CN110529877B - Multi-phase fuel nozzle - Google Patents

Multi-phase fuel nozzle Download PDF

Info

Publication number
CN110529877B
CN110529877B CN201910698326.9A CN201910698326A CN110529877B CN 110529877 B CN110529877 B CN 110529877B CN 201910698326 A CN201910698326 A CN 201910698326A CN 110529877 B CN110529877 B CN 110529877B
Authority
CN
China
Prior art keywords
gas
fuel
cylinder
nozzle
flow channel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201910698326.9A
Other languages
Chinese (zh)
Other versions
CN110529877A (en
Inventor
曾维
王丹
詹先义
赵林
谢卫红
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC South Industry Co Ltd
Original Assignee
AECC South Industry Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC South Industry Co Ltd filed Critical AECC South Industry Co Ltd
Priority to CN201910698326.9A priority Critical patent/CN110529877B/en
Publication of CN110529877A publication Critical patent/CN110529877A/en
Application granted granted Critical
Publication of CN110529877B publication Critical patent/CN110529877B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air
    • F23R3/12Air inlet arrangements for primary air inducing a vortex
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

The invention discloses a multi-phase fuel nozzle, comprising: the nozzle comprises a nozzle body, wherein a liquid fuel flow channel for guiding liquid fuel, a gas-solid mixed flow channel for guiding gas-solid mixed gas flow containing solid fuel powder and a gas fuel flow channel for guiding gas fuel are arranged in the nozzle body, the liquid fuel flow channel, the gas-solid mixed flow channel and the gas fuel flow channel are sequentially arranged from inside to outside in concentric circles, a flow inlet of the liquid fuel flow channel is communicated with the end face of a flow inlet end of the nozzle body, and flow inlets of the gas-solid mixed flow channel and the gas fuel flow channel are respectively communicated with the outer side wall of the nozzle body. The nozzle body is provided with a fuel atomizer and an air swirler in the injection end, the fuel atomizer is communicated with the outflow end of the liquid fuel flow passage, the air swirler is communicated with the outflow end of the gas-solid mixing flow passage, and the end face of the injection end of the nozzle body is communicated with the outflow end of the gas fuel flow passage so as to spray the gas fuel into the combustion chamber.

Description

Multi-phase fuel nozzle
Technical Field
The invention relates to the technical field of gas turbines, in particular to a multiphase fuel nozzle.
Background
The existing gas turbine, especially the aeroderivative gas turbine improved by the aeroengine, mainly uses a single fuel as the using medium, which is used for the using environment of multiple fuels (such as movable emergency power system, travel camp, temporary station in battlefield, etc.), the fuel of the gas turbine may need to be obtained locally, and what is burnt; or multiple fuels may be burned in proportion as required by certain specific applications (e.g., certain emissions requirements). Due to the phase difference (solid, liquid and gas) and calorific value difference among various fuels, each fuel needs to be developed into a corresponding fuel supply system, and the whole fuel supply system of the gas turbine including the fuel nozzle system needs to be replaced when a certain fuel is replaced, so that the maintenance cost of the gas turbine is increased and the reliability is reduced. To solve this technical problem, it is necessary to design a fuel nozzle that can switch fuels at any time and place without stopping the machine for maintenance.
The conventional fuel nozzle is a fuel nozzle, can use natural gas and fuel oil at the same time, takes the natural gas as a main part and the fuel oil as an auxiliary part, and ensures long-term continuous work. The main defects of the fuel nozzles are that the requirements on the quality of the fuel are high, the coverage area of the fuel varieties is very narrow, even a certain variety of fuel (such as 0# diesel oil) is specified, the structure is very complex, the forms are rich and various, for example, a large number of oil holes are formed in an air flow passage support plate, and the fuel nozzles are matched with natural gas nozzles and the like.
Disclosure of Invention
The invention provides a multiphase fuel nozzle, which aims to solve the technical problems of complex structure, rich and various forms, high requirement on fuel quality and narrow coverage of fuel varieties of the conventional fuel nozzle.
The technical scheme adopted by the invention is as follows:
a multi-phase fuel nozzle, comprising: the nozzle body is used for being connected with the mounting case, a liquid fuel flow passage for guiding liquid fuel, a gas-solid mixed flow passage for guiding gas-solid mixed airflow containing solid fuel powder and a gas fuel flow passage for guiding gas fuel are arranged in the nozzle body, the liquid fuel flow passage, the gas-solid mixed flow passage and the gas fuel flow passage are sequentially arranged from inside to outside in a concentric circle mode, a flow inlet of the liquid fuel flow passage is communicated with the end face of a flow inlet end of the nozzle body, and flow inlets of the gas-solid mixed flow passage and the gas fuel flow passage are respectively communicated with the outer side wall of the nozzle body; the fuel atomizer is communicated with the outflow end of the liquid fuel flow passage to atomize the liquid fuel and then spray the atomized liquid fuel into the air swirler, the air swirler is communicated with the outflow end of the gas-solid mixing flow passage to enable the gas-solid mixed gas flow and/or the atomized liquid fuel to form a rotational flow and then spray the rotational flow into a combustion chamber of the gas turbine, and the end surface of the injection end of the nozzle body is communicated with the outflow end of the gas fuel flow passage to enable the gas fuel to be sprayed into the combustion chamber.
Furthermore, the nozzle body comprises a core rod, two ends of the core rod are communicated, the core rod extends in the axial direction, an inner channel of the core rod forms a liquid fuel flow channel, a flow inlet end of the core rod is communicated with a pipeline for supplying liquid fuel, and a flow outlet end of the core rod is recessed inwards to form a mounting cavity for mounting the fuel atomizer; the fuel atomizer is fixedly arranged in the mounting cavity, and the outflow end of the fuel atomizer is communicated with the liquid fuel flow passage.
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 externally protruded to form an annular sealing convex ring, the first end of the atomizing chamber body extends into the installation cavity from the outflow end of the core rod, and the end face of the sealing convex ring abuts against the outflow 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 provided with a sealing body for sealing the first end of the atomizing chamber body, and the second end of the atomizing chamber body is connected with a nozzle body for spraying atomized liquid fuel into the air swirler.
The nozzle body further comprises a hollow cylindrical first body cylinder group sleeved outside the core rod, the first body cylinder group is used for being matched with the core rod to form a gas-solid mixing flow channel, a through gas-solid mixing flow inlet is formed in the side wall of the first body cylinder group, and the gas-solid mixing flow inlet is communicated with a pipeline for supplying gas-solid mixing airflow; the first end of the first body cylinder group is hermetically connected with the outer ring wall of the core rod inflow end, and the second end of the first body cylinder group is provided with an 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 outwards protruded to form an annular connecting convex ring, and the connecting convex ring is fixed with the inner wall surface of the second end surface of the first body cylinder group; a through second inflow hole is formed in the side wall of the air swirler and is used for enabling the gas-solid mixed airflow in the gas-solid mixed flow channel to enter the air swirler to form a rotational flow; the spraying end of the fuel atomizer axially extends into the air swirler so that a swirling flow field is formed between the spraying end of the fuel atomizer and the nozzle of the air swirler under the action of the second inflow hole, and liquid fuel sprayed by the fuel atomizer is further atomized.
Furthermore, the first body cylinder group comprises a first welding cylinder body and a switching cylinder body which are sequentially arranged along the axial direction, and a supporting cylinder body arranged in the first welding cylinder body; the first end of the switching cylinder is hermetically connected with the peripheral wall of the core rod inflow end, the second end of the switching cylinder is in threaded connection with the first end of the first welding cylinder, and the gas-solid mixed flow inlet is formed in the switching cylinder; two ends of the supporting cylinder body are respectively propped against the end face of the second end of the switching cylinder body and the peripheral wall of the core rod outflow end, and a connecting notch for communicating the gas-solid mixing flow channel is formed in the side wall of the supporting cylinder body; the air swirler is arranged in the shaft hole at the second end of the first welding cylinder.
The nozzle body further comprises a second body cylinder group which is sleeved outside the first body cylinder group and is in a hollow cylinder shape, the second body cylinder group is used for being matched with the first body cylinder group to form a gas fuel flow channel, a through gas fuel inlet is arranged on the side wall of the second body cylinder group, and the gas fuel inlet is communicated with a pipeline for supplying gas fuel; the first end of the second body cylinder group is hermetically connected with the outer ring wall of the first end of the first body cylinder group, and the end surface of the second end of the second body cylinder group is provided with a through gas nozzle for injecting gas fuel in the gas fuel flow passage into the combustion chamber.
Further, the second body cylinder group comprises a second welding cylinder body and an end cover body which are sequentially arranged along the axial direction; the outer peripheral wall of the first end of the second welding cylinder is convex to form an annular connecting flange, and a gas nozzle is arranged on the end face of the second end of the second welding cylinder; the end cover body is hermetically arranged on the excircle of the first end of the first body cylinder group, the opening side of the end cover body is detachably and hermetically connected with the connecting flange plate, and a gas fuel inlet is arranged on the side wall of the end cover body; the multiphase fuel nozzle is detachably connected to the mounting cartridge by a connector that passes through the connecting flange and the end cap.
Furthermore, the multiphase fuel nozzle also comprises an adapter joint for introducing the gas-solid mixed gas flow and a locking end cover for locking the adapter joint; the adapter joint is hermetically arranged on the excircle of the first end of the first body cylinder group, one side of the adapter joint is abutted against the end face of the first end of the second body cylinder group, and the adapter joint is respectively communicated with a pipeline for supplying gas-solid mixed gas flow and a gas-solid mixed flow inlet; the locking end cover is in threaded connection with the outer circle of the first end of the first body cylinder group and abuts against the other side of the adapter connector, and is used for locking and positioning the adapter connector on the outer circle of the first body cylinder group.
Furthermore, the multiphase fuel nozzle also comprises a first sealing ring piece, a second sealing ring piece, a third sealing ring piece and a locking nut for locking and fixing, wherein the first sealing ring piece, the second sealing ring piece and the third sealing ring piece are used for sealing gaps; the first sealing ring piece is arranged on the outer circle of the first end of the first body cylinder group, is clamped between the first side of the adapter joint and the first end face of the second body cylinder group and is used for sealing a gap between the first side of the adapter joint and the outer circle surface of the first body cylinder group and the first end face of the second body cylinder group; the second sealing ring piece is arranged on the outer circle of the first end of the first body cylinder group, is tightly clamped between the locking end cover and the second side of the adapter joint and is used for sealing a gap between the second side of the adapter joint and the outer circle surface of the first body cylinder group and the locking end cover; the third sealing ring piece is arranged on the outer circle of the first end of the core bar and clamped between the locking nut and the end face of the first end of the first body cylinder group, and is used for sealing a gap between the first end of the first body cylinder group, the outer circle surface of the core bar and the locking nut.
The invention has the following beneficial effects:
in the multiphase fuel nozzle, the liquid fuel flow passage, the gas-solid mixing 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;
besides the function of conveying solid fuel, the air swirler can form a strong swirling flow field between the injection end of the fuel atomizer and the nozzle of the air swirler, and the swirling flow field can be used as an auxiliary atomization area of liquid fuel to further atomize the fuel sprayed by the fuel atomizer, so that the fuel can still obtain good liquid droplet atomization effect under extremely low fuel flow (even close to the low fuel flow), therefore, the fuel nozzle of the invention not only can realize that any fuel (liquid fuel, solid fuel or gas fuel) is injected into the combustion chamber, but also can ensure that the liquid fuel flow channel can supply fuel to the combustion chamber according to any low fuel proportion, further realize that various fuels are injected into the combustion chamber in any proportion in the fuel nozzle, and still have good combustion effect, so that the combustion chamber can obtain real-time variable multi-fuel supply, and the seamless conversion of various fuels is carried out under the condition that the energy (electric energy and heat energy) output of the combustion chamber is not stopped, the variety of the fuels applicable to the combustion chamber is increased, the range is expanded, 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 multi-phase fuel nozzle of a preferred embodiment of the present invention;
FIG. 2 is a schematic diagram of the right side view of the structure of FIG. 1;
FIG. 3 is a schematic sectional view taken along line A-A in FIG. 1;
FIG. 4 is a schematic sectional view taken along line B-B in FIG. 1;
fig. 5 is a schematic sectional view along the direction C-C in fig. 1.
Description of the figures
10. A core bar; 101. a liquid fuel flow passage; 102. installing a cavity; 20. a first body cylinder group; 201. a gas-solid mixing flow channel; 202. a gas-solid mixed flow inlet; 21. a first welding cylinder; 22. switching the cylinder; 23. a support cylinder; 230. a connection notch; 24. a locking ring; 30. a second body cylinder group; 301. a gaseous fuel flow path; 302. a gaseous fuel inlet; 303. a gas nozzle; 31. a second welding cylinder; 310. connecting a flange plate; 32. an end cap body; 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 nozzle body; 50. an air swirler; 501. a second intake aperture; 60. a transfer joint; 70. a first seal ring member; 80. a second seal ring member; 90. a third seal ring member; 110. locking the end cover; 120. and locking the nut.
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 multi-phase fuel nozzle comprising: the nozzle comprises a nozzle body used for being connected with an installation casing, wherein a liquid fuel flow channel 101 used for guiding liquid fuel, a gas-solid mixed flow channel 201 used for guiding gas-solid mixed airflow containing solid fuel powder and a gas fuel flow channel 301 used for guiding gas fuel are arranged in the nozzle body, the liquid fuel flow channel 101, the gas-solid mixed flow channel 201 and the gas fuel flow channel 301 are sequentially arranged from inside to outside in a concentric circle mode, a flow inlet of the liquid fuel flow channel 101 is communicated with the end face of a flow inlet end of the nozzle body, and flow inlets of the gas-solid mixed flow channel 201 and the gas fuel flow channel 301 are respectively communicated with the outer side wall of the nozzle body. 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 flow channel 101 so as 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 gas-solid mixing flow channel 201 so as to enable the gas-solid mixed gas flow and/or the atomized liquid fuel to form a rotational flow and then inject the rotational flow into a combustion chamber of the gas turbine, and the end surface of the injection end of the nozzle body is communicated with the outflow end of the gas fuel flow channel 301 so as to enable the gas fuel to be injected into the combustion chamber.
When the multiphase fuel nozzle works, liquid fuel supplied by an external pipeline firstly enters a liquid fuel flow channel 101 from a flow inlet on the end face of a flow inlet end of a nozzle body, then enters a fuel atomizer 40 from a flow outlet end of the liquid fuel flow channel 101 for atomization, atomized fuel is sprayed into an air swirler 50 from the fuel atomizer 40, and finally sprayed into a combustion chamber from the air swirler 50; gas-solid mixed airflow containing solid fuel powder supplied by an external pipeline firstly enters the gas-solid mixed runner 201 from a flow inlet on the side wall of the nozzle body, then enters the air swirler 50 from an outflow end of the gas-solid mixed runner 201 to form a rotational flow, and finally is sprayed into the combustion chamber by the air swirler 50; the gas fuel supplied by the external pipeline firstly enters the gas fuel flow passage 301 from the inlet on the side wall of the nozzle body and then is directly injected into the combustion chamber from the injection port on the end face of the injection end of the nozzle body.
In the multiphase fuel nozzle, the liquid fuel flow passage 101, the gas-solid mixing flow passage 201 and the gas fuel flow passage 301 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; besides the function of conveying solid fuel, the conveying air used in the gas-solid mixing channel 201 can form a strong swirling flow field between the injection end of the fuel atomizer 40 and the nozzle of the air swirler 50 due to the action of the air swirler 50, and the swirling flow field can be used as an auxiliary atomization area of liquid fuel to further atomize the fuel sprayed by the fuel atomizer 40, so that the fuel can still obtain good liquid droplet atomization effect under extremely low fuel flow (even close to 0), therefore, the fuel nozzle of the invention not only can realize that any fuel (liquid fuel, solid fuel or gas fuel) is injected into the combustion chamber, but also can ensure that the liquid fuel channel 101 can supply fuel to the combustion chamber according to any low fuel proportion, further realize that various fuels are injected into the combustion chamber in any proportion in the fuel nozzle, and still have good combustion effect, the combustion chamber can obtain real-time variable multi-fuel supply, and the seamless conversion of various fuels can be carried out under the condition that the energy (electric energy and heat energy) output of the gas turbine is not stopped, so that the variety and the range of the fuel suitable for the gas turbine are increased, and the adaptability to the fuel environment is enhanced.
Alternatively, as shown in fig. 1, the nozzle body includes a core rod 10 having two ends communicating with each other and extending in the axial direction, the inner passage of the core rod 10 forms a liquid fuel flow passage 101, the inflow end of the core rod 10 communicates with a pipe for supplying liquid fuel, and the outflow end of the core rod 10 is recessed to form a mounting cavity 102 for mounting the fuel atomizer 40. The fuel atomizer 40 is fixedly installed in the installation cavity 102, and the fuel atomizer 40 is communicated with the outflow end of the liquid fuel flow channel 101.
Specifically, as shown in fig. 1, the fuel atomizer 40 includes a hollow cylindrical atomizing chamber body 41, the atomizing chamber body 41 is coaxially arranged with the core rod 10, and the outer peripheral wall of the atomizing chamber body 41 is protruded to form an annular sealing convex ring 410, a first end of the atomizing chamber body 41 extends into the installation cavity 102 from the outflow end of the core rod 10, and the end surface of the sealing convex ring 410 abuts against the outflow end of the core rod 10 to seal the installation 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 fixedly installed in the shaft hole of the first end of the atomizing chamber body 41, and a 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 through the nozzle body 43.
Preferably, as shown in fig. 4, the number of the first inflow holes 411 is plural, the plural first inflow holes 411 are arranged on the atomizing chamber body 41 at regular intervals along the circumferential direction of the atomizing chamber body 41, and each of the first inflow holes 411 is a tangential hole extending in 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.
Optionally, as shown in fig. 1, the nozzle body further includes a first body cylinder group 20 sleeved outside the core rod 10 and having a hollow cylinder shape, the first body cylinder group 20 is used for cooperating with the core rod 10 to form a gas-solid mixing flow channel 201, a gas-solid mixing flow inlet 202 is provided on a side wall of the first body cylinder group 20, and the gas-solid mixing flow inlet 202 is communicated with a pipeline for supplying a gas-solid mixing flow to introduce the gas-solid mixing flow into the gas-solid mixing flow channel 201. The first end of the first body cylinder set 20 is hermetically connected with the outer annular wall of the inflow end of the core rod 10, and the second end of the first body cylinder set 20 is provided with an air swirler 50.
Specifically, as shown in fig. 1, the air swirler 50 is in a hollow cylindrical shape and is coaxially arranged with the fuel atomizer 40, so that the liquid fuel sprayed from the fuel atomizer 40 directly enters the air swirler 50, 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 face of the first body barrel group 20. Referring to fig. 3, a through second inflow hole 501 is formed in the sidewall of the air swirler 50, and the second inflow hole 501 is used for enabling the gas-solid mixed gas flow in the gas-solid mixed flow channel 201 to enter the air swirler 50 and form a swirling flow. The injection end of the fuel atomizer 40 extends axially into the air swirler 50 to form a swirling flow field between the injection end of the fuel atomizer 40 and the nozzle of the air swirler 50 under the action of the second inflow hole 501, so that the liquid fuel sprayed from the fuel atomizer 40 is further atomized. When the gas-solid mixing device works, gas-solid mixed airflow in the outflow end of the gas-solid mixing flow 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 spraying end of the fuel atomizer 40 and the nozzle of the air swirler 50, and further, after the liquid fuel sprayed from the fuel atomizer 40 is further atomized, the liquid fuel is sprayed into a combustion chamber through the nozzle of the air swirler 50.
Preferably, as shown in fig. 3, the number of the second inflow holes 501 is plural, the plural second inflow holes 501 are uniformly arranged on the air swirler 50 at 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 the tangential direction of the reference circle with the inner hole circle of the air swirler 50 as the reference circle, so as to introduce the gas-solid mixed gas flow in the gas-solid mixed flow passage 201 into the air swirler 50.
Specifically, as shown in fig. 1, the first body cylinder group 20 includes a first welding cylinder 21 and an adapter cylinder 22, which are sequentially provided in the axial direction, and a support cylinder 23 installed in the first welding cylinder 21. The first end of the switching cylinder 22 is hermetically connected with the peripheral wall of the inflow end of the core rod 10, the second end of the switching cylinder 22 is in threaded connection with the first end of the first welding cylinder 21, and the gas-solid mixed flow inlet 202 is arranged on the switching cylinder 22. Further, as shown in fig. 1, the first body cylinder group 20 further includes a locking ring 24 for locking the adapter cylinder 22, and the locking ring 24 is mounted on the outer circumference of the first end of the first welding cylinder 21 and is deformed to be clamped with the outer circumferential wall of the second end of the adapter cylinder 22. Two ends of the supporting cylinder 23 respectively abut against the end face of the second end of the adapting cylinder 22 and the peripheral wall of the outflow end of the core rod 10, and a connecting notch 230 for communicating the gas-solid mixing flow channel 201 is arranged on the side wall of the supporting cylinder 23. An air swirler 50 is disposed in the axial bore at the second end of the first welding cylinder 21. Further, as shown in fig. 5, the number of the connecting notches 230 is plural, and the plural connecting notches 230 are uniformly arranged on the supporting cylinder 23 at intervals along the circumferential direction of the supporting cylinder 23.
Optionally, as shown in fig. 1, the nozzle body further includes a second body cartridge group 30 which is sleeved outside the first body cartridge group 20 and has a hollow cylindrical shape, the second body cartridge group 30 is used for cooperating with the first body cartridge group 20 to form a gas fuel flow passage 301, a gas fuel inlet 302 is provided on a side wall of the second body cartridge group 30, and the gas fuel inlet 302 is communicated with a pipeline for supplying gas fuel. The first end of the second body cylinder group 30 is hermetically connected with the outer ring wall of the first end of the first body cylinder group 20, and the end surface of the second end of the second body cylinder group 30 is provided with a through gas nozzle 303 for injecting the gas fuel in the gas fuel channel 301 into the combustion chamber. In operation, the gas fuel supplied from the external pipeline enters the gas fuel channel 301 through the gas fuel inlet 302, and then is directly injected into the combustion chamber through the gas nozzle 303 at the outlet end of the gas fuel channel 301.
Specifically, as shown in fig. 1, the second body cylinder group 30 includes a second welding cylinder 31 and an end cap body 32 which are sequentially provided in the axial direction. The outer peripheral wall of the first end of the second welding cylinder 31 is convex to form an annular connecting flange 310, and the end face of the second end of the second welding cylinder 31 is provided with a gas nozzle 303. The end cover 32 is hermetically installed on the outer circle of the first end of the first body cylinder group 20, the opening side of the end cover 32 is detachably and hermetically connected with the connecting flange 310, and a gas fuel inlet 302 is formed on the side wall of the end cover 32. The fuel nozzle is removably connected to the mounting cartridge by a connection through the connecting flange 310 and the end cap 32.
Preferably, as shown in fig. 1, the first welding cylinder 21 and the second welding cylinder 31 are integrally connected by welding for easy assembly and connection, and the first ends of the first welding cylinder 21 and the second welding cylinder 31 are connected to form the injection end surface of the nozzle body, so as to install and fix the air swirler 50 and open the gas nozzle 303 on the end surface. The number of gas spout 303 is a plurality of, and a plurality of gas spouts 303 are evenly arranged on second welding barrel 31 along the circumference of second welding barrel 31, interval to evenly spray gaseous fuel to in the combustion chamber.
Specifically, as shown in fig. 1 and 2, the fuel nozzle further includes an adapter 60 for introducing the gas-solid mixture flow and a locking end cap 110 for locking the adapter 60. The adapter 60 is hermetically installed on the outer circle of the first end of the first body cylinder group 20, one side of the adapter 60 abuts against the end surface of the first end of the second body cylinder group 30, and the adapter 60 is respectively communicated with a pipeline for supplying gas-solid mixed gas flow and a gas-solid mixed flow inlet 202. A locking end cap 110 is threaded onto the outer circle of the first end of the first body cartridge set 20 and abuts the other side of the adapter 60 for locking the adapter 60 in place on the outer circle of the first body cartridge set 20.
Preferably, as shown in fig. 1, the fuel nozzle further includes a first seal ring member 70, a second seal ring member 80, a third seal ring member 90 for sealing the gap, and a lock nut 120 for lock-fixing, the lock nut 120 being threadedly coupled to an outer circumference of the first end of the core rod 10 near the first end of the first body barrel group 20. The first sealing ring member 70 is disposed on the outer circumference of the first end of the first body cylinder set 20 and clamped between the first side of the adapter 60 and the first end surface of the second body cylinder set 30 for sealing the gaps between the first side of the adapter 60 and the outer circumferential surface of the first body cylinder set 20 and the first end surface of the second body cylinder set 30, thereby preventing the gas fuel from leaking from these gaps. The second seal ring member 80 is disposed on the outer circumference of the first end of the first body cylinder set 20 and clamped between the locking end cap 110 and the second side of the adapter 60, for sealing the gap between the second side of the adapter 60 and the outer circumferential surface of the first body cylinder set 20 and the locking end cap 110, and preventing the gas fuel from leaking from the gaps. The third sealing ring member 90 is mounted on the outer circle of the first end of the core bar 10, and is clamped between the lock nut 120 and the first end face of the first body cylinder group 20, so as to seal the gap between the first end of the first body cylinder group 20 and the outer circle face of the core bar 10 and the lock nut 120, and prevent the gas-solid mixed gas flow from leaking from the gaps.
Specifically, the first seal ring member 70, the second seal ring member 80, and the third seal ring member 90 are all easily deformable metal rings.
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 (6)

1. A multi-phase fuel nozzle, comprising:
the nozzle comprises a nozzle body used for being connected with an installation casing, wherein a liquid fuel flow channel (101) used for guiding liquid fuel, a gas-solid mixed flow channel (201) used for guiding gas-solid mixed airflow containing solid fuel powder and a gas fuel flow channel (301) used for guiding gas fuel are arranged in the nozzle body, the liquid fuel flow channel (101), the gas-solid mixed flow channel (201) and the gas fuel flow channel (301) are sequentially arranged from inside to outside in a concentric circle mode, a flow inlet of the liquid fuel flow channel (101) is communicated with the end face of a flow inlet end of the nozzle body, and flow inlets of the gas-solid mixed flow channel (201) and the gas fuel flow channel (301) are respectively communicated with the outer side wall of the nozzle body;
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 channel (101) so as to atomize the liquid fuel and then inject the atomized liquid fuel into the air swirler (50), the air swirler (50) is communicated with the outflow end of the gas-solid mixed flow channel (201) so as to enable the gas-solid mixed gas flow and/or the atomized liquid fuel to form a rotational flow and then inject the rotational flow into a combustion chamber of the gas turbine, and the end surface of the injection end of the nozzle body is communicated with the outflow end of the gas fuel flow channel (301) so as to enable the gas fuel to be injected into the combustion chamber;
the nozzle body comprises a core rod (10) with two communicated ends and extending along the axial direction, an inner channel of the core rod (10) forms a liquid fuel flow channel (101), the inflow end of the core rod (10) is communicated with a pipeline for supplying liquid fuel, and the outflow end of the core rod (10) is recessed inwards to form a mounting cavity (102) for mounting a fuel atomizer (40); the fuel atomizer (40) is fixedly arranged in the mounting cavity (102), and the fuel atomizer (40) is communicated with the outflow end of the liquid fuel flow channel (101);
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 convex to form an annular sealing convex ring (410), the first end of the atomizing chamber body (41) extends into the installation cavity (102) from the outflow end of the core rod (10), and the end face of the sealing convex ring (410) abuts against the outflow 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) for sealing the first end of the atomizing chamber body (41) is fixedly arranged in a shaft hole at the first end of the atomizing chamber body (41), and the second end of the atomizing chamber body (41) is connected with a nozzle body (43) for injecting atomized liquid fuel into the air swirler (50); when the liquid fuel atomizer works, liquid fuel in the liquid fuel flow channel (101) firstly enters the installation cavity (102) from the outflow end of the liquid fuel flow channel (101), then enters the atomizing chamber of the atomizing chamber body (41) under the action of the first inflow hole (411) and forms rotational flow in the atomizing chamber to be atomized, and finally is sprayed into the air swirler (50) through the nozzle body (43);
the number of the first inflow holes (411) is multiple, the multiple 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 first inflow hole (411) is a tangential hole which takes the outer circle of the atomizing chamber as a reference circle and extends along the tangential direction of the reference circle so as to introduce the liquid fuel in the installation cavity (102) into the atomizing chamber and form rotational flow atomization in the atomizing chamber;
the nozzle body further comprises a hollow cylindrical first body cylinder group (20) sleeved outside the core rod (10), the first body cylinder group (20) is used for being matched with the core rod (10) to form a gas-solid mixing flow channel (201), a through gas-solid mixing flow inlet (202) is formed in the side wall of the first body cylinder group (20), and the gas-solid mixing flow inlet (202) is communicated with a pipeline for supplying gas-solid mixing gas flow so as to guide the gas-solid mixing gas flow into the gas-solid mixing flow channel (201); the first end of the first body cylinder group (20) is hermetically connected with the outer ring wall of the inflow end of the core rod (10), and the second end of the first body cylinder group (20) is provided with an air swirler (50);
the air swirler (50) is in a hollow cylinder shape and is coaxially arranged with the fuel atomizer (40), so that liquid fuel sprayed by the fuel atomizer (40) directly enters the air swirler (50), the outer ring wall of the air swirler (50) is convex outwards 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 first body cylinder group (20); a through second inflow hole (501) is formed in the side wall of the air swirler (50), and the second inflow hole (501) is used for enabling the gas-solid mixed airflow in the gas-solid mixed flow channel (201) to enter the air swirler (50) and form a rotational flow; the injection end of the fuel atomizer (40) axially extends into the air swirler (50) so as to form a swirling flow field between the injection end of the fuel atomizer (40) and the nozzle of the air swirler (50) under the action of the second inflow hole (501) to further atomize the liquid fuel sprayed by the fuel atomizer (40); when the device works, gas-solid mixed airflow in the outflow end of the gas-solid mixed flow 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 spraying end of the fuel atomizer (40) and the nozzle of the air swirler (50), and further, liquid fuel sprayed out of the fuel atomizer (40) is further atomized and then sprayed into a combustion chamber through the nozzle of the air swirler (50);
the number of the second inflow holes (501) is multiple, the second inflow holes (501) are uniformly distributed on the air swirler (50) at intervals along the circumferential direction of the air swirler (50), and each second inflow hole (501) is a tangential hole or a tangential groove which takes an inner hole circle of the air swirler (50) as a reference circle and extends along the tangential direction of the reference circle so as to introduce the gas-solid mixed airflow in the gas-solid mixed flow passage (201) into the air swirler (50).
2. The multi-phase fuel nozzle of claim 1,
the first body cylinder group (20) comprises a first welding cylinder body (21) and a switching cylinder body (22) which are sequentially arranged along the axial direction, and a supporting cylinder body (23) arranged in the first welding cylinder body (21);
the first end of the switching cylinder (22) is hermetically connected with the peripheral wall of the flow inlet end of the core rod (10), the second end of the switching cylinder (22) is in threaded connection with the first end of the first welding cylinder (21), and the gas-solid mixed flow inlet (202) is arranged on the switching cylinder (22);
two ends of the supporting cylinder (23) are respectively abutted against the end face of the second end of the switching cylinder (22) and the peripheral wall of the outflow end of the core rod (10), and a connecting notch (230) for communicating the gas-solid mixing flow channel (201) is formed in the side wall of the supporting cylinder (23);
the air swirler (50) is arranged in the shaft hole of the second end of the first welding cylinder (21).
3. The multi-phase fuel nozzle of claim 1,
the nozzle body further comprises a second body barrel group (30) which is sleeved outside the first body barrel group (20) and is in a hollow barrel shape, the second body barrel group (30) is used for being matched with the first body barrel group (20) to form the gas fuel flow channel (301), a through gas fuel inlet (302) is formed in the side wall of the second body barrel group (30), and the gas fuel inlet (302) is communicated with a pipeline for supplying gas fuel;
the first end of the second body cylinder group (30) is connected with the outer ring wall of the first end of the first body cylinder group (20) in a sealing mode, and a through gas nozzle (303) is arranged on the end face of the second end of the second body cylinder group (30) so that gas fuel in the gas fuel flow channel (301) can be sprayed into the combustion chamber.
4. The multi-phase fuel nozzle of claim 3,
the second body cylinder group (30) comprises a second welding cylinder body (31) and an end cover body (32) which are sequentially arranged along the axial direction;
the outer peripheral wall of the first end of the second welding cylinder (31) is convex outwards to form an annular connecting flange (310), and the end face of the second end of the second welding cylinder (31) is provided with the gas nozzle (303);
the end cover body (32) is hermetically arranged on the excircle of the first end of the first body cylinder group (20), the opening side of the end cover body (32) is detachably and hermetically connected with the connecting flange plate (310), and the side wall of the end cover body (32) is provided with the gas fuel inlet (302);
the multiphase fuel nozzle is removably coupled to the mounting cartridge by a coupling that passes through the coupling flange (310) and the end cap (32).
5. The multi-phase fuel nozzle of claim 3,
the multiphase fuel nozzle also comprises an adapter joint (60) for introducing a gas-solid mixed gas flow and a locking end cover (110) for locking the adapter joint (60);
the adapter joint (60) is hermetically arranged on the excircle of the first end of the first body cylinder group (20), one side of the adapter joint (60) abuts against the end face of the first end of the second body cylinder group (30), and the adapter joint (60) is respectively communicated with a pipeline for supplying gas-solid mixed gas flow and the gas-solid mixed flow inlet (202);
the locking end cover (110) is in threaded connection with the outer circle of the first end of the first body cylinder group (20) and abuts against the other side of the adapter joint (60) and is used for locking and positioning the adapter joint (60) on the outer circle of the first body cylinder group (20).
6. The multi-phase fuel nozzle of claim 5,
the multiphase fuel nozzle also comprises a first sealing ring piece (70), a second sealing ring piece (80), a third sealing ring piece (90) and a locking nut (120) for locking and fixing, wherein the first sealing ring piece (70), the second sealing ring piece (80) and the third sealing ring piece (90) are used for sealing gaps, and the locking nut (120) is in threaded connection with the outer circle of the first end of the core rod (10) and is close to the first end of the first body barrel group (20);
the first sealing ring member (70) is arranged on the outer circle of the first end of the first body cylinder group (20), is clamped between the first side of the adapter joint (60) and the first end face of the second body cylinder group (30), and is used for sealing a gap between the first side of the adapter joint (60) and the outer circle surface of the first body cylinder group (20) and the first end face of the second body cylinder group (30);
the second sealing ring piece (80) is arranged on the outer circle of the first end of the first body cylinder group (20), is clamped between the locking end cover (110) and the second side of the adapter joint (60), and is used for sealing a gap between the second side of the adapter joint (60) and the outer circle surface of the first body cylinder group (20) and the locking end cover (110);
the third sealing ring piece (90) is arranged on the outer circle of the first end of the core rod (10), is tightly clamped between the locking nut (120) and the end face of the first end of the first body cylinder group (20), and is used for sealing a gap between the first end of the first body cylinder group (20), the outer circular surface of the core rod (10) and the locking nut (120).
CN201910698326.9A 2019-07-31 2019-07-31 Multi-phase fuel nozzle Active CN110529877B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201910698326.9A CN110529877B (en) 2019-07-31 2019-07-31 Multi-phase fuel nozzle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201910698326.9A CN110529877B (en) 2019-07-31 2019-07-31 Multi-phase fuel nozzle

Publications (2)

Publication Number Publication Date
CN110529877A CN110529877A (en) 2019-12-03
CN110529877B true CN110529877B (en) 2021-02-09

Family

ID=68660507

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201910698326.9A Active CN110529877B (en) 2019-07-31 2019-07-31 Multi-phase fuel nozzle

Country Status (1)

Country Link
CN (1) CN110529877B (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080078183A1 (en) * 2006-10-03 2008-04-03 General Electric Company Liquid fuel enhancement for natural gas swirl stabilized nozzle and method
CN101206029B (en) * 2006-12-21 2010-12-08 中国科学院工程热物理研究所 Nozzle for minisize gas-turbine combustor
CN101713546B (en) * 2008-10-08 2013-06-26 中国航空工业第一集团公司沈阳发动机设计研究所 Low-pollution combustor for various fuels
CN202581309U (en) * 2012-06-04 2012-12-05 清远市精旺环保设备有限公司 Atomizing nozzle
CN107166435A (en) * 2017-07-07 2017-09-15 西安富兰克石油技术有限公司 A kind of multi fuel nozzle, fuel spray system and its turbogenerator
CN108443912A (en) * 2018-02-08 2018-08-24 中国船舶重工集团公司第七0三研究所 A kind of self-priming air-assisted atomization dual fuel nozzle

Also Published As

Publication number Publication date
CN110529877A (en) 2019-12-03

Similar Documents

Publication Publication Date Title
US10415832B2 (en) Multi-swirler fuel/air mixer with centralized fuel injection
US9476592B2 (en) System for injecting fuel in a gas turbine combustor
US9239167B2 (en) Lean burn injectors having multiple pilot circuits
JP6035021B2 (en) Dual orifice fuel nozzle with improved fuel atomization
US5579645A (en) Radially mounted air blast fuel injector
US8387391B2 (en) Aerodynamically enhanced fuel nozzle
CA2509895C (en) Natural gas fuel nozzle for gas turbine engine
CN1763434B (en) Low-cost dual-fuel combustor and related method
US7028483B2 (en) Macrolaminate radial injector
US5044559A (en) Gas assisted liquid atomizer
US4441323A (en) Combustion equipment for a gas turbine engine including a fuel burner capable of accurate positioning and installation as a unit in a flame tube
EP2226559B1 (en) System for fuel injection in a turbine engine
JP6557463B2 (en) Fuel injector with premixed pilot nozzle
US4342198A (en) Gas turbine engine fuel injectors
US4754600A (en) Axial-centripetal swirler injection apparatus
EP2554910B1 (en) Methods relating to integrating late lean injection into combustion turbine engines
US6895755B2 (en) Nozzle with flow equalizer
US7000403B2 (en) Primary fuel nozzle having dual fuel capability
EP1489269B1 (en) Methods and apparatus for injecting cleaning fluids into combustors
US8616471B2 (en) Multipoint injectors with standard envelope characteristics
CN102174338B (en) Low-flow, high-mixing ratio and stepless regulation gas-liquid mixing gas generator
US5228283A (en) Method of reducing nox emissions in a gas turbine engine
EP2220437B1 (en) Impingement cooled can combustor
CA1105724A (en) Integrated, replaceable combustor swirler and fuel injector
EP2554905B1 (en) Assemblies and apparatus related to integrating late lean injection into combustion turbine engines

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant