Pneumatic cone of annular pipe combustion chamber, annular pipe combustion chamber and method for eliminating high-temperature backflow

Abstract

The pneumatic cone comprises a flow guide cone and a center cylinder from front to back, the flow guide cone is conical, the cone angle faces forwards, the center cylinder is cylindrical, a plurality of air inlet holes are formed in the cylinder wall, the outer diameter of the bottom face of the flow guide cone is matched with the outer diameter of the center cylinder, and the flow guide cone and the center cylinder are coaxially and fixedly connected. An end plate is fixedly arranged at the tail end of the center cylinder in a sealed mode, and air outlet holes are densely distributed in the end plate. The invention further relates to a ring pipe combustion chamber adopting the pneumatic cone and a method for eliminating high-temperature backflow of the ring pipe combustion chamber. A part of cold air flow entering the annular pipe combustion chamber enters the pneumatic cone and then is sprayed out from the air outlet hole in the tail end of the pneumatic cone, a cold air impact potential nucleus area is formed behind the pneumatic cone, backflow of high-temperature hot flow sprayed out along the annularly-distributed flame tubes can be effectively restrained, and the combustion efficiency is improved. A backflow vortex core at the center of an outlet of the annular pipe combustion chamber is eliminated, and structure ablation or damage at the downstream center in the annular pipe combustion chamber caused by backflow of high-temperature heat flow is avoided.

Description

Technical Field

[0001] The invention relates to an aerodynamic cone of an annular tube combustion chamber, an annular tube combustion chamber using the aerodynamic cone and a method for eliminating high-temperature backflow of the annular tube combustion chamber, belonging to the technical field of annular tube combustion chambers. Background Art

[0002] The annular tube combustor was initially used in aircraft engine structures, and later expanded to different types of high-temperature airflow application fields. With its easy maintenance, replicability, modularity, and high-pressure resistance, it has been widely used in specific high-temperature airflow application fields such as large flow and high pressure.

[0003] A typical annular tube combustion chamber is mainly composed of a combustion chamber casing, a flame tube distributed along a ring in the casing, and a nozzle arranged at the head end of the flame tube. For example, the invention patent with the publication number CN108375081A discloses a dual-fuel annular tube combustion chamber using fuel oil and natural gas as fuel, including a dual-fuel nozzle, a flame tube, a shell, a dual-fuel igniter, a fuel main pipe, a natural gas main pipe, an atomizing air bleed pipe, an atomizing air main pipe, a fuel oil supply branch pipe, a natural gas supply branch pipe, an atomizing air branch pipe, a diffuser and a positioning pin; the shell is equipped with sixteen independent burners, each burner includes a dual-fuel nozzle and a flame tube, and the sixteen flame tubes are assembled into a ring and overlapped with the turbine first-stage guide; the other ends of the fuel oil supply branch pipe, the natural gas supply branch pipe, and the atomizing air branch pipe are respectively connected to the corresponding interfaces of the dual-fuel nozzle; two symmetrically distributed dual-fuel igniters are installed on the outside of the shell, and the dual-fuel igniters pass through the shell and are connected to the flame tube. The annular tube combustion chamber is easy to use, simple to operate, has wide adaptability, and is easy to promote and apply on a large scale. For another example, the invention patent with the publication number CN116538535A discloses a temperature measurement system for an annular tube combustion chamber and its working method, wherein the temperature measurement system for annular tube combustion chamber comprises: a combustion chamber shell, wherein the inner and outer walls of the combustion chamber shell enclose an inner cavity of the combustion chamber; a plurality of flame tubes are arranged in the inner cavity of the combustion chamber, and the plurality of flame tubes are evenly spaced along the circumferential direction in the inner cavity of the combustion chamber; a cross-flame tube is arranged between two adjacent flame tubes for flame transmission; a viewing window is arranged on both radial sides of the cross-flame tube, and is suitable for providing an optical path for the laser; a TDLAS temperature measurement component comprises a laser transmitter and a laser receiver, wherein the laser transmitter and the laser receiver are respectively arranged on both radial sides of the cross-flame tube and are arranged opposite to the viewing window; the temperature measurement system for annular tube combustion chamber can improve the accuracy and timeliness of combustion monitoring and diagnosis of annular tube combustion chamber of a gas turbine. The above-mentioned technologies have their own characteristics and are respectively applicable to various adaptive occasions. However, when the above technology is applied, since the airflow ejected from the flame tube distributed along the ring is a high-temperature hot flow, it is easy to form a backflow in the center of the downstream combustion chamber, causing ablation or damage to the structure in the center of the combustion chamber, and easily causing flow oscillation in the combustion chamber due to large backflow vortices. Summary of the invention

[0004] In order to overcome the above-mentioned defects of the prior art, the present invention provides an aerodynamic cone of an annular tube combustion chamber, an annular tube combustion chamber and a method for eliminating high-temperature reflux, which can suppress the reflux of high-temperature heat flow ejected from the flame tube and eliminate the reflux vortex core at the outlet center of the annular tube combustion chamber.

[0005] The technical solution for achieving the above-mentioned purpose of the present invention is: the aerodynamic cone of the annular tube combustion chamber includes a guide cone and a center tube from front to back, the guide cone is conical in shape with the cone angle facing forward, the center tube is cylindrical in shape, and a plurality of air inlet holes are provided on the tube wall, the outer diameter of the bottom surface of the guide cone matches the outer diameter of the center tube, the two are coaxially fixedly connected, and the end of the center tube is fixedly sealed with an end plate, and the end plate is densely covered with air outlet holes.

[0006] Preferably, the air outlet holes include outer ring anti-return holes, central purge holes and peripheral divergent holes, the number of the outer ring anti-return holes is multiple, and they are evenly distributed on the same radial circumference on the end plate near the outer edge of the plate surface, the central purge hole is located on the inner side of the outer ring anti-return holes, the number of the central purge holes is multiple, and they are evenly distributed on the same radial circumference on the end plate, or the central purge holes are divided into several groups, and the number of central purge holes in each group is multiple, and several groups of central purge holes are evenly distributed on the end plate along different radial circumferences, the aperture of the central purge hole is smaller than the aperture of the outer ring anti-return holes, the peripheral divergent holes are located on the outer side of the central purge holes, the peripheral divergent holes are divided into several groups, the number of peripheral divergent holes in each group is multiple, and several groups of peripheral divergent holes are evenly distributed on the end wall along different radial circumferences, and several groups of peripheral divergent holes are distributed from the outer side to the inner side of the outer ring anti-return holes, and the aperture of the peripheral divergent holes is smaller than the aperture of the central purge hole.

[0007] Preferably, the diameter of the outer ring anti-return holes is 15-25 mm, and the number is 8-30.

[0008] Preferably, the diameter of the central purge holes is 6-20 mm, the number is 5-60, and they are divided into 1-6 groups and arranged on the end plate. When the central purge holes are divided into several groups, the central purge holes of adjacent groups are staggered in radial direction.

[0009] Preferably, the diameter of the peripheral divergent holes is 1-4 mm, and the number is 5-15 times the number of the outer ring anti-return holes.

[0010] Furthermore, adjacent groups of peripheral divergent holes are arranged in a staggered distribution in the radial direction.

[0011] Preferably, the total opening area of ​​the air outlet holes is not greater than 1 / 2 of the total opening area of ​​the air inlet holes.

[0012] Preferably, the air inlet holes are divided into a plurality of groups, each group of air inlet holes has a plurality of air inlet holes, and the plurality of groups of air inlet holes are evenly distributed along different circumferences in the axial direction on the central tube.

[0013] Preferably, adjacent groups of air inlet holes are staggered in the axial direction.

[0014] Preferably, the diameter of the air inlet holes is 8-25 mm, and they are divided into 2-6 groups and arranged on the wall of the central tube, and the number of air inlet holes in each group is 8-16.

[0015] Preferably, the cone angle of the guide cone is 45°-120°.

[0016] Preferably, ear plates are provided on the front outer wall of the central tube, and the number of the ear plates is several (for example, 3), and the ear plates are evenly distributed along the same circumference on the outer wall of the central tube.

[0017] Preferably, the front side plate surface of the end plate is provided with an annular protrusion protruding forward, the outer edge diameter of the annular protrusion matches the inner diameter of the end of the center tube, the outer edge diameter of the end plate matches the outer diameter of the center tube or is slightly larger than the outer diameter of the center tube, and the annular protrusion is inserted into the end of the center tube from back to front and fixedly connected. The outer ring anti-return hole is located on the inner side of the annular protrusion.

[0018] An annular tube combustion chamber comprises a combustion chamber casing, a flame tube mounting plate is vertically fixedly provided in the combustion chamber casing, a plurality of flame tubes are fixedly mounted on the flame tube mounting plate, the plurality of flame tubes are evenly distributed on the flame tube mounting plate along the same circumference with the axis of the combustion chamber casing as the axis, an aerodynamic cone is provided in the combustion chamber casing, the aerodynamic cone adopts the aerodynamic cone of any one of the annular tube combustion chambers disclosed in the present invention, the aerodynamic cone is coaxially arranged in the combustion chamber casing, is located on the inner side of the flame tubes distributed along the annular shape, and has a radial spacing between each of the flame tubes, the end of the center tube is sealed and connected to the flame tube mounting plate, the flame tube mounting plate is provided with an aerodynamic cone mounting hole which is conformable to the end of the center tube, and the guide cone is located on the front side of the head end of each of the flame tubes.

[0019] Preferably, the total opening area of ​​the air inlet holes is not greater than 2.5 times the total opening area of ​​the air inlet holes of one of the flame tubes.

[0020] A nozzle is provided at the head end of each flame tube, and the guide cone is located in front of each nozzle and has a spacing between the guide cone and each nozzle in the axial direction.

[0021] A method for eliminating high-temperature backflow in an annular tube combustion chamber, wherein an aerodynamic cone of any one of the annular tube combustion chambers disclosed in the present invention is provided in a combustion chamber casing of the annular tube combustion chamber, wherein the aerodynamic cone is coaxially arranged in the combustion chamber casing, located on the inner side of a flame tube distributed along a ring shape, and a radial spacing is left between each of the flame tubes, the end of the center tube is sealed and connected to a flame tube mounting plate, the flame tube mounting plate is provided with an aerodynamic cone mounting hole conforming to the end of the center tube, the guide cone is located at the front side of the head end of each of the flame tubes, or the annular tube combustion chamber adopts any one of the annular tube combustion chambers disclosed in the present invention, a part of the cold air flow entering the annular tube combustion chamber passes through the air inlet into the aerodynamic cone, and then is ejected from the air outlet, forming a cold air impact potential core area behind the aerodynamic cone, suppressing the backflow formed at the center of the combustion chamber casing behind the flame tube by the high-temperature heat flow ejected from the flame tube distributed along the ring shape, and eliminating the backflow vortex core at the outlet center of the annular tube combustion chamber.

[0022] The beneficial effects of the present invention are: (1) A portion of the cold air flow entering the annular tube combustion chamber can enter the aerodynamic cone through the air inlet of the aerodynamic cone, and then be ejected from the air outlet at the end of the aerodynamic cone, forming a cold air impact potential core area behind the aerodynamic cone, which can effectively suppress the backflow formed by the high-temperature heat flow ejected from the flame tube distributed along the annular flame tube at the center of the combustion chamber casing behind the flame tube (the downstream center of the annular tube combustion chamber), eliminate the backflow vortex core at the outlet center of the annular tube combustion chamber, and avoid the high-temperature heat flow backflow from directly contacting or scouring the structure at the downstream center of the annular tube combustion chamber, causing ablation or damage; (2) The air outlet holes at the end of the aerodynamic cone adopt various forms and corresponding arrangements, so that the cold air impact potential core area formed behind the aerodynamic cone is strong at the periphery, full at the center, and cooled in place, which can effectively prevent the high-temperature heat flow ejected from the flame tube from flowing back and cool the aerodynamic cone at the same time; (3) Since a cold air impact potential core region is formed behind the aerodynamic cone, the formation of a large recirculation vortex downstream in the annular tube combustion chamber can be effectively avoided, thereby eliminating or slowing down flow oscillation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is an axial cross-sectional view of an embodiment of the pneumatic cone of the present invention; Figure 2 yes Figure 1 A perspective view of the aerodynamic cone of an embodiment; Figure 3 is a structural schematic diagram of an embodiment of the end plate of the present invention; Figure 4 yes Figure 3an axial cross-sectional view of the end plate of an embodiment; Figure 5 is an axial cross-sectional view of an embodiment of the annular tube combustion chamber of the present invention; Figure 6 yes Figure 5 Schematic diagram of the internal airflow flow of the annular can combustion chamber of the embodiment. DETAILED DESCRIPTION

[0024] All directional indications (such as front, back, inside, outside, etc.) in the embodiments of the present invention are only used to explain the relative position relationship between the components in a certain specific posture (as shown in the accompanying drawings), and do not constitute a limitation on the actual use direction. If the specific posture changes, the directional indication will also change accordingly.

[0025] See also Figure 1-Figure 4 The present invention discloses an aerodynamic cone of an annular tube combustion chamber, which includes a guide cone 1 and a center tube 2 from front to back. The guide cone is conical in shape with the cone angle facing forward. The center tube is cylindrical (cylindrical), and a plurality of air inlet holes 3 are provided on the tube wall for air intake of the center tube. The outer diameter of the bottom surface of the guide cone matches the outer diameter of the center tube, and the two are coaxially fixedly connected. An end plate 4 is fixedly sealed at the end of the center tube. The end plate is a circular plate, which is vertically arranged with the axis of the center tube. The end plate is densely covered with air outlet holes for exhausting the gas entering the center tube.

[0026] The air outlet holes preferably include outer ring return holes 5 , central purge holes 6 and peripheral divergent holes 7 .

[0027] There are multiple outer ring anti-return holes, which are evenly distributed on the same radial circle on the end plate near the outer edge of the plate surface. The diameter of the outer ring anti-return holes is preferably 15-25mm, such as 15mm, 20mm, 22mm or 25mm, and the number is 8-30.

[0028] The central purge hole is located on the inner side of the outer ring anti-return hole. There are multiple central purge holes, which are evenly distributed on the same circumference along the radial direction on the end plate, or the central purge holes are divided into several groups, and the number of central purge holes in each group is multiple, and several groups of central purge holes are evenly distributed on different circumferences along the radial direction on the end plate. The aperture of the central purge hole is smaller than the aperture of the outer ring anti-return hole. The aperture of the central purge hole is preferably 6-20mm, such as 6mm, 10mm, 15mm or 20mm, and the number is 5-60. The central purge holes can be divided into 1-6 groups and arranged on the end plate. When the central purge holes are divided into several groups, the central purge holes of adjacent groups are preferably staggered in the radial direction.

[0029] The peripheral diverging holes are located outside the central purge hole, and the peripheral diverging holes are divided into several groups. The number of peripheral diverging holes in each group is multiple, and several groups of peripheral diverging holes are evenly distributed along different circumferences in the radial direction on the end wall. Several groups of peripheral diverging holes are distributed from the outside to the inside of the outer ring return hole. The aperture of the peripheral diverging holes is smaller than the aperture of the central purge hole. The aperture of the peripheral diverging holes is preferably 1-4mm; for example, 1mm, 2mm, 3mm or 4mm, and the number is 5-15 times the number of the outer ring return holes. Adjacent groups of peripheral diverging holes are preferably staggered in the radial direction.

[0030] The total opening area of ​​the air outlet holes is preferably not greater than 1 / 2 of the total opening area of ​​the air inlet holes, so that the gas entering the central tube can form a jet when discharged from the air outlet holes.

[0031] The air inlet holes are preferably divided into several groups, each group of air inlet holes has a plurality of air inlet holes, and the several groups of air inlet holes are evenly distributed on different circumferences along the axial direction on the central tube, and adjacent groups of air inlet holes are preferably staggered and distributed in the axial direction to make the air intake of the central tube uniform. The aperture of the air inlet holes is preferably 8-25 mm, such as 8 mm, 10 mm, 20 mm or 25 mm, and they are divided into 2-6 groups and arranged on the wall of the central tube, and the number of air inlet holes in each group is 8-16.

[0032] The cone angle of the guide cone is preferably 45°-120°, for example 45°, 60°, 90° or 120°.

[0033] The front outer wall of the center tube is preferably provided with an ear plate 8 for installing the aerodynamic cone in the annular tube combustion chamber. The number of the ear plates is several (for example, 3), and the ear plates are evenly distributed along the same circumference on the outer wall of the center tube.

[0034] The front side plate surface of the end plate is preferably provided with an annular protrusion 9 protruding forward, the outer edge diameter of the annular protrusion matches the inner diameter of the end of the center tube, and is mainly used for positioning and connection with the center tube. The outer edge diameter of the end plate matches the outer diameter of the center tube or is slightly larger than the outer diameter of the center tube. The annular protrusion is inserted into the end of the center tube from back to front and fixedly connected (for example, bonded). The outer ring anti-return hole is located on the inner side of the annular protrusion.

[0035] See also Figure 5The present invention further discloses an annular tube combustion chamber, comprising a combustion chamber casing 10, wherein the combustion chamber casing is in a cylindrical shape, and a flame tube mounting plate 11 is vertically fixedly arranged in the combustion chamber casing, wherein the flame tube mounting plate is a circular plate, and is vertically arranged to be connected to the axis of the combustion chamber casing, and a plurality of flame tubes 12 are fixedly mounted on the flame tube mounting plate, and the plurality of flame tubes are evenly distributed on the flame tube mounting plate along the same circumference with the axis of the combustion chamber casing as the axis, and usually, the end of the flame tube is fixedly mounted on the flame tube mounting plate, and the flame tube mounting plate is provided with a flame tube mounting hole which is conformed to the end of each flame tube and has a one-to-one corresponding position, and a nozzle (the nozzle is provided with an air inlet passage for the incoming gas of the annular tube combustion chamber to enter the corresponding flame tube) 13 is arranged at the head end of each flame tube. An aerodynamic cone is provided in the combustion chamber casing, and the aerodynamic cone adopts the aerodynamic cone of any one of the annular tube combustion chambers disclosed in the present invention. The aerodynamic cone is coaxially arranged in the combustion chamber casing, located on the inner side of the flame tube distributed along the ring, and a radial distance is left between each of the flame tubes. The end of the center tube is sealed and connected to the flame tube mounting plate, and the flame tube mounting plate is provided with an aerodynamic cone mounting hole that is shaped according to the end of the center tube. The guide cone is located on the front side of the head end of each of the flame tubes, preferably on the front side of each of the nozzles, and a distance is left between each of the nozzles in the axial direction. It is mainly used to guide the incoming gas of the annular tube combustion chamber, so that most of the incoming gas can enter each of the flame tubes more smoothly to participate in combustion.

[0036] The total opening area of ​​the air inlet holes is preferably not greater than 2.5 times the total opening area of ​​the air inlet holes of one of the flame tubes to ensure that most of the incoming gas of the annular tube combustion chamber can enter the flame tube to participate in combustion without affecting the combustion efficiency of each of the flame tubes.

[0037] See also Figure 6The present invention also discloses a method for eliminating high-temperature backflow in an annular tube combustion chamber, wherein the annular tube combustion chamber comprises a combustion chamber casing, the combustion chamber casing is in a cylindrical shape, a flame tube mounting plate is vertically fixedly arranged in the combustion chamber casing, the flame tube mounting plate is a circular plate, and is vertically arranged with the axis of the combustion chamber casing, a plurality of flame tubes are fixedly mounted on the flame tube mounting plate, and the plurality of flame tubes are evenly distributed on the flame tube mounting plate along the same circumference with the axis of the combustion chamber casing as the axis, and the combustion chamber casing is provided with any one of the annular tube combustion chambers disclosed in the present invention. An aerodynamic cone of a tube combustion chamber, wherein the aerodynamic cone is coaxially arranged in the combustion chamber casing (can be fixedly connected to the inner wall of the combustion chamber casing through the ear plate), is located on the inner side of the flame tube distributed along the ring, and has a radial spacing between each of the flame tubes, the end of the center tube is sealed and connected to the flame tube mounting plate, and the flame tube mounting plate is provided with an aerodynamic cone mounting hole that is shaped like the end of the center tube, the guide cone is located on the front side of the head end of each of the flame tubes, or the annular tube combustion chamber adopts any one of the annular tube combustion chambers disclosed in the present invention. The incoming gas enters the annular tube combustion chamber from the upstream of the annular tube combustion chamber, and a part (most of) of the incoming gas enters the flame tube from the air inlet channel on the nozzle and the through holes on the body of the flame tube to participate in combustion. After the combustion, the incoming gas is ejected from the outlet of the flame tube to the downstream of the annular tube combustion chamber to form a high-temperature jet. Another part (a small part) of the incoming gas enters the aerodynamic cone through the air inlet hole and is ejected from the air outlet (low-temperature jet), forming a cold air impact potential core area behind the aerodynamic cone, suppressing the backflow of the high-temperature heat flow ejected from the flame tube distributed along the annular distribution at the center of the combustion chamber casing behind the flame tube, eliminating the backflow vortex core at the outlet center of the annular tube combustion chamber, and avoiding the backflow of the high-temperature heat flow directly contacting or scouring the structure at the downstream center in the annular tube combustion chamber, causing ablation or damage.

[0038] Among the jets ejected from the air outlet, the low-temperature jets ejected from the outer ring return holes (large diameter and small spacing) are powerful cold air flows, which can realize potential core flow over a longer distance, and mainly play the role of suppressing the high-temperature jets at the outlet of each flame tube from rewinding and refluxing toward the center of the combustion chamber casing; the low-temperature jets ejected from the central purge holes mainly play the role of filling the downstream central negative pressure area of ​​the annular tube combustion chamber, and avoiding the peripheral heat flow reflux caused by the existence of the central negative pressure downstream of the potential core flow of the outer ring return holes; the low-temperature jets ejected from the peripheral divergent holes (small spacing and closer proximity) mainly play the role of cooling and protecting the end plate, and preventing the end plate from being washed by the high-temperature return hot air flow at the outlet of the flame tube.

[0039] The pneumatic cone is hollow, light in weight, simple in structure, easy to process, and low in cost.

[0040] The aerodynamic cone of any annular can combustor of the present invention can be used for any annular can combustor of the present invention.

[0041] Any annular can combustor of the present invention may also adopt the aerodynamic cone of any annular can combustor of the present invention.

[0042] Unless otherwise specified or one preferred or optional technical means is a further limitation of another technical means, all preferred and optional technical means disclosed in the present invention can be arbitrarily combined to form several different technical solutions.

Claims

1. The aerodynamic cone of the annular tube combustion chamber is characterized by From front to back, it includes a guide cone and a center tube. The guide cone is conical in shape with the cone angle facing forward. The center tube is cylindrical in shape with multiple air inlet holes on the tube wall. The outer diameter of the bottom surface of the guide cone matches the outer diameter of the center tube, and the two are coaxially fixedly connected. The end of the center tube is fixedly sealed with an end plate, and the end plate is densely covered with air outlet holes.

2. The aerodynamic cone of the annular can combustion chamber according to claim 1, characterized in that The air outlet holes include outer ring anti-return holes, central purge holes and peripheral divergent holes. The number of the outer ring anti-return holes is multiple and they are evenly distributed on the same radial circumference of the end plate near the outer edge of the plate surface. The central purge hole is located on the inner side of the outer ring anti-return holes. The number of the central purge holes is multiple and they are evenly distributed on the same radial circumference of the end plate, or the central purge holes are divided into several groups, each group of central purge holes has multiple numbers, and several groups of central purge holes are evenly distributed on different radial circumferences of the end plate. The aperture of the central purge hole is smaller than the aperture of the outer ring anti-return holes. The peripheral divergent holes are located on the outer side of the central purge holes. The peripheral divergent holes are divided into several groups, each group of peripheral divergent holes has multiple numbers, and several groups of peripheral divergent holes are evenly distributed on the end wall along different radial circumferences. Several groups of peripheral divergent holes are distributed from the outer side to the inner side of the outer ring anti-return holes, and the aperture of the peripheral divergent holes is smaller than the aperture of the central purge hole.

3. The aerodynamic cone of the annular can combustion chamber according to claim 2, characterized in that The total opening area of ​​the air outlet holes is not greater than 1 / 2 of the total opening area of ​​the air inlet holes.

4. The aerodynamic cone of the annular can combustion chamber according to claim 1, characterized in that The air inlet holes are divided into a plurality of groups, each group of air inlet holes has a plurality of air inlet holes, and the air inlet holes in the plurality of groups are evenly distributed along different circumferences in the axial direction on the central tube.

5. The aerodynamic cone of the can-annular combustion chamber according to claim 4, characterized in that Adjacent groups of air inlet holes are arranged in an axially staggered distribution.

6. The aerodynamic cone of the annular can combustion chamber according to claim 1, characterized in that The cone angle of the guide cone is 45°-120°.

7. The aerodynamic cone of the can-annular combustion chamber according to claim 1, characterized in that The front outer wall of the central tube is provided with a plurality of ear plates, which are evenly distributed along the same circumference on the outer wall of the central tube.

8. An annular tube combustion chamber, comprising a combustion chamber casing, wherein a flame tube mounting plate is vertically fixedly disposed in the combustion chamber casing, a plurality of flame tubes are fixedly mounted on the flame tube mounting plate, and the plurality of flame tubes are evenly distributed on the flame tube mounting plate along the same circumference with the axis of the combustion chamber casing as the axis, characterized in that An aerodynamic cone is provided in the combustion chamber casing, and the aerodynamic cone adopts the aerodynamic cone of the annular tube combustion chamber described in any one of claims 1-7. The aerodynamic cone is coaxially arranged in the combustion chamber casing, located on the inner side of the flame tube distributed along the ring, and a radial distance is left between each of the flame tubes. The end of the center tube is sealed and connected to the flame tube mounting plate, and the flame tube mounting plate is provided with an aerodynamic cone mounting hole that is shaped like the end of the center tube. The guide cone is located on the front side of the head end of each of the flame tubes.

9. The annular canal combustion chamber according to claim 8, characterized in that The total opening area of ​​the air inlet holes is not greater than 2.5 times the total opening area of ​​the air inlet holes of one of the flame tubes.

10. A method for eliminating high temperature reflux in an annular tube combustion chamber, characterized in that The combustion chamber casing of the annular tube combustion chamber is provided with an aerodynamic cone of the annular tube combustion chamber described in any one of claims 1 to 7, the aerodynamic cone is coaxially arranged in the combustion chamber casing, located on the inner side of the flame tube distributed along the ring shape, and a radial distance is left between each of the flame tubes, the end of the center tube is sealed and connected to the flame tube mounting plate, the flame tube mounting plate is provided with an aerodynamic cone mounting hole conforming to the end of the center tube, the guide cone is located on the front side of the head end of each of the flame tubes, or the annular tube combustion chamber adopts the annular tube combustion chamber described in any one of claims 8 or 9, a part of the cold air flow entering the annular tube combustion chamber passes through the air inlet into the aerodynamic cone, and then is ejected from the air outlet, forming a cold air impact potential core area behind the aerodynamic cone, suppressing the backflow formed by the high-temperature heat flow ejected from the flame tube distributed along the ring shape at the center of the combustion chamber casing behind the flame tube, and eliminating the backflow vortex core at the outlet center of the annular tube combustion chamber.

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