CN113137629B - Double-stage integral swirler and flame tube head structure - Google Patents
Double-stage integral swirler and flame tube head structure Download PDFInfo
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- CN113137629B CN113137629B CN202110417253.9A CN202110417253A CN113137629B CN 113137629 B CN113137629 B CN 113137629B CN 202110417253 A CN202110417253 A CN 202110417253A CN 113137629 B CN113137629 B CN 113137629B
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- swirler
- flame tube
- tube head
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- inner channel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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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
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
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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)
- Spray-Type Burners (AREA)
Abstract
The invention discloses a two-stage integral swirler and a flame tube head structure. The two-stage integral swirler is arranged between the fuel nozzle and the flame tube head ring and used for shearing and atomizing fuel sprayed by the fuel nozzle and conveying the fuel into an inner cavity of the flame tube head ring, the two-stage integral swirler is cylindrical and forms an inner channel arranged along an axis in the middle, the two-stage integral swirler is provided with a bevel hole and a curved surface flow channel which are respectively communicated with the inner channel, the bevel hole is arranged close to the input end of the two-stage integral swirler, the curved surface flow channel is arranged on one side of the bevel hole, which is far away from the input end, the air flow outside the bevel hole is introduced into the inner channel through the bevel hole and forms a first rotating air flow in the inner channel, and the air flow outside the curved surface flow channel is introduced into the inner channel through the curved surface flow channel and forms a second rotating air flow in the inner channel. The two-stage integral swirler can meet the requirement of a high-temperature combustion chamber on a concentration field of a main combustion area.
Description
Technical Field
The invention relates to the technical field of combustion chambers of gas turbine engines, in particular to a two-stage integral swirler. Besides, the invention also relates to a flame tube head structure.
Background
The fuel oil atomizer is an important component of a combustion chamber of a gas turbine engine, each turbine power machine is provided with at least one nozzle for supplying fuel oil, an oil mist field is formed for combustion under the action of the fuel oil atomizer, and the operating performance of the fuel oil atomizer directly influences the ignition and flameout performance, the combustion performance, the pollutant discharge performance and the like of the combustion chamber.
FIG. 1 is a schematic view of a currently used fuel atomizing apparatus, which is composed of a nozzle and a stabilizer, wherein the stabilizer is fixed to a flame tube by welding, the stabilizer is a bowl-shaped bluff body structure, three air streams pass through the stabilizer, an air stream I enters a main combustion area from a narrow gap, and a backflow area is formed at the downstream of the stabilizer; the airflow II flows out through the inclined hole, and the air is used for cooling the inner wall surface of the stabilizer and blowing off carbon deposition; and the airflow III is mainly used for preventing carbon deposition on the end face of the nozzle. The fuel atomization quality of the fuel atomization device mainly depends on the design performance of the nozzle, and the requirement of the high-temperature-rise combustion chamber on the concentration field of the main combustion area cannot be met.
The fuel atomization device in use mainly has the following defects: firstly, the backflow zone mode formed by the stabilizer adopted in the fuel oil atomization device limits the air inflow of the fuel oil atomization device to be not large, otherwise, the speed of the backflow zone is high, the ignition performance and the combustion efficiency in a small state are influenced, but because the air inflow is small, the carbon deposition of a flame tube head ring (10) is serious, a large amount of smoke particles are easily generated in a main combustion zone, and the exhaust pollution is caused; secondly, a stabilizer in the fuel oil atomizer is welded with a flame tube into a whole, a nozzle is inserted into a center hole of the stabilizer, the difference value of expansion amounts generated by the flame tube and a combustion chamber casing due to different temperatures can only be compensated by adopting a sliding structure between a nozzle mounting seat and a nozzle rod, and the largest defect of adopting the sliding structure between the nozzle mounting seat and the nozzle rod is that air leakage is easy to generate, and the higher the pressure of the combustion chamber is, the larger the air leakage amount is; and thirdly, the quality of fuel oil atomization mainly depends on the design performance of a nozzle, and the requirement of a high-temperature-rise combustion chamber on a concentration field of a main combustion area cannot be met.
Disclosure of Invention
The invention provides a two-stage integral swirler, which aims to solve the technical problems that the existing flame tube head structure is poor in atomization performance and cannot meet the requirement of a high-temperature combustion chamber on a concentration field of a main combustion area.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a double-stage integral swirler is arranged between a fuel nozzle and a flame tube head ring and used for shearing, atomizing and conveying fuel sprayed by the fuel nozzle into an inner cavity of the flame tube head ring, the double-stage integral swirler is cylindrical and forms an inner channel distributed along an axis in the middle, the double-stage integral swirler is provided with a bevel hole and a curved flow channel which are respectively communicated with the inner channel, the bevel hole is arranged close to the input end of the double-stage integral swirler, the curved flow channel is arranged on one side of the bevel hole, which is far away from the input end, air flow outside the bevel hole is introduced into the inner channel through the bevel hole and forms a first rotating air flow rotating at a high speed in the circumferential direction in the inner channel, the air flow outside the curved flow channel is introduced into the inner channel through the curved flow channel and forms a second rotating air flow rotating at a high speed in the circumferential direction in the inner channel, the rotating direction of the second rotating air flow is opposite to the rotating direction of the first rotating air flow, the fuel sprayed by the fuel nozzle is tightly adhered to oil drops, the fuel atomized by the second rotating air flow and enters the inner wall surface of the flame tube head ring from the flame tube head ring through the common action of the first rotating air flow and the flame tube head ring to form a rotating head rotating and cover the flame head rotating head.
Furthermore, the oblique cutting holes are distributed in a spiral shape, the number of the oblique cutting holes is multiple, the oblique cutting holes are sequentially distributed at intervals along the circumferential direction of the double-stage integral vortex device, the curved surface flow channels are distributed in a spiral shape, the number of the curved surface flow channels is multiple, the curved surface flow channels are sequentially distributed at intervals along the circumferential direction of the double-stage integral vortex device, and the air flow channels formed by the curved surface flow channels are opposite to the rotating direction of the air flow channels formed by the oblique cutting holes.
Furthermore, the two-stage integral swirler comprises a first-stage swirler for assembling a fuel nozzle and a second-stage swirler for installing on a flame tube head ring, the first-stage swirler and the second-stage swirler are both of hollow cylindrical structures, the first-stage swirler and the second-stage swirler are coaxially arranged and connected into an integral structure, the inner channel comprises an inner channel front section arranged in the first-stage swirler, an inner channel rear section arranged in the second-stage swirler and an annular channel formed by a radial gap between the first-stage swirler and the second-stage swirler, the inner channel front section and the inner channel rear section are communicated with each other, and the annular channel is communicated with the tail end of the inner channel front section at an output end; the secondary swirler is sleeved on the periphery of the output end of the primary swirler, the oblique cutting hole penetrates through the cylinder wall of the primary swirler and is communicated with the front section of the inner channel, a curved surface flow channel is formed by an axial gap between the primary swirler and the secondary swirler, and the output end of the curved surface flow channel is communicated with the input end of the annular channel.
Furthermore, a convex annular first connecting flange is arranged on the outer peripheral wall of the primary swirler, the first connecting flange is located between the input end and the output end of the primary swirler, a convex annular second connecting flange is arranged on the outer peripheral wall of the secondary swirler, the second connecting flange is arranged on the input end of the secondary swirler, the inclined hole is formed in one side, close to the input end, of the first connecting flange, a curved flow channel is formed by an axial gap between the first connecting flange and the second connecting flange, and an annular channel is formed by a radial gap between the primary swirler and a cylinder of the secondary swirler.
Further, the concave arc that runs through first connecting flange along the axial that is equipped with on the lateral wall of first connecting flange leads to the groove, a plurality of arcs lead to the groove and turn round in order towards same soon and form a circumference, second connecting flange is equipped with the arc blade towards the side wall face epirelief of first connecting flange, a plurality of arc blades turn round in order towards same soon and form a circumference, the arc blade is led to the groove one-to-one with the arc and is laid, lead to the groove through arc blade and arc and cooperate so that second connecting flange fixed position is installed on first connecting flange and pass through welded fastening along axial cartridge, two adjacent arc blades enclose between first connecting flange and second connecting flange and close and form a curved surface runner.
Further, the shape of inner channel anterior segment is the tubaeform that radial dimension outwards expands gradually along the direction of input towards the output, and the shape of inner channel back end is the tubaeform that radial dimension outwards expands gradually along the direction of input towards the output.
Furthermore, a floating installation seat for installing the fuel nozzle in a floating mode is arranged on the input end of the primary swirler, the fuel nozzle is movably arranged along the radial direction of the primary swirler by inserting the fuel nozzle into the floating installation seat, and therefore deviation of the fuel nozzle caused by different thermal expansion of the primary swirler and the fuel nozzle is compensated.
Furthermore, the floating installation seat comprises a movable bushing for fixing the fuel nozzle from the output end of the fuel nozzle and a bushing cover plate for axially positioning the movable bushing on the end face of the input end of the primary swirler, the movable bushing is clamped between the bushing cover plate and the primary swirler in the axial direction and is movably arranged in the radial direction of the primary swirler, and the inner diameter of the input end of the primary swirler is larger than that of the movable bushing.
Further, the movable bushing comprises a mounting ring and a mounting edge extending outwards in the radial direction of the mounting ring, the bushing cover plate comprises a fixing ring and a limiting edge extending inwards in the radial direction of the fixing ring, the mounting ring is used for being sleeved on the output end of the fuel nozzle, and the movable bushing is arranged in a sliding mode in the radial direction by pressing the mounting edge between the limiting edge and the input end of the primary swirler.
The invention also provides a flame tube head structure, which comprises a cylindrical flame tube head ring and any one of the two-stage integral type vortex devices arranged at the inlet end of the flame tube head ring, wherein the flame tube head ring is provided with a diverging hole for allowing external airflow to enter the inner side of the flame tube head ring and forming rotary jet flow with the same rotating direction as the second high-speed rotational flow, and a wall surface rotary air film attached to the inner wall surface of the flame tube head ring is formed at the inner wall surface of the flame tube head ring through the interaction of the rotary jet flow and the second high-speed rotational flow, so that the cooling protection of the flame tube head ring is realized.
The invention has the following beneficial effects:
the two-stage integral swirler is provided with the bevel hole and the curved surface flow channel which are communicated with the inner channel of the two-stage integral swirler. The fuel is sprayed into an inner channel of the double-stage integral swirler through the fuel nozzle, one part of external air flow is introduced into the inner channel through the inclined hole, first rotating air flow which rotates and flows at a high speed along the circumferential direction is formed in the inner channel, the other part of external air flow enters the inner channel through the curved surface flow channel and flows into the head ring of the flame tube, and second rotating air flow which rotates and flows at a high speed along the circumferential direction is formed, the rotating direction of the second rotating air flow is opposite to that of the first rotating air flow, the integral swirler ensures the channel concentricity of the first rotating air flow and the second rotating air flow, the circumferential direction of the air flow is uniform to the maximum extent, so that the capability of shearing the fuel sprayed by the fuel nozzle at the intersection of the first rotating air flow and the second rotating air flow is stronger, the fuel forms oil drops with tiny particle sizes, the atomization of the fuel is realized, the fuel atomization particle sizes are tiny, the atomization effect is good, the head air flow structure and the concentration distribution of the fuel can be effectively improved, and the combustion chamber has good point flameout performance, good high-temperature discharge performance and low pollution under the wide working state, so that the combustion chamber is suitable for the high-temperature combustion device; the rotary covering air film which flows along the circumferential direction in a rotating mode is formed on the wall face of the flame tube head ring under the action of the second rotary air flow and the rotary jet flow, the rotary covering air film is tightly attached to the inner wall face of the flame tube head ring, the inner wall face of the flame tube head ring is protected, fuel oil drops are effectively isolated from being in contact with the high-temperature head wall face, head carbon deposit formation is prevented, the cooling effect is good, thermal protection of the flame tube head ring can be achieved to the maximum extent, the deformation, ablation and crack occurrence possibility are reduced, the service life and reliability of the flame tube head ring are improved, the rotary covering air film is uniformly mixed with fuel oil after leaving the flame tube head wall face, combustion reaction is generated, the air utilization rate is further improved, local high oil-gas ratio areas are reduced, and pollution emission is reduced.
In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. 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, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification. In the drawings:
FIG. 1 is a schematic cross-sectional front view of a prior art fuel atomization device;
FIG. 2 is a perspective view of a dual-stage integrated swirler in accordance with a preferred embodiment of the present invention;
FIG. 3 is a cross-sectional view of a dual-stage integrated swirler of a preferred embodiment of the present invention;
FIG. 4 isbase:Sub>A schematic sectional view taken along line A-A in FIG. 3;
FIG. 5 is a schematic sectional view taken along line B-B in FIG. 3;
FIG. 6 is a schematic structural view of a flame tube head configuration according to a preferred embodiment of the invention;
fig. 7 is a view from direction F1 of fig. 6.
Illustration of the drawings:
10. a two-stage integral swirler; 11. an inner channel; 111. an annular channel; 12. obliquely cutting a hole; 13. a curved surface runner; 14. a primary swirler; 141. an inner channel front section; 142. a first connecting flange; 1421. an arc-shaped through groove; 143. a mounting seat; 1431. a movable bushing; 1432. a bushing cover plate; 15. a secondary swirler; 151. an inner channel rear section; 152. a second connecting flange; 1521. an arc-shaped blade; 20. a fuel nozzle; 30. a flame tube head structure; 31. a liner head ring; 311. a diverging 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.
FIG. 1 is a schematic cross-sectional front view of a prior art fuel atomization device; FIG. 2 is a perspective view of a dual stage integral swirler of a preferred embodiment of the present invention; FIG. 3 is a cross-sectional view of a dual-stage integrated swirler of a preferred embodiment of the present invention;
FIG. 4 isbase:Sub>A schematic sectional view taken along line A-A in FIG. 3; FIG. 5 is a schematic sectional view taken along line B-B in FIG. 3; FIG. 6 is a schematic structural view of a flame tube head configuration according to a preferred embodiment of the invention; fig. 7 is a view from direction F1 of fig. 6.
As shown in fig. 2 and 3, in the dual-stage integrated swirler 10 of the present embodiment, the dual-stage integrated swirler 10 is disposed between the fuel nozzle 20 and the flame tube head ring 31, and is configured to shear, atomize and deliver the fuel injected by the fuel nozzle 20 into an inner cavity of the flame tube head ring 31, the dual-stage integrated swirler 10 is cylindrical and forms an inner channel 11 arranged along an axis in a middle portion, the dual-stage integrated swirler 10 is provided with a chamfered hole 12 and a curved flow channel 13 respectively communicated with the inner channel 11, the chamfered hole 12 is disposed near an input end of the dual-stage integrated swirler 10, the curved flow channel 13 is disposed on a side of the chamfered hole 12 away from the input end, the air flow outside the chamfered hole 12 is introduced into the inner channel 11 through the chamfered hole 12 and forms a first swirling air flow flowing at a high speed in a circumferential direction in the inner channel 11, the air flow outside the curved flow channel 13 is introduced into the inner channel 11 and forms a second swirling air flow flowing at a high speed in a circumferential direction in the inner channel 11 through the curved flow channel 13, a swirling direction of the first swirling air flow and the second swirling air flow outside the inner channel 11, and the fuel injection head ring 31 and the flame tube head ring 31 are rotated to form a micro swirling jet flow, and the fuel droplets flowing along the flame tube head ring.
The two-stage integrated swirler 10 of the present invention is provided with a chamfered hole 12 and a curved surface flow passage 13 which are communicated with an inner passage 11 of the two-stage integrated swirler 10. The fuel is sprayed into an inner channel 11 of the double-stage integral swirler 10 through a fuel nozzle 20, one part of external air flow is introduced into the inner channel 11 through an oblique-cut hole 12, a first rotating air flow which rotates and flows at a high speed along the circumferential direction is formed in the inner channel 11, the other part of external air flow enters the inner channel 11 through a curved surface flow channel 13 and flows into a flame tube head ring 31, a second rotating air flow which rotates and flows at a high speed along the circumferential direction is formed in the inner channel 11, the rotating direction of the second rotating air flow is opposite to that of the first rotating air flow, the double-stage integral swirler 10 ensures that the concentricity of the first rotating air flow and the second rotating air flow is ensured, the air flow is uniform in the circumferential direction to the maximum extent, so that the capacity of shearing the fuel sprayed by the fuel nozzle 20 at the intersection of the first rotating air flow and the second rotating air flow is stronger, the fuel forms tiny oil drops, the atomization of the fuel is realized, the particle size of the fuel is tiny, the atomization effect is good, the head air flow structure and the fuel concentration distribution can be effectively improved, the combustion chamber has good emission performance under a wide working condition, good low-temperature-rise and good pollution discharge point, and the invention is suitable for high-temperature combustion chamber; under the action of the second rotary air flow and the rotary jet flow, a rotary covering air film which flows along the circumferential direction in a rotary mode is formed on the wall face of the flame tube head ring 31 and is tightly attached to the inner wall face of the flame tube head ring 31, so that the inner wall face of the flame tube head ring 31 is protected, fuel oil drops are effectively isolated from contacting with the high-temperature head wall face, head carbon deposition is prevented from forming, the cooling effect is good, thermal protection on the flame tube head ring 31 can be achieved to the maximum degree, the possibility of deformation, ablation and crack occurrence is reduced, the service life and reliability of the flame tube head ring 31 are prolonged, the rotary covering air film is uniformly mixed with fuel oil after leaving the flame tube head wall face and generates a combustion reaction, the air utilization rate is further improved, a local high oil-gas ratio area is reduced, and the pollution emission level is reduced.
It can be understood that the hole of the chamfered hole 12 is machined by electric spark machining, the cost is low, the economy is good, the machining quality is good, and the efficiency is high, in the invention, through the mutual shearing action of the two high-speed rotating air flows with opposite rotation directions on the fuel, the atomized particle size of the fuel is smaller, the fuel atomization effect is better, and the atomized quality of the fuel is not completely dependent on the design performance of the fuel nozzle 20.
Further, the inclined cutting holes 12 are arranged in a spiral shape, the number of the inclined cutting holes 12 is multiple, the inclined cutting holes 12 are sequentially arranged at intervals along the circumferential direction of the double-stage integral swirler, the curved surface flow channels 13 are arranged in a spiral shape, the number of the curved surface flow channels 13 is multiple, the curved surface flow channels 13 are sequentially arranged at intervals along the circumferential direction of the double-stage integral swirler, and the air flow channels formed by the curved surface flow channels 13 are opposite to the rotating direction of the air flow channels formed by the inclined cutting holes 12. The first swirling air flow swirling in the circumferential direction at a high speed is formed in the inner passage 11 by the rectifying action of the chamfered holes 12, and the second swirling air flow swirling in the circumferential direction at a high speed is formed in the inner passage 11 by the rectifying action of the curved flow passage 13. The number of the oblique cutting holes 12 may be five, six or eight, and the number of the curved flow channels 13 may be five, six or eight, and the number is set according to the actual use situation.
Referring to fig. 4 and 5, further, the two-stage integral swirler includes a first-stage swirler 14 for assembling the fuel nozzle 20 and a second-stage swirler 15 for mounting on the flame tube head ring 31, both the first-stage swirler 14 and the second-stage swirler 15 are hollow cylindrical structures, the first-stage swirler 14 and the second-stage swirler 15 are coaxially arranged and connected into an integral structure, the inner channel 11 includes an inner channel front section 141 arranged in the first-stage swirler 14, an inner channel rear section 151 arranged in the second-stage swirler 15, and an annular channel 111 formed by a radial gap between the first-stage swirler 14 and the second-stage swirler 15, the inner channel front section 141 and the inner channel rear section 151 are communicated with each other, and the annular channel 111 is communicated with a tail end of the inner channel front section 141 at an output end; the secondary swirler 15 is sleeved on the periphery of the output end of the primary swirler 14, the inclined cutting hole 12 penetrates through the cylinder wall of the primary swirler 14, the inclined cutting hole 12 is communicated with the front section 141 of the inner channel, a curved flow channel 13 is formed by an axial gap between the primary swirler 14 and the secondary swirler 15, and the output end of the curved flow channel 13 is communicated with the input end of the annular channel 111. It is understood that the primary swirler 14 may be a unitary structure co-cast with the secondary swirler 15, a unitary structure formed by 3D printing, or a unitary structure formed by welding. Specifically, the secondary swirler 15 is sleeved on the periphery of the output end of the primary swirler 14, the inner diameter of the inner channel front section 141 is smaller than the inner diameter of the inner channel rear section 151, a radial gap between the primary swirler 14 and the secondary swirler 15 forms an annular channel 111, an axial gap between the primary swirler 14 and the secondary swirler 15 forms a curved flow channel 13, the output end of the curved flow channel 13 is communicated with the input end of the annular channel 111, the output end of the annular channel 111 is communicated with the inner channel front section 141 at the intersection of the inner channel front section 151 and the inner channel rear section 152, so that all air flows through the annular channel 111 and the inner channel front section 141 flow into the inner channel rear section 152, and further fuel sprayed by the fuel nozzle 20 is sheared in the inner channel rear section 152. In the present embodiment, the primary swirler 14 and the secondary swirler 15 are always concentric.
It can be understood that, in this embodiment, the fuel flow channel of the fuel nozzle 20 is designed as a spiral channel, the fuel injected by the fuel nozzle 20 is conical and impacts on the outlet at the end of the primary swirler 14, and is atomized into tiny oil drops under the high-speed shearing of the reverse rotating jet formed by the primary swirler 1423 and the secondary swirler 1524; the primary swirler 14 is used to form an expanding swirling air flow, and the secondary swirler 15 is used to form a swirling air flow having a stronger degree of swirl. The secondary swirler 15 is fitted with a swirler fixing ring through bolts and then fixed on the flame tube head ring 31. Specifically, the second-stage swirler 15 is connected with a swirler fixing ring in the middle and is prevented from loosening by a gasket, and the swirler fixing ring is welded with the wall surface of the flame tube head into a whole through a welding line. Optionally, when the first rotating airflow rotates clockwise and has an axial inflow velocity, the second rotating airflow rotates counterclockwise and has an axial inflow velocity; the second rotating airflow rotates clockwise and has an axial inflow velocity when the first rotating airflow rotates counterclockwise and has an axial inflow velocity.
Furthermore, a convex annular first connecting flange 142 is arranged on the outer peripheral wall of the primary swirler 14, the first connecting flange 142 is located between the input end and the output end of the primary swirler 14, a convex annular second connecting flange 152 is arranged on the outer peripheral wall of the secondary swirler 15, the second connecting flange 152 is arranged on the input end of the secondary swirler 15, the chamfered hole 12 is arranged on one side, close to the input end, of the first connecting flange 142, a curved flow channel 13 is formed by an axial gap between the first connecting flange 142 and the second connecting flange 152, and an annular channel 111 is formed by a radial gap between the primary swirler 14 and a cylinder of the secondary swirler 15. In the present embodiment, the primary swirler 14 and the secondary swirler 15 are welded, and an axial gap is formed between the second connecting flange 152 and the first connecting flange 142, and the axial gap cooperates with the arc-shaped vane 1521 to form the curved flow passage 13.
Further, an arc-shaped through groove 1421 axially penetrating through the first connecting flange 142 is concavely arranged on the side wall of the first connecting flange 142, the plurality of arc-shaped through grooves 1421 are sequentially turned in the same turning direction to form a circumference, arc-shaped blades 1521 are convexly arranged on the side wall surface of the second connecting flange 152 facing the first connecting flange 142, the plurality of arc-shaped blades 1521 are sequentially turned in the same turning direction to form a circumference, the arc-shaped blades 1521 and the arc-shaped through grooves 1421 are arranged in a one-to-one correspondence manner, the arc-shaped blades 1521 and the arc-shaped through grooves 1421 are axially inserted and matched to enable the second connecting flange 152 to be positioned and mounted on the first connecting flange 142 and fixed by welding, and two adjacent arc-shaped blades 1521 are enclosed between the first connecting flange 142 and the second connecting flange 152 to form a curved flow channel 13. 1. The stage swirler 1423 and the stage swirler 1524 are welded into a whole at the arc-shaped through groove 1421 by using vacuum brazing, so that the relative positions of the first swirler and the second swirler can be fixed, and meanwhile, the gas flow is prevented from leaking from the side walls of the first connecting flange 142 and the second connecting flange 152.
Further, for the position of crossing of its first rotatory air current of reasonable control and the rotatory air current of second and then reach better shearing atomization effect, the shape of inner channel anterior segment 141 is the tubaeform that radial dimension expands outward gradually along the direction of input towards the output, and the shape of inner channel back end 151 is the tubaeform that radial dimension expands outward gradually along the direction of input towards the output.
Further, a floating mount 143 for floating mounting the fuel nozzle 20 is provided on an input end of the primary swirler 14, and the fuel nozzle 20 is movably disposed in a radial direction of the primary swirler 14 by inserting the fuel nozzle 20 on the floating mount 143 to compensate for deviation of the fuel nozzle 20 due to different thermal expansion of the primary swirler 14 and the fuel nozzle 20. In the embodiment, the first swirler and the second swirler are fixedly connected into a whole, and there is no relative movement between the first swirler and the second swirler, which is beneficial to ensuring the stability of the first swirling air flow and the second swirling air flow to ensure the consistency of the atomization effect, and the consistency has a great influence on the atomization effect, and the fuel nozzle 20 is floatingly mounted on the primary swirler 14, so that the fuel nozzle 20 is integrally and movably arranged along the radial direction relative to the first swirler and the second swirler, and is beneficial to reducing the abrasion and damage caused by thermal deformation in the actual use process.
It will be appreciated that the floating mount 143 compensates for the eccentricity of the fuel nozzle 20 nozzle center and the integrated swirler center due to thermal expansion, yet ensures that no excess air enters the conical passage of the de-primary swirler 14 through the clearance fit between the two.
Further, the floating mount 143 includes a movable liner 1431 for fixing the fuel nozzle 20 from the output end of the fuel nozzle 20 and a liner cover plate 1432 for positioning the movable liner 1431 axially on the end face of the input end of the primary swirler 14, the movable liner 1431 is snap-fitted axially between the liner cover plate 1432 and the primary swirler 14 and is movably disposed in the radial direction of the primary swirler 14, and the inner diameter of the input end of the primary swirler 14 is larger than the inner diameter of the movable liner 1431. Specifically, the fixing ring of the bushing cover plate 1432 is fixed with the primary swirler 14 at the end face of the input end of the primary swirler 14 by fusion welding, a space is left between the limiting edge of the bushing cover plate 1432 and the end face of the input end of the primary swirler 14 to form a clamping groove, the mounting edge of the movable bushing 1431 is embedded in the clamping groove and is arranged in a radially slidable manner, and the mounting ring of the movable bushing 1431 is used for assembling the fuel nozzle 20.
Specifically, the movable liner 1431 includes a mounting ring and a mounting edge extending radially outward of the mounting ring, and the liner cover plate 1432 includes a fixing ring and a retaining edge extending radially inward of the fixing ring, the mounting ring is configured to be fitted over the output end of the fuel nozzle 20, and the movable liner 1431 is slidably disposed in the radial direction by press-fitting the mounting edge between the retaining edge and the input end of the primary swirler 14. Alternatively, the mounting ring and the mounting rim are integrally formed, and the retaining ring and the retaining rim are integrally formed.
Referring to fig. 6 and 7, the present invention further provides a dual-stage integrated swirler 10 including a cylindrical flame tube head ring 31 and the two-stage integrated swirler 10 installed at an inlet end of the flame tube head ring 31, wherein the flame tube head ring 31 is provided with a diverging hole 311 for allowing an external airflow to enter the inner side of the flame tube head ring 31 and forming a swirling jet flow having the same swirling direction as the second high-speed swirling flow, and a wall surface swirling air film attached to the inner wall surface of the flame tube head ring 31 is formed at the inner wall surface of the flame tube head ring 31 by interaction of the swirling jet flow and the second high-speed swirling flow, so as to realize cooling protection of the flame tube head ring 31. Specifically, the center axis of the diverging holes 311 is inclined toward the rotational direction of the swirling flow, and a part of the air outside the wall of the liner head ring 31 is guided through the diverging holes 311 to be injected into the wall of the liner head ring 31 and to rotate the jet flow. It can be understood that, in this embodiment, the number of the diverging holes 311 is plural, the plural diverging holes 311 are arranged at intervals along the circumferential direction of the flame tube head ring 31 to form a circle of diverging hole groups, the plural groups of diverging hole groups are arranged at intervals along the extending direction of the surface of the flame tube head ring 31, so that the airflow outside the diverging holes 311 enters the flame tube head ring 31 through the diverging holes 311 and forms a rotating jet flow, and the rotating direction of the rotating jet flow is opposite to the rotating direction of the second high-speed rotational flow.
The flame tube head structure 30 is provided with the two-stage integral swirler 10, and the first rotating airflow and the second rotating airflow which are uniformly distributed in the circumferential direction and are generated by the two-stage integral swirler 10, and in the flame tube head structure 30, the fuel oil atomization particle size is small, the atomization effect is good, so that the head airflow structure and the fuel oil concentration distribution of a combustion chamber can be effectively improved, and the combustion chamber is ensured to have good ignition and extinction performance, good outlet temperature field and low pollution emission performance in a wide working state, so that the structure is better suitable for the combustion chamber with high temperature rise and low emission; by arranging the floating mounting seat 143, the deviation between the center of the fuel nozzle 20 and the center of the double-stage integral swirler 10 fixed by the flame tube head ring 31 due to different thermal expansion can be effectively compensated, the air flow leakage is reduced, and the fuel atomization deterioration caused by the air flow leakage is further reduced; through the rotatory air current of second and rotatory efflux, can protect the internal face of flame tube head ring 31, it is effectual completely cut off fuel oil and drip and the contact of high temperature head wall, be favorable to preventing head carbon deposit from forming, the cooling effect is good, can furthest's realization is to the thermal protection of flame tube head, the possibility of deformation, ablation, crackle emergence has been reduced, flame tube head life-span and reliability have been improved, and rotatory cover gas film leaves behind the flame tube head ring 31 wall with the fuel homogeneous mixing and take place the combustion reaction, further improve air utilization, reduce local high oil-gas ratio region simultaneously, be favorable to reducing pollution emission.
The present invention has been described in terms of the preferred embodiment, and it is not intended to be limited to the embodiment. 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 (9)
1. A double-stage integral swirler is arranged between a fuel nozzle (20) and a flame tube head ring (31) and is used for shearing and atomizing fuel sprayed by the fuel nozzle (20) and conveying the fuel into an inner cavity of the flame tube head ring (31),
the double-stage integral swirler is cylindrical and is provided with an inner channel (11) distributed along the axis in the middle, the double-stage integral swirler is provided with a bevel hole (12) and a curved surface runner (13) which are respectively communicated with the inner channel (11), the bevel hole (12) is arranged close to the input end of the double-stage integral swirler, the curved surface runner (13) is arranged on one side of the bevel hole (12) far away from the input end,
introducing airflow outside the oblique cutting holes (12) into the inner channel (11) through the oblique cutting holes (12) and forming first rotary airflow which flows in a circumferential high-speed rotating mode in the inner channel (11), introducing airflow outside the curved surface flow channel (13) into the inner channel (11) through the curved surface flow channel (13) and forming second rotary airflow which flows in the circumferential high-speed rotating mode in the inner channel (11), wherein the rotating direction of the second rotary airflow is opposite to that of the first rotary airflow, fuel oil sprayed by the fuel nozzle (20) is sheared into oil drops with small particle size under the combined action of the first rotary airflow and the second rotary airflow so as to achieve atomization of the fuel oil, and a rotary covering air film which rotates in the circumferential direction and flows tightly to the inner wall face of the flame tube head ring (31) is formed under the combined action of the second rotary airflow and rotary jet flow entering from the outer portion of the flame tube head ring (31) so as to achieve cooling of the flame tube head ring (31);
the double-stage integrated swirler comprises a first-stage swirler (14) for assembling a fuel nozzle (20) and a second-stage swirler (15) for being installed on a flame tube head ring (31);
a convex annular first connecting flange (142) is arranged on the outer peripheral wall of the primary swirler (14), the first connecting flange (142) is positioned between the input end and the output end of the primary swirler (14), a convex annular second connecting flange (152) is arranged on the outer peripheral wall of the secondary swirler (15), and the second connecting flange (152) is arranged on the input end of the secondary swirler (15);
the side wall of the first connecting flange (142) is concavely provided with an arc-shaped through groove (1421) which penetrates through the first connecting flange (142) along the axial direction, the arc-shaped through grooves (1421) are sequentially turned towards the same turning direction to form a circumference, the side wall surface of the second connecting flange (152) which faces the first connecting flange (142) is convexly provided with arc-shaped blades (1521), the arc-shaped blades (1521) are sequentially turned towards the same turning direction to form a circumference, the arc-shaped blades (1521) and the arc-shaped through grooves (1421) are arranged in a one-to-one correspondence manner, the arc-shaped blades (1521) and the arc-shaped through grooves (1421) are axially inserted and matched to enable the second connecting flange (152) to be positioned and installed on the first connecting flange (142) and fixed by welding, and two adjacent arc-shaped blades (1521) are enclosed between the first connecting flange (142) and the second connecting flange (152) to form the curved surface flow passage (13).
2. The two-stage integrated swirler of claim 1,
the oblique holes (12) are spirally distributed, the number of the oblique holes (12) is multiple, the oblique holes (12) are sequentially distributed at intervals along the circumferential direction of the double-stage integral swirler,
the curved surface runners (13) are spirally arranged, the number of the curved surface runners (13) is multiple, the curved surface runners (13) are sequentially arranged at intervals along the circumferential direction of the two-stage integral vortex device, and the rotating directions of airflow channels formed by the curved surface runners (13) and airflow channels formed by the oblique cutting holes (12) are opposite.
3. The two-stage integrated swirler of claim 1,
the primary vortex generator (14) and the secondary vortex generator (15) are both hollow cylindrical structures, the primary vortex generator (14) and the secondary vortex generator (15) are coaxially arranged and connected into an integral structure,
the inner channel (11) comprises an inner channel front section (141) arranged in the primary swirler (14), an inner channel rear section (151) arranged in the secondary swirler (15) and an annular channel (111) formed by a radial gap between the primary swirler (14) and the secondary swirler (15), the inner channel front section (141) is communicated with the inner channel rear section (151), and the annular channel (111) is communicated with the tail end of the inner channel front section (141) at the output end;
the secondary vortex device (15) is sleeved on the periphery of the output end of the primary vortex device (14), the inclined cutting hole (12) penetrates through the cylinder wall of the primary vortex device (14), the inclined cutting hole (12) is communicated with the inner channel front section (141), an axial gap between the primary vortex device (14) and the secondary vortex device (15) forms the curved surface flow channel (13), and the output end of the curved surface flow channel (13) is communicated with the input end of the annular channel (111).
4. The dual-stage integrated swirler of claim 3,
the inclined cutting hole (12) is formed in one side, close to the input end, of the first connecting flange (142), an axial gap between the first connecting flange (142) and the second connecting flange (152) forms the curved flow channel (13), and a radial gap between the primary swirler (14) and a cylinder of the secondary swirler (15) forms the annular channel (111).
5. The dual-stage integrated swirler of claim 3,
the shape of the front section (141) of the inner channel is a trumpet shape with the radial dimension gradually expanding outwards along the direction from the input end to the output end,
the inner channel rear section (151) is in the shape of a trumpet with a radial dimension gradually expanding outwards along the direction from the input end to the output end.
6. The dual-stage integrated swirler of claim 3,
the input end of the primary swirler (14) is provided with a floating installation seat (143) for installing the fuel nozzle (20) in a floating mode, the fuel nozzle (20) is movably arranged along the radial direction of the primary swirler (14) by inserting the fuel nozzle (20) on the floating installation seat (143), and deviation of the fuel nozzle (20) caused by different thermal expansion of the primary swirler (14) and the fuel nozzle (20) is compensated.
7. The dual-stage integrated swirler of claim 6,
the floating mount (143) comprising a movable bushing (1431) for fixing the fuel nozzle (20) from the output end of the fuel nozzle (20) and a bushing cover plate (1432) for positioning the movable bushing (1431) axially on the end face of the input end of the primary swirler (14),
the movable bushing (1431) is clamped between the bushing cover plate (1432) and the primary swirler (14) along the axial direction and is movably arranged along the radial direction of the primary swirler (14),
the inner diameter of the input end of the primary swirler (14) is larger than the inner diameter of the movable bushing (1431).
8. The dual-stage integrated swirler of claim 7,
the movable bushing (1431) comprises a mounting ring and a mounting edge extending radially outwards along the mounting ring, the bushing cover plate (1432) comprises a fixing ring and a limiting edge extending radially inwards along the fixing ring,
the mounting ring is used for being sleeved on the output end of a fuel nozzle (20), and the movable bushing (1431) can be arranged in a sliding mode along the radial direction through the fact that the mounting edge is pressed between the limiting edge and the input end of the primary swirler (14).
9. A flame tube head structure, which is characterized in that,
comprising a cylindrical liner head ring (31) and the two-stage integrated swirler of one of the preceding claims 1 to 8 mounted on the inlet end of the liner head ring (31),
the flame tube head ring (31) is provided with a diverging hole (311) for allowing external airflow to enter the inner side of the flame tube head ring (31) and form rotating jet flow with the same rotating direction as the second high-speed rotational flow, and a wall surface rotating air film attached to the inner wall surface of the flame tube head ring (31) is formed on the inner wall surface of the flame tube head ring (31) through the interaction of the rotating jet flow and the second high-speed rotational flow, so that the cooling protection of the flame tube head ring (31) is realized.
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| CN114413282B (en) * | 2021-12-15 | 2023-05-30 | 西安航天动力研究所 | Stabilizer for strengthening oil-gas mixing for ramjet engine |
| CN114963236A (en) * | 2022-06-23 | 2022-08-30 | 中国航发贵阳发动机设计研究所 | Mounting structure of radial air intake swirler |
| CN115163667A (en) * | 2022-07-27 | 2022-10-11 | 合肥工业大学 | Vortex type air outlet plane static pressure air bearing |
| CN115560359A (en) * | 2022-09-26 | 2023-01-03 | 中国航发湖南动力机械研究所 | Swirler assembly and gas turbine combustor |
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