CN110529879B - Two-phase fuel nozzle - Google Patents
Two-phase fuel nozzle Download PDFInfo
- Publication number
- CN110529879B CN110529879B CN201910698400.7A CN201910698400A CN110529879B CN 110529879 B CN110529879 B CN 110529879B CN 201910698400 A CN201910698400 A CN 201910698400A CN 110529879 B CN110529879 B CN 110529879B
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- sealing
- gas
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- 239000000446 fuel Substances 0.000 title claims abstract description 253
- 239000007788 liquid Substances 0.000 claims abstract description 135
- 238000007789 sealing Methods 0.000 claims abstract description 127
- 238000002347 injection Methods 0.000 claims abstract description 13
- 239000007924 injection Substances 0.000 claims abstract description 13
- 238000003466 welding Methods 0.000 claims description 52
- 238000000889 atomisation Methods 0.000 claims description 15
- 238000002485 combustion reaction Methods 0.000 claims description 14
- 230000009977 dual effect Effects 0.000 claims description 10
- 238000009434 installation Methods 0.000 claims description 8
- 230000007704 transition Effects 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 57
- 230000009471 action Effects 0.000 description 9
- 239000000295 fuel oil Substances 0.000 description 9
- 239000003921 oil Substances 0.000 description 8
- 238000004519 manufacturing process Methods 0.000 description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 239000000571 coke Substances 0.000 description 2
- 238000004939 coking Methods 0.000 description 2
- 238000005336 cracking Methods 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000003345 natural gas Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Images
Classifications
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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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
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
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- 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)
Abstract
The invention discloses a two-phase fuel nozzle, comprising: the nozzle comprises a nozzle body, wherein a liquid fuel flow passage, an auxiliary air flow passage and a gas fuel flow passage are arranged in the nozzle body, the liquid fuel flow passage, the auxiliary air flow passage and the gas fuel flow passage are sequentially arranged from inside to outside in a concentric circle mode, the inflow ends of the auxiliary air flow passage and the gas fuel flow passage are respectively communicated with the outer side wall of the nozzle body, the inflow end of the liquid fuel flow passage is connected with a gas-liquid sealing component, and the inflow end of the liquid fuel flow passage is communicated with the end face of the inflow end of the nozzle body through the gas-liquid sealing component. The nozzle comprises a nozzle body, a liquid fuel channel is arranged in the nozzle body, a fuel atomizer and an air swirler are arranged in the injection end of the nozzle body, the fuel atomizer is communicated with the outflow end of the liquid fuel channel, the air swirler is communicated with the outflow end of the auxiliary air channel, so that auxiliary atomized air forms a rotational flow in the air swirler to further atomize liquid fuel sprayed by the fuel atomizer, and the end face of the injection end of the nozzle body is communicated with the outflow end of the gas fuel channel.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a two-phase fuel nozzle.
Background
The existing gas turbine, especially the aeroderivative gas turbine improved by aeroengine, mainly uses natural gas and fuel oil as the using medium, i.e. one fuel nozzle can respectively inject natural gas and fuel oil into the combustion chamber of the gas turbine, and at the same time, the fuel nozzle is also provided with an auxiliary atomizing air loop for supplying auxiliary atomizing air to carry out auxiliary atomization on the fuel oil.
Because the temperature of the fuel is generally about 20 ℃, and the temperature of the auxiliary atomized air from the air compressor is about 300 ℃, the sealing between two flow paths with large temperature difference is particularly difficult, and if no good sealing is realized, the problems that the fuel is cracked and coked under the action of leaked high-temperature air and further an oil way is blocked due to the failure of a sealing ring are easy to occur; on the other hand, the gas-liquid dual-phase fuel nozzle is complex in structure and mainly formed by forging a blank or casting a blank, and is difficult to manufacture and high in manufacturing cost.
Disclosure of Invention
The invention provides a two-phase fuel nozzle, which aims to solve the technical problems that high-temperature air is easy to leak to cause cracking and coking of liquid fuel, so that an oil way is blocked, and the two-phase fuel nozzle is complex in structure and high in manufacturing cost.
The technical scheme adopted by the invention is as follows:
a dual phase fuel nozzle comprising: the nozzle body is used for being connected with the mounting case, a liquid fuel flow channel for guiding liquid fuel, an auxiliary air flow channel for guiding auxiliary atomized air and a gas fuel flow channel for guiding gas fuel are arranged in the nozzle body, the liquid fuel flow channel, the auxiliary air flow channel and the gas fuel flow channel are sequentially distributed from inside to outside in a concentric circle mode, the inflow ends of the auxiliary air flow channel and the gas fuel flow channel are respectively communicated with the outer side wall of the nozzle body, the inflow end of the liquid fuel flow channel is communicated with a gas-liquid sealing component for preventing the inflow end of the liquid fuel flow channel from being communicated with the auxiliary air flow channel, and the inflow end of the liquid fuel flow channel is communicated with the end face of the inflow end of the nozzle body through the gas-liquid sealing component; the nozzle comprises a nozzle body, a nozzle body and an auxiliary air flow channel, wherein a fuel atomizer and an air swirler are arranged in an injection end of the nozzle body, the fuel atomizer is communicated with an outflow end of the liquid fuel flow channel so as to atomize liquid fuel and then spray the liquid fuel into the air swirler, the air swirler is communicated with an outflow end of the auxiliary air flow channel so as to enable auxiliary atomized air to form a rotational flow between a nozzle of the fuel atomizer and a nozzle of the air swirler so as to further atomize the liquid fuel sprayed by the fuel atomizer, the further atomized liquid fuel is sprayed into a combustion chamber, and an end face of the injection end of the nozzle body is communicated with the outflow end of the gas fuel flow channel so as to enable the gas fuel.
Furthermore, the nozzle body comprises a core bar and a hollow cylindrical welding cylinder group, wherein the two ends of the core bar are communicated, and the core bar extends along the axial direction; the core bar is positioned in the shaft hole of the welding cylinder group, the inner channel of the core bar forms a liquid fuel flow channel, the first end of the core bar is tightly propped against the inner wall of the shaft hole at the first end of the welding cylinder group, and the second end of the core bar is recessed inwards to form a mounting cavity for mounting a fuel atomizer; an annular channel between the core bar and the shaft hole of the welding cylinder group forms an auxiliary air flow channel 201, a gas fuel flow channel annularly arranged outside the shaft hole of the welding cylinder group is also arranged in the welding cylinder group, and a flow inlet of the auxiliary air flow channel 201 and a flow inlet of the gas fuel flow channel are respectively arranged on the side wall of the welding cylinder group; the gas-liquid sealing member is positioned in the shaft hole of the welding cylinder group and connected with the first end of the core bar so as to seal a gap between the first end of the core bar and the inner wall of the shaft hole of the welding cylinder group and prevent the inflow end of the liquid fuel flow passage from being communicated with the inflow end of the auxiliary air flow passage.
Further, the gas-liquid sealing component comprises an oil-passing sealing screw, a first sealing piece, a second sealing piece and a third sealing piece, wherein the first sealing piece, the second sealing piece and the third sealing piece are used for sealing; the oil-through sealing screw is a hollow screw which is through along the axial direction, a screw rod of the oil-through sealing screw extends into the core rod from the inflow end of the liquid fuel flow passage, then is communicated with the liquid fuel flow passage and is in threaded connection with the inner wall of the core rod, and the screw head of the oil-through sealing screw is tightly propped against the inner wall of the shaft hole at the first end of the welding cylinder group; the first sealing element is arranged in the liquid fuel flow passage and positioned between the end surface of the screw rod and the inner step of the liquid fuel flow passage, so as to form radial sealing to prevent the liquid fuel in the liquid fuel flow passage from leaking from a gap between the screw rod and the liquid fuel flow passage; the second sealing element is arranged on the outer step at the end face of the first end of the core rod and is used for forming first axial seal so as to seal a gap between the outer wall of the first end of the core rod and the inner wall of the welding cylinder group; the third sealing element is arranged on an outer step at the inner end face of the screw head and used for forming second axial sealing to seal a gap between the outer wall of the screw head and the inner wall of the welding barrel group.
Further, the first sealing element and the second sealing element are both metal sealing rings with C-shaped sections; the third sealing element is an O-shaped sealing ring.
The gas-liquid sealing component further comprises a sealing bush for sealing, the sealing bush is arranged on the screw rod and tightly propped against the inner wall of the welding cylinder group, and the sealing bush is tightly clamped between the first end face of the core rod and the end face of the screw head; the outer wall of the sealing bush is provided with an inwards concave annular vent groove, and the welding cylinder group is provided with a communication hole for communicating the vent groove with the atmosphere, so that the atmosphere enters the vent groove and then the two sides of the first sealing element, the two sides of the second sealing element and the two sides of the third sealing element form pressure difference respectively.
Furthermore, the fuel atomizer comprises a hollow cylindrical atomizing chamber body, the atomizing chamber body and the core rod are coaxially arranged, the outer peripheral wall of the atomizing chamber body is convex to form an annular sealing convex ring, the first end of the atomizing chamber body extends into the installation cavity from the second end of the core rod, and the end face of the sealing convex ring is welded and fixed with the end face of the second end of the core rod to seal the installation cavity; a first through inflow hole is formed in the side wall of the first end of the atomizing chamber body, and the first inflow hole is used for enabling the liquid fuel in the mounting cavity to enter the atomizing chamber body and form a rotational flow for atomization; the shaft hole of the first end of the atomizing chamber body is fixedly welded with a sealing body used for sealing the first end of the atomizing chamber body, and the second end of the atomizing chamber body is connected with a first nozzle body used for spraying atomized liquid fuel into the air swirler.
Furthermore, the air swirler is in a hollow cylinder shape and is coaxially arranged with the fuel atomizer, the outer ring wall of the air swirler is convex to form an annular connecting convex ring, and the connecting convex ring is fixed with the inner wall surface of the end surface of the second end of the welding cylinder group; the jet end of the fuel atomizer axially extends into the air swirler, a through second inflow hole is formed in the side wall of the air swirler, and the second inflow hole is communicated with the outflow end of the auxiliary air flow channel, so that auxiliary atomized air enters the air swirler and forms a rotational flow to further atomize liquid fuel sprayed by the fuel atomizer.
Furthermore, the welding cylinder group comprises a nozzle cylinder component, an air equalizing cylinder and a nozzle cylinder which are sequentially arranged and connected along the axial direction, and the nozzle cylinder component, the air equalizing cylinder and the nozzle cylinder are hollow cylinders with two communicated ends; the shaft hole of the nozzle barrel part, the shaft hole of the air equalizing barrel and the shaft hole of the nozzle barrel are connected to form an auxiliary air flow passage, and the flow inlet of the auxiliary air flow passage is arranged on the side wall of the nozzle barrel; the gas fuel flow passage is simultaneously arranged in the nozzle barrel part, the gas homogenizing barrel and the nozzle barrel, and the flow inlet of the gas fuel flow passage is arranged on the side wall of the nozzle barrel; the air swirler is arranged in the shaft hole at the second end of the nozzle barrel piece.
Furthermore, the gas fuel flow passage comprises a flow inlet section arranged in the nozzle barrel, a transition section arranged in the gas homogenizing barrel and a flow outlet section arranged in the nozzle barrel; the gas homogenizing cylinder comprises an extending-in part, a first connecting disc part and a second connecting disc part which are sequentially arranged and connected, the extending-in part extends into a shaft hole of the nozzle cylinder part from the first end of the nozzle cylinder part, the end face of the first connecting disc part is abutted against the end face of the first end of the nozzle cylinder part and is welded and fixed, and the transition section penetrates through the first connecting disc part; the second end of the nozzle barrel is sleeved on the first connecting disc part and the second connecting disc part respectively and is welded and fixed with the outer wall of the first connecting disc part and the outer wall of the second connecting disc part respectively, the inlet of the flow inlet section is arranged on the outer wall of the nozzle barrel, and the outlet of the flow inlet section is arranged on the end face of the second end of the nozzle barrel.
Further, the nozzle barrel part comprises an inner barrel sleeved outside the core rod, an outer barrel sleeved outside the inner barrel and a second nozzle body; the extending part of the gas homogenizing cylinder extends into the inner cylinder from the first end of the inner cylinder, and the first connecting disc part of the gas homogenizing cylinder is fixedly welded with the outer cylinder; an annular flow passage between the outer cylinder and the inner cylinder forms an outflow section of the gas fuel flow passage; the second nozzle body is respectively connected with the second ends of the inner cylinder and the outer cylinder, and a gas nozzle communicated with the gas fuel channel is arranged on the second nozzle body for spraying the gas fuel outwards into the combustion chamber.
The invention has the following beneficial effects:
in the two-phase fuel nozzle, although the liquid fuel flow passage and the auxiliary air flow passage are arranged in a concentric circle, the inflow end of the liquid fuel flow passage is communicated with the gas-liquid sealing component which is used for preventing the inflow end of the liquid fuel flow passage from being communicated with the auxiliary air flow passage, so that high-temperature auxiliary atomized air in the auxiliary air flow passage supplied by the air compressor cannot leak into the liquid fuel flow passage, the liquid fuel in the liquid fuel flow passage cannot crack and coke under the action of high-temperature air, an oil passage is blocked, and the problem of isolation and sealing of the high-temperature air and low-temperature fuel oil in the fuel nozzle is solved; in the two-phase fuel nozzle, the liquid fuel flow passage, the auxiliary air flow passage and the gas fuel flow passage are sequentially distributed from inside to outside in concentric circles, so that the structure of the fuel nozzle can be integrated as much as possible, the geometric size of the fuel nozzle is reduced, the fuel nozzle is simple and compact in structure and reasonable in layout, the complexity of the product structure is reduced, the time for replacing and maintaining the fuel nozzle is saved, and the manufacturing cost is reduced; the auxiliary atomization air in the auxiliary air flow passage forms rotational flow in the air swirler under the action of the air swirler, and further atomizes the fuel oil sprayed by the fuel oil atomizer, so that the fuel oil can still obtain good liquid drop atomization effect under extremely low fuel flow (even close to the extremely low fuel flow), and the fuel nozzle can enable the liquid fuel flow passage to supply the fuel oil to a combustion chamber according to any low fuel proportion, so that seamless conversion of two fuels is carried out under the condition that the output of energy (electric energy and heat energy) of a gas turbine is not stopped, and the adaptability to the fuel environment is enhanced.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a cross-sectional front view structural schematic of a two-phase fuel nozzle of a preferred embodiment of the present invention;
fig. 2 is a schematic diagram of the right-side structure of fig. 1.
Description of the figures
10. A core bar; 101. a liquid fuel flow passage; 102. installing a cavity; 20. welding the cylinder group; 201. an auxiliary air flow channel; 202. a gaseous fuel flow path; 203. a communicating hole; 21. a nozzle cartridge; 211. an inner barrel; 212. an outer cylinder; 213. a second nozzle body; 2130. a gas nozzle; 22. a gas homogenizing cylinder; 23. a nozzle barrel; 30. a gas-liquid seal member; 31. oil is filled into the sealing screw; 32. a first seal member; 33. a second seal member; 34. a third seal member; 35. a seal bushing; 350. a vent channel; 40. a fuel atomizer; 41. an atomization chamber body; 410. a sealing convex ring; 411. a first intake aperture; 42. a seal body; 43. a first nozzle body; 50. an air swirler; 501. a second intake aperture.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
Referring to FIG. 1, a preferred embodiment of the present invention provides a dual phase fuel nozzle comprising: the nozzle body is used for being connected with an installation casing, a liquid fuel flow channel 101 used for guiding liquid fuel, an auxiliary air flow channel 201 used for guiding auxiliary atomizing air and a gas fuel flow channel 202 used for guiding gas fuel are arranged in the nozzle body, the liquid fuel flow channel 101, the auxiliary air flow channel 201 and the gas fuel flow channel 202 are sequentially arranged from inside to outside in a concentric circle mode, the inflow ends of the auxiliary air flow channel 201 and the gas fuel flow channel 202 are respectively communicated with the outer side wall of the nozzle body, the inflow end of the liquid fuel flow channel 101 is connected with a gas-liquid sealing component 30 used for preventing the inflow end of the liquid fuel flow channel 101 from being communicated with the auxiliary air flow channel 201, and the inflow end of the liquid fuel flow channel 101 is communicated with the end face of the inflow end of the nozzle body through the gas-liquid sealing component. The fuel atomizer 40 and the air swirler 50 are arranged in the injection end of the nozzle body, the fuel atomizer 40 is communicated with the outflow end of the liquid fuel channel 101 to atomize the liquid fuel and then inject the liquid fuel into the air swirler 50, the air swirler 50 is communicated with the outflow end of the auxiliary air channel 201 to enable the auxiliary atomized air to form a rotational flow between the nozzle of the fuel atomizer 40 and the nozzle of the air swirler 50 to further atomize the liquid fuel sprayed by the fuel atomizer 40 and spray the further atomized liquid fuel into the combustion chamber, and the end surface of the injection end of the nozzle body is communicated with the outflow end of the gas fuel channel 202 to enable the gas fuel to be sprayed into the combustion chamber.
When the two-phase fuel nozzle works, liquid fuel supplied by an external pipeline firstly enters the liquid fuel flow channel 101 from a flow inlet on the end face of the flow inlet end of the nozzle body, then enters the fuel atomizer 40 from the flow outlet end of the liquid fuel flow channel 101, and is atomized under the action of the fuel atomizer 40 and then is sprayed into the air swirler 50; meanwhile, the auxiliary atomization air supplied by the compressor firstly enters the auxiliary air runner 201 from the inlet on the side wall of the nozzle body, then enters the air swirler 50 from the outlet end of the auxiliary air runner 201, and forms a rotational flow under the action of the air swirler 50, so as to further atomize the liquid fuel sprayed out by the fuel atomizer 40 and then spray the liquid fuel into the combustion chamber; the gas fuel supplied by the external pipeline firstly enters the gas fuel flow passage 202 through the inlet on the side wall of the nozzle body and then is directly injected into the combustion chamber through the injection port on the end face of the injection end of the nozzle body.
In the two-phase fuel nozzle, although the liquid fuel runner 101 and the auxiliary air runner 201 are arranged in a concentric circle, the gas-liquid sealing component 30 is communicated with the inflow end of the liquid fuel runner 101, and the gas-liquid sealing component 30 is used for preventing the inflow end of the liquid fuel runner 101 from being communicated with the auxiliary air runner 201, so that high-temperature auxiliary atomized air in the auxiliary air runner 201 supplied by the air compressor cannot leak into the liquid fuel runner 101, the liquid fuel in the liquid fuel runner 101 cannot crack and coke under the action of high-temperature air, an oil path is blocked, and the problem of isolation and sealing of the high-temperature air and low-temperature fuel oil in the fuel nozzle is solved; in the two-phase fuel nozzle, the liquid fuel flow passage 101, the auxiliary air flow passage 201 and the gas fuel flow passage 202 are sequentially arranged from inside to outside in concentric circles, so that the structure of the fuel nozzle can be integrated as much as possible, the geometric size of the fuel nozzle is reduced, the fuel nozzle is simple and compact in structure and reasonable in layout, the complexity of the product structure is reduced, the time for replacing and maintaining the fuel nozzle is saved, and the manufacturing cost is reduced; and the auxiliary atomization air in the auxiliary air runner 201 forms a rotational flow in the air swirler 50 under the action of the air swirler 50, and further atomizes the fuel sprayed by the fuel atomizer 40, so that the fuel can still obtain good droplet atomization effect under the condition of extremely low fuel flow (even approaching to 0), therefore, the fuel nozzle of the invention can enable the liquid fuel runner 101 to supply the fuel to the combustion chamber according to any low fuel proportion, so as to perform seamless conversion of two fuels under the condition that the output of energy (electric energy and heat energy) of a gas turbine is not stopped, and enhance the adaptability to the fuel environment.
Alternatively, as shown in fig. 1, the nozzle body includes a core bar 10 having two ends connected and extending in the axial direction, and a welding cylinder group 20 sleeved outside the core bar 10 and having a hollow cylindrical shape. The core bar 10 is positioned in the shaft hole of the welding cylinder group 20, the inner channel of the core bar 10 forms a liquid fuel flow passage 101, the first end of the core bar 10 is tightly pressed against the inner wall of the shaft hole of the first end of the welding cylinder group 20 to prevent the inflow end of the liquid fuel flow passage 101 from being communicated with the auxiliary air flow passage 201, and the second end of the core bar 10 is recessed to form a mounting cavity 102 for mounting the fuel atomizer 40. An auxiliary air flow channel 201 is formed by an annular channel between the core bar 10 and the shaft hole of the welding cylinder group 20, a gas fuel flow channel 202 annularly arranged outside the shaft hole is further arranged in the welding cylinder group 20, and a flow inlet of the auxiliary air flow channel 201 and a flow inlet of the gas fuel flow channel 202 are respectively arranged on the side wall of the welding cylinder group 20. The gas-liquid sealing member 30 is located in the axial hole of the welding cartridge group 20 and connected to the first end of the core bar 10 to seal the gap between the first end of the core bar 10 and the inner wall of the axial hole of the welding cartridge group 20 and prevent the inflow end of the liquid fuel flow passage 101 from communicating with the inflow end of the auxiliary air flow passage 201.
In the alternative embodiment, as shown in fig. 2, the gas-liquid sealing member 30 includes an oil seal screw 31, and a first seal 32, a second seal 33, and a third seal 34 for sealing. The oil-passing sealing screw 31 is a hollow screw which is through along the axial direction, a screw rod of the oil-passing sealing screw 31 extends into the core bar 10 from the inflow end of the liquid fuel flow passage 101, then is communicated with the liquid fuel flow passage 101 and is in threaded connection with the inner wall of the core bar 10, and a screw head of the oil-passing sealing screw 31 is tightly propped against the inner wall of the shaft hole at the first end of the welding barrel group 20 so as to prevent the inflow end of the liquid fuel flow passage 101 from being communicated with the auxiliary air flow passage 201. The first seal 32 is provided in the liquid fuel flow passage 101 between an end surface of the screw and a step in the liquid fuel flow passage 101, and the first seal 32 is used to form a radial seal to prevent the liquid fuel in the liquid fuel flow passage 101 from leaking through a gap between the screw and the liquid fuel flow passage 101. The second sealing member 33 is installed on the outer step at the end surface of the first end of the core bar 10, and is used for forming a first axial seal to seal the gap between the outer wall of the first end of the core bar 10 and the inner wall of the welding cylinder group 20. A third seal 34 is mounted on the outer step at the inner end face of the screw head for forming a second axial seal to seal the gap between the outer wall of the screw head and the inner wall of the welding cartridge set 20. The second sealing element 33, the third sealing element 34 and the first sealing element 32 cooperate to form triple seals, so as to seal a gap between the outer wall of the first end of the core rod 10 and the inner wall of the shaft hole of the first end of the welding cylinder group, seal a gap between the outer wall of the screw head of the oil-passing sealing screw 31 and the inner wall of the shaft hole of the first end of the welding cylinder group 20, and seal a gap between the screw rod of the oil-passing sealing screw 31 and the inner wall of the inflow end of the liquid fuel flow passage 101, thereby preventing the high-temperature auxiliary atomization air in the auxiliary air flow passage 201 from leaking into the liquid fuel flow passage 101 from the three.
Furthermore, the first sealing element 32 and the second sealing element 33 are both metal sealing rings with C-shaped cross sections, and mainly utilize the pressure difference between the high pressure side and the low pressure side to act on the inner side of the C-shaped sealing element, so as to add the attaching force between the sealing elements and the channel wall and improve the sealing effect. The third seal 34 is an O-ring seal, which is primarily a rubber seal that is more resistant to corrosion by liquid fuel.
Preferably, as shown in fig. 1, the gas-liquid sealing member 30 further includes a sealing bushing 35 for sealing, the sealing bushing 35 is installed on the screw rod and tightly pressed against the inner wall of the welding cylinder group 20, and the sealing bushing 35 is tightly clamped between the first end surface and the head surface of the core rod 10, the sealing bushing 35 is used for sealing a gap between the screw rod of the oil-filled sealing screw 31 and the inner wall of the first end shaft hole of the welding cylinder group 20, so as to prevent the high-temperature auxiliary atomizing air in the auxiliary air flow passage 201 from leaking into the liquid fuel flow passage 101 through the gap. The outer wall of the sealing bush 35 is provided with an inward concave annular vent groove 350, the welding cylinder group 20 is provided with a communication hole 203 for communicating the vent groove 350 with atmosphere, the communication hole 203 is used for enabling atmosphere to enter the vent groove 350 so as to enable two sides of the first sealing element 32, two sides of the second sealing element 33 and two sides of the third sealing element 34 to respectively form pressure difference, so that the first sealing element 32, the second sealing element 33 and the third sealing element 34 respectively obtain good sealing performance, and even if a small amount of high-temperature air leaks, due to the good sealing performance of the first sealing element 32, the second sealing element 33 and the third sealing element 34, the leaked high-temperature air cannot leak into the liquid fuel flow channel 101, so that liquid fuel cracking and coking are caused, and an oil path is blocked.
Alternatively, as shown in fig. 1, the fuel atomizer 40 includes a hollow cylindrical atomizing chamber body 41, the atomizing chamber body 41 is arranged coaxially with the core rod 10, and the outer peripheral wall of the atomizing chamber body 41 is convex to form an annular sealing convex ring 410, a first end of the atomizing chamber body 41 extends into the mounting cavity 102 from a second end of the core rod 10, and an end face of the sealing convex ring 410 is welded and fixed with an end face of a second end of the core rod 10 to seal the mounting cavity 102. A first through-flow inlet 411 is formed in a sidewall of the first end of the atomizing chamber body 41, and the first through-flow inlet 411 is used for allowing the liquid fuel in the installation cavity 102 to enter the atomizing chamber body 41 and form a swirling flow for atomization. A sealing body 42 for sealing the first end of the atomizing chamber body 41 is welded and fixed in the shaft hole of the first end of the atomizing chamber body 41, and a first nozzle body 43 for injecting the liquid fuel atomized therein into the air swirler 50 is connected to the second end of the atomizing chamber body 41. In operation, the liquid fuel in the liquid fuel channel 101 firstly enters the installation cavity 102 from the outflow end of the liquid fuel channel 101, then enters the atomizing chamber of the atomizing chamber body 41 under the action of the first inflow hole 411 and forms a rotational flow in the atomizing chamber for atomization, and finally is sprayed into the air swirler 50 by the first nozzle body 43.
Preferably, the number of the first inflow holes 411 is plural, the plural first inflow holes 411 are uniformly arranged on the atomizing chamber body 41 at intervals along the circumferential direction of the atomizing chamber body 41, and each of the first inflow holes 411 is a tangential hole extending along a tangential direction of a reference circle with an outer circle of the atomizing chamber as the reference circle, so as to introduce the liquid fuel in the installation cavity 102 into the atomizing chamber and form swirl atomization in the atomizing chamber.
Alternatively, as shown in fig. 1, the air swirler 50 is in the shape of a hollow cylinder and is coaxially arranged with the fuel atomizer 40, an outer annular wall of the air swirler 50 is protruded to form an annular connecting convex ring, and the connecting convex ring is fixed to an inner wall surface of the second end surface of the welding cylinder group 20. The injection end of the fuel atomizer 40 axially extends into the air swirler 50, a through second inflow hole 501 is formed in the side wall of the air swirler 50, and the second inflow hole 501 is communicated with the outflow end of the auxiliary air flow channel 201, so that the auxiliary atomization air enters the air swirler 50 and forms a rotational flow to further atomize the liquid fuel sprayed by the fuel atomizer 40. In operation, the auxiliary atomization air in the outflow end of the auxiliary air channel 201 enters the air swirler 50 under the action of the second inflow hole 501 and forms a rotational flow in the air swirler 50, so that a rotational flow field is formed between the injection end of the fuel atomizer 40 and the nozzle of the air swirler 50, and the liquid fuel sprayed from the fuel atomizer 40 is further atomized and then sprayed into the combustion chamber through the nozzle of the air swirler 50.
Preferably, as shown in fig. 1, the number of the second inflow holes 501 is plural, the plural second inflow holes 501 are arranged on the air swirler 50 at regular intervals along the circumferential direction of the air swirler 50, and each second inflow hole 501 is a tangential hole or a tangential groove extending along a tangential direction of an inner hole circle of the air swirler 50 as a reference circle so as to introduce the auxiliary atomizing air in the auxiliary air flow passage 201 into the air swirler 50.
Alternatively, as shown in fig. 1, the welding cylinder group 20 includes a nozzle cylinder member 21, a gas homogenizing cylinder 22 and a nozzle cylinder 23, which are sequentially arranged and connected along the axial direction, and the nozzle cylinder member 21, the gas homogenizing cylinder 22 and the nozzle cylinder 23 are hollow cylinders with two ends communicated. The axial hole of the nozzle cylinder 21, the axial hole of the air equalizing cylinder 22, and the axial hole of the nozzle cylinder 23 are connected to form an auxiliary air flow passage 201, and the inlet of the auxiliary air flow passage 201 is provided on the side wall of the nozzle cylinder 23. The gas fuel flow path 202 is arranged in the nozzle cylinder 21, the gas equalizing cylinder 22, and the nozzle cylinder 23 at the same time, and the inlet of the gas fuel flow path 202 is arranged on the side wall of the nozzle cylinder 23. An air swirler 50 is disposed in the axial bore at the second end of the nozzle cartridge 21.
In this alternative embodiment, as shown in FIG. 1, the gas fuel flowpath 202 includes an inlet section disposed within the nozzle barrel 23, a transition section disposed within the homogenizing valve 22, and an outlet section disposed within the nozzle barrel 21. The gas cylinder 22 comprises an extending part, a first connecting disc part and a second connecting disc part which are sequentially arranged and connected, the extending part extends into a shaft hole of the nozzle cylinder part 21 from the first end of the nozzle cylinder part 21, the end face of the first connecting disc part abuts against and is fixedly welded with the end face of the first end of the nozzle cylinder part 21, and the transition section penetrates through the first connecting disc part. The second end of the nozzle tube 23 is respectively sleeved on the first connecting disc part and the second connecting disc part and is respectively welded and fixed with the outer wall of the first connecting disc part and the outer wall of the second connecting disc part, the inlet of the inflow section is arranged on the outer wall of the nozzle tube 23, and the outlet of the inflow section is arranged on the end face of the second end of the nozzle tube 23.
In this alternative embodiment, as shown in fig. 1, the nozzle cartridge 21 includes an inner cylinder 211 fitted around the core rod 10, an outer cylinder 212 fitted around the inner cylinder 211, and a second nozzle body 213. The extending part of the gas homogenizing cylinder 22 extends into the inner cylinder 211 from the first end of the inner cylinder 211, and the first connecting disc part of the gas homogenizing cylinder 22 is welded and fixed with the outer cylinder 212. An annular flow passage between the outer cylinder 212 and the inner cylinder 211 constitutes an outflow section of the gas fuel flow passage 202. The second nozzle body 213 is connected to the second ends of the inner cylinder 211 and the outer cylinder 212, respectively, and the second nozzle body 213 is provided with a gas nozzle 2130 which is communicated with the gas fuel flow passage 202 to inject the gas fuel to the combustion chamber.
In the invention, the welding cylinder group 20 comprises a nozzle cylinder part 21, a gas homogenizing cylinder 22 and a nozzle cylinder 23 which are sequentially arranged and connected along the axial direction, the gas homogenizing cylinder 22 comprises an extending part, a first connecting disc part and a second connecting disc part which are sequentially arranged and connected, the extending part extends into a shaft hole of the nozzle cylinder part 21 from the first end of the nozzle cylinder part 21, the end surface of the first connecting disc part is abutted against and welded and fixed with the end surface of the first end of the nozzle cylinder part 21, and the transition section is arranged by penetrating through the first connecting disc part. The second end of the nozzle tube 23 is respectively sleeved on the first connecting disc part and the second connecting disc part and is respectively welded and fixed with the outer wall of the first connecting disc part and the outer wall of the second connecting disc part, and the nozzle tube 21 comprises an inner tube 211 sleeved outside the core rod 10, an outer tube 212 sleeved outside the inner tube 211 and a second nozzle body 213. The extending part of the gas homogenizing cylinder 22 extends into the inner cylinder 211 from the first end of the inner cylinder 211, the first connecting disc part of the gas homogenizing cylinder 22 is welded and fixed with the outer cylinder 212, and the second nozzle body 213 is respectively connected with the second ends of the inner cylinder 211 and the outer cylinder 212, namely the structure of the welding cylinder group 20 is adopted, so that the whole fuel nozzle can be formed by adopting a cylindrical bar stock machine, thereby saving the manufacturing cost of forging blanks and casting blanks, improving the manufacturing efficiency of the fuel nozzle and reducing the labor intensity of manufacturers.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. A dual phase fuel nozzle, comprising:
a nozzle body used for being connected with the mounting case, a liquid fuel flow passage (101) used for guiding liquid fuel, an auxiliary air flow passage (201) used for guiding auxiliary atomizing air and a gas fuel flow passage (202) used for guiding gas fuel are arranged in the nozzle body, the liquid fuel flow passage (101), the auxiliary air flow passage (201) and the gas fuel flow passage (202) are sequentially arranged from inside to outside in concentric circles, and the flow inlet ends of the auxiliary air flow passage (201) and the gas fuel flow passage (202) are respectively communicated with the outer side wall of the nozzle body, a gas-liquid sealing member (30) for preventing the communication between the inflow end of the liquid fuel flow path (101) and the auxiliary air flow path (201) is communicated with the inflow end of the liquid fuel flow path (101), the inflow end of the liquid fuel flow channel (101) is communicated with the end surface of the inflow end of the nozzle body through the gas-liquid sealing component (30);
the nozzle body comprises a core bar (10) with two communicated ends and extending along the axial direction, and a hollow cylindrical welding cylinder group (20) sleeved outside the core bar (10); the core rod (10) is positioned in the shaft hole of the welding cylinder group (20), the inner channel of the core rod (10) forms the liquid fuel flow channel (101), the first end of the core rod (10) is tightly propped against the inner wall of the shaft hole of the first end of the welding cylinder group (20), and the second end of the core rod (10) is recessed inwards to form a mounting cavity (102) for mounting a fuel atomizer (40); an annular channel between the core bar (10) and the shaft hole of the welding cylinder group (20) forms the auxiliary air flow channel (201), the welding cylinder group (20) is also internally provided with the gas fuel flow channel (202) annularly arranged outside the shaft hole, and the flow inlet of the auxiliary air flow channel (201) and the flow inlet of the gas fuel flow channel (202) are respectively arranged on the side wall of the welding cylinder group (20); the gas-liquid sealing member (30) is positioned in the shaft hole of the welding cylinder group (20) and connected with the first end of the core rod (10) so as to seal a gap between the first end of the core rod (10) and the inner wall of the shaft hole of the welding cylinder group (20) and prevent the inflow end of the liquid fuel flow passage (101) from being communicated with the inflow end of the auxiliary air flow passage (201);
a fuel atomizer (40) and an air swirler (50) are arranged in the injection end of the nozzle body, the fuel atomizer (40) is communicated with the outflow end of the liquid fuel flow passage (101) to atomize the liquid fuel and then inject the liquid fuel into the air swirler (50), the air swirler (50) is communicated with the outflow end of the auxiliary air flow passage (201) to enable the auxiliary atomizing air to form a rotational flow between the nozzle of the fuel atomizer (40) and the nozzle of the air swirler (50) to further atomize the liquid fuel sprayed from the fuel atomizer (40) and inject the further atomized liquid fuel into the combustion chamber, and the end surface of the injection end of the nozzle body is communicated with the outflow end of the gas fuel flow passage (202) to enable the gas fuel to be sprayed into the combustion chamber;
the gas-liquid sealing component (30) comprises an oil-passing sealing screw (31), a first sealing piece (32), a second sealing piece (33) and a third sealing piece (34) which are used for sealing; the oil-passing sealing screw (31) is a hollow screw which is through along the axial direction, a screw rod of the oil-passing sealing screw (31) extends into the core rod (10) from the inflow end of the liquid fuel flow passage (101), then is communicated with the liquid fuel flow passage (101) and is in threaded connection with the inner wall of the core rod (10), and the screw head of the oil-passing sealing screw (31) is tightly propped against the inner wall of a shaft hole at the first end of the welding barrel group (20); the first sealing piece (32) is arranged in the liquid fuel flow passage (101) and positioned between the end face of the screw and a step in the liquid fuel flow passage (101) so as to form a radial seal to prevent the liquid fuel in the liquid fuel flow passage (101) from leaking out of a gap between the screw and the liquid fuel flow passage (101); the second sealing element (33) is arranged on an outer step at the end face of the first end of the core rod (10) and is used for forming a first axial seal so as to seal a gap between the outer wall of the first end of the core rod (10) and the inner wall of the welding cylinder group (20); the third sealing element (34) is arranged on an outer step at the inner end face of the screw head and used for forming a second axial seal to seal a gap between the outer wall of the screw head and the inner wall of the welding barrel group (20).
2. The dual phase fuel nozzle of claim 1,
the first sealing element (32) and the second sealing element (33) are both metal sealing rings with C-shaped sections;
the third sealing element (34) is an O-shaped sealing ring.
3. The dual phase fuel nozzle of claim 1,
the gas-liquid sealing component (30) further comprises a sealing bush (35) for sealing, the sealing bush (35) is arranged on the screw rod and tightly propped against the inner wall of the welding cylinder group (20), and the sealing bush (35) is tightly clamped between the end surface of the first end of the core rod (10) and the end surface of the screw head;
the outer wall of the sealing bush (35) is provided with an inwards concave annular vent groove (350), the welding cylinder group (20) is provided with a communication hole (203) used for communicating the vent groove (350) with atmosphere, so that atmosphere enters the vent groove (350) to enable the two sides of the first sealing element (32), the two sides of the second sealing element (33) and the two sides of the third sealing element (34) to form pressure difference respectively.
4. The dual phase fuel nozzle of claim 1,
the fuel atomizer (40) comprises a hollow cylindrical atomizing chamber body (41), the atomizing chamber body (41) and the core rod (10) are coaxially arranged, the outer peripheral wall of the atomizing chamber body (41) is externally convex to form an annular sealing convex ring (410), a first end of the atomizing chamber body (41) extends into the installation cavity (102) from a second end of the core rod (10), and the end face of the sealing convex ring (410) is welded and fixed with the end face of the second end of the core rod (10) to seal the installation cavity (102);
a first through inflow hole (411) is formed in the side wall of the first end of the atomizing chamber body (41), and the first through inflow hole (411) is used for enabling the liquid fuel in the mounting cavity (102) to enter the atomizing chamber body (41) and form a rotational flow for atomization;
a sealing body (42) used for sealing the first end of the atomizing chamber body (41) is fixedly welded in the shaft hole of the first end of the atomizing chamber body (41), and the second end of the atomizing chamber body (41) is connected with a first nozzle body (43) used for spraying atomized liquid fuel into the air swirler (50).
5. The dual phase fuel nozzle of claim 1,
the air swirler (50) is in a hollow cylinder shape and is coaxially arranged with the fuel atomizer (40), the outer ring wall of the air swirler (50) is convex to form an annular connecting convex ring, and the connecting convex ring is fixed with the inner wall surface of the second end face of the welding cylinder group (20);
the injection end of fuel atomizer (40) stretches into along the axial in air swirler (50), be equipped with second influent stream hole (501) that link up on the lateral wall of air swirler (50), second influent stream hole (501) with the end intercommunication that flows out of auxiliary air runner (201) to make auxiliary atomizing air get into in air swirler (50) and form the whirl in order further to atomize by fuel atomizer (40) spun liquid fuel.
6. The dual phase fuel nozzle of claim 1,
the welding cylinder group (20) comprises a nozzle cylinder component (21), an air equalizing cylinder (22) and a nozzle cylinder (23) which are sequentially arranged and connected along the axial direction, and the nozzle cylinder component (21), the air equalizing cylinder (22) and the nozzle cylinder (23) are hollow cylinders with two communicated ends;
the shaft hole of the nozzle barrel piece (21), the shaft hole of the gas homogenizing barrel (22) and the shaft hole of the nozzle barrel (23) are connected to form the auxiliary air flow channel (201), and the flow inlet of the auxiliary air flow channel (201) is arranged on the side wall of the nozzle barrel (23);
the gas fuel flow passage (202) is simultaneously arranged in the nozzle barrel part (21), the gas homogenizing cylinder (22) and the nozzle barrel (23), and a flow inlet of the gas fuel flow passage (202) is arranged on the side wall of the nozzle barrel (23);
the air swirler (50) is arranged in the shaft hole of the second end of the nozzle barrel part (21).
7. The dual phase fuel nozzle of claim 6,
the gas fuel flow passage (202) comprises a flow inlet section arranged in the nozzle barrel (23), a transition section arranged in the gas homogenizing barrel (22) and a flow outlet section arranged in the nozzle barrel part (21);
the gas homogenizing cylinder (22) comprises an extending part, a first connecting disc part and a second connecting disc part which are sequentially arranged and connected, the extending part extends into a shaft hole of the nozzle cylinder part (21) from the first end of the nozzle cylinder part (21), the end face of the first connecting disc part is abutted against the end face of the first end of the nozzle cylinder part (21) and is welded and fixed, and the transition section penetrates through the first connecting disc part;
the second end of the nozzle barrel (23) is sleeved on the first connecting disc part and the second connecting disc part respectively and is welded and fixed with the outer wall of the first connecting disc part and the outer wall of the second connecting disc part respectively, the inlet of the inflow section is arranged on the outer wall of the nozzle barrel (23), and the outlet of the inflow section is arranged on the end face of the second end of the nozzle barrel (23).
8. The dual phase fuel nozzle of claim 7,
the nozzle barrel part (21) comprises an inner barrel (211) sleeved outside the core rod (10), an outer barrel (212) sleeved outside the inner barrel (211) and a second nozzle body (213);
the extending part of the gas homogenizing cylinder (22) extends into the inner cylinder (211) from the first end of the inner cylinder (211), and the first connecting disc part of the gas homogenizing cylinder (22) is fixedly welded with the outer cylinder (212);
an annular flow passage between the outer cylinder (212) and the inner cylinder (211) forms an outflow section of the gas fuel flow passage (202);
the second nozzle body (213) is respectively connected with the second ends of the inner cylinder (211) and the outer cylinder (212), and a gas nozzle (2130) which is communicated with the gas fuel runner (202) and used for injecting gas fuel into the combustion chamber outwards is arranged on the second nozzle body (213).
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| CN201910698400.7A CN110529879B (en) | 2019-07-31 | 2019-07-31 | Two-phase fuel nozzle |
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| CN201910698400.7A CN110529879B (en) | 2019-07-31 | 2019-07-31 | Two-phase fuel nozzle |
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| CN110529879A CN110529879A (en) | 2019-12-03 |
| CN110529879B true CN110529879B (en) | 2020-12-25 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113048512B (en) * | 2019-12-27 | 2022-08-16 | 中国航发商用航空发动机有限责任公司 | Fuel grading control assembly, fuel system, gas turbine, override valve and fuel grading control method |
| CN115013204A (en) * | 2022-06-20 | 2022-09-06 | 江苏大学 | Dual-fuel vortex nozzle |
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| CN208918718U (en) * | 2018-10-23 | 2019-05-31 | 潍柴西港新能源动力有限公司 | Gas-engine mixer |
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| CN101529163A (en) * | 2006-09-14 | 2009-09-09 | 索拉透平公司 | Gas turbine fuel injector with a removable pilot assembly |
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