second, third grade of fuel injection pipe road (411,412 and 460) to small part extends through fuel injector pipeline (60),
Described fuel injection pipe road (60) extends through described bar (32) to described nozzle assembly (12) between described valve pocket (43),
Each of described first, second, third grade of fuel injection pipe road (411,412 and 460) has first, second, third fuel injection point (413,414 and 462),
First, second controllably links to each other with third level fuel injection pipe road (411,412 and 460) with first, second respectively with the 3rd fuel nozzle valve (415,416 and 480),
Described first, second can be respectively opened to operate pressure (419,420 and 482) under at different first, second and the 3rd with the 3rd fuel nozzle valve (415,416 and 480) and opened,
Described valve pocket (43) comprises single fuel supply connector (484) and single fuel signal connector (486), described fuel supply connector (484) links to each other with the described first and second fuel nozzle valves (415 and 416) with the fuel supply relation, described fuel signal connector (486) links to each other with the first and second fuel nozzle valves (415 and 416) with the pressure feed relation
Described fuel injection pipe road (60) comprises single supply band (62), and this supplies with band and has flat board (the 76 and 78) veneer that a lengthwise that combines extends,
Each flat board has the parallel slot (84) that is spaced laterally apart and extends at length direction,
Flat board combines and makes that relative groove (84) aligns in each flat board, the inner fuel circulation passage (90) on formation first, second and third level fuel injection pipe road (411,412 and 460) by supplying with strip length from entry end (66) to outlet end (69).
9. fuel injector as claimed in claim 8 (10) also comprises:
First order fuel injection pipe road (411), it is the pilot fuel line (288) that is arranged in annular main nozzle (59),
Fuel injection pipe road, the second level (412), it is main nozzle first fuel conduit (280) that is arranged in annular main nozzle (59),
Third level fuel injection pipe road (460), it is for being arranged in main nozzle second fuel conduit (282) of annular main nozzle (59).
10. fuel injector as claimed in claim 9 (10) also comprises: first fuel injection point (413) on first order fuel injection pipe road (411) is the top spray orifice (55) at fuel injector top (57) of the pilot burner (58) that is positioned at fuel injector (10)
The second and the 3rd fuel injection point (414 and 462) is respectively the spray orifice (106) of main nozzle first and second fuel conduits (280 and 282) of the main nozzle (59) that is arranged in fuel injector (10).
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/801439 | 2004-03-15 | ||
| US10/801,439 US7036302B2 (en) | 2004-03-15 | 2004-03-15 | Controlled pressure fuel nozzle system |
| US10/814488 | 2004-03-31 | ||
| US10/814,488 US6955040B1 (en) | 2004-03-31 | 2004-03-31 | Controlled pressure fuel nozzle injector |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1676902A true CN1676902A (en) | 2005-10-05 |
| CN1676902B CN1676902B (en) | 2010-11-17 |
Family
ID=34915797
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200510054199 Active CN1676902B (en) | 2004-03-15 | 2005-01-15 | Controlled pressure fuel nozzle system |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN1676902B (en) |
| FR (1) | FR2867552B1 (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7716931B2 (en) | 2006-03-01 | 2010-05-18 | General Electric Company | Method and apparatus for assembling gas turbine engine |
| CN101852158A (en) * | 2009-03-31 | 2010-10-06 | 株式会社电装 | Connector |
| CN1670348B (en) * | 2004-03-15 | 2010-12-08 | 通用电气公司 | Controlled pressure fuel nozzle system |
| CN103925084A (en) * | 2013-01-15 | 2014-07-16 | 通用电气公司 | Methods And Systems For Operating Gas Turbine Engines |
| CN105318922A (en) * | 2014-07-11 | 2016-02-10 | 阿尔斯通技术有限公司 | Method for measuring the mass flow of a stream of a gaseous medium and fuel supply system |
| CN105723155A (en) * | 2013-11-13 | 2016-06-29 | 西门子股份公司 | Fuel injection system for a turbine engine |
| CN109416181A (en) * | 2016-05-12 | 2019-03-01 | 西门子公司 | For reducing the selective combustion device control method of discharge |
| CN118088321A (en) * | 2024-04-18 | 2024-05-28 | 中国航发燃气轮机有限公司 | Gas turbine, fuel supply system and method thereof |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2913250B1 (en) * | 2007-03-02 | 2009-05-29 | Turbomeca Sa | METHOD FOR STARTING A GAS TURBINE HELICOPTER ENGINE, FUEL SUPPLY CIRCUIT FOR SUCH AN ENGINE, AND MOTOR HAVING SUCH A CIRCUIT |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4027473A (en) * | 1976-03-05 | 1977-06-07 | United Technologies Corporation | Fuel distribution valve |
| US5735117A (en) * | 1995-08-18 | 1998-04-07 | Fuel Systems Textron, Inc. | Staged fuel injection system with shuttle valve and fuel injector therefor |
| GB0023727D0 (en) * | 2000-09-27 | 2000-11-08 | Lucas Industries Ltd | Control system |
| US6718770B2 (en) * | 2002-06-04 | 2004-04-13 | General Electric Company | Fuel injector laminated fuel strip |
-
2005
- 2005-01-12 FR FR0500305A patent/FR2867552B1/en not_active Expired - Fee Related
- 2005-01-15 CN CN 200510054199 patent/CN1676902B/en active Active
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1670348B (en) * | 2004-03-15 | 2010-12-08 | 通用电气公司 | Controlled pressure fuel nozzle system |
| US7716931B2 (en) | 2006-03-01 | 2010-05-18 | General Electric Company | Method and apparatus for assembling gas turbine engine |
| CN101029739B (en) * | 2006-03-01 | 2011-11-30 | 通用电气公司 | Combustion chamber of gas turbine engine and the gas turbine engine |
| CN101852158A (en) * | 2009-03-31 | 2010-10-06 | 株式会社电装 | Connector |
| CN103925084A (en) * | 2013-01-15 | 2014-07-16 | 通用电气公司 | Methods And Systems For Operating Gas Turbine Engines |
| CN103925084B (en) * | 2013-01-15 | 2017-04-12 | 通用电气公司 | Methods And Systems For Operating Gas Turbine Engines |
| CN105723155A (en) * | 2013-11-13 | 2016-06-29 | 西门子股份公司 | Fuel injection system for a turbine engine |
| CN105318922A (en) * | 2014-07-11 | 2016-02-10 | 阿尔斯通技术有限公司 | Method for measuring the mass flow of a stream of a gaseous medium and fuel supply system |
| CN109416181A (en) * | 2016-05-12 | 2019-03-01 | 西门子公司 | For reducing the selective combustion device control method of discharge |
| US11067279B2 (en) | 2016-05-12 | 2021-07-20 | Siemens Energy Global GmbH & Co. KG | Method of selective combustor control for reduced emissions |
| CN118088321A (en) * | 2024-04-18 | 2024-05-28 | 中国航发燃气轮机有限公司 | Gas turbine, fuel supply system and method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2867552B1 (en) | 2008-07-11 |
| CN1676902B (en) | 2010-11-17 |
| FR2867552A1 (en) | 2005-09-16 |
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