Energy-saving burner with adjustable flame shape and heating equipment

Abstract

The invention provides an energy-saving burner with an adjustable flame shape and heating equipment, and belongs to the technical field of gas power equipment. The combustor comprises a combustion shell, a fuel premixing chamber and an atomizer. Wherein the combustion shell is provided with a first kerosene inlet, a first oxygen inlet and a flame outlet; the fuel premixing chamber is detachably arranged in the cavity of the combustion shell; the fuel premixing chamber is provided with a premixing channel, a second kerosene inlet communicated with the first kerosene inlet, a second oxygen inlet communicated with the first oxygen inlet and a material outlet, and the premixing channel, the second kerosene inlet, the second oxygen inlet and the material outlet are communicated; one end of the atomizer is arranged at the material outlet, and the other end is communicated with the flame outlet; and the igniter is used for igniting the material sprayed by the atomizer. The combustor can simulate the real service environment of a detection part and has the effects of adjustable flame, stable combustion, cost reduction and the like.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of gas power equipment, in particular, to an energy-saving burner with adjustable flame shape and heating equipment. BACKGROUND

[0002] The aero-engine is known as the "jewel on the crown of modern industry", the tip of the equipment manufacturing industry, and the national treasure. The turbine blade of the aero-engine is known as the heart of the aero-engine. With the gradual increase of the demand for thrust-to-weight ratio, the temperature in the engine is also getting higher and higher, which puts higher requirements on the performance of core components such as turbine blades, turbine discs, and casings. Therefore, other types of ground test methods are needed to examine the performance of key components before installation.

[0003] Currently, the core engine and the overall test of the aero-engine focus on the integrated performance of the components, and it is also the only way to examine the performance of the components (such as turbine working blades). However, this method not only has high cost (the aero-engine turbine working blade is generally two levels, each level has about 60-70 blades, and the current price of each blade is about 100,000 yuan. Even if other factors are not considered, only the blade is considered, the cost of one time is tens of millions of yuan), but also the working environment of the aero-engine is harsh, and there are many influencing factors. At the same time, due to the compact structure of the aero-engine, it is extremely difficult to install sensors, and it is difficult to obtain the working state parameters (temperature, stress, etc.) of the turbine working blade completely. At the same time, during the test, even if the blade fails, it is also very difficult to infer the failure mechanism from the measurement data. If the working blade breaks down in advance, the damage is also serious. Therefore, the core engine and the overall test cannot be used as the development test of the components (such as turbine working blades), and cannot replace the component (such as blade) level test, and a professional test system for simulating the flight in the air must be developed.

[0004] It should be noted that the information disclosed in the above background section is only used to strengthen the understanding of the background of the present disclosure, and therefore can include information that does not constitute prior art known to those of ordinary skill in the art. SUMMARY

[0005] The purpose of the present disclosure is to overcome the shortcomings of the prior art, and to provide an energy-saving burner with adjustable flame shape and heating equipment. The purpose is to reduce the manufacturing cost while simulating the real conditions of the components in the service environment.

[0006] According to a first aspect of the present disclosure, an energy-saving burner with adjustable flame shape is provided, which comprises a combustion shell, a fuel premixing chamber, an atomizer, and an igniter. The combustion shell has a first kerosene inlet, a first oxygen inlet, and a flame outlet. The fuel premixing chamber is detachably arranged in the cavity of the combustion shell; the fuel premixing chamber is provided with a premixing channel, a second kerosene inlet communicated with the first kerosene inlet, a second oxygen inlet arranged in communication with the first oxygen inlet, and a material outlet. One end of the atomizer is arranged at the material outlet, and the other end is arranged in communication with the flame outlet. The igniter is used for igniting the material sprayed by the atomizer.

[0007] According to an embodiment of the present disclosure, the combustion shell comprises a first shell, a second shell and a third shell which are sequentially detachably connected; The first shell and the second shell form a containing chamber for mounting the fuel premixing chamber. The first kerosene inlet and the first oxygen inlet are arranged on the first shell. The flame outlet is arranged on the third shell.

[0008] According to an embodiment of the present disclosure, the first shell is provided with a kerosene channel. The second kerosene inlet has a plurality of second kerosene inlets which are uniformly distributed along the circumference of the fuel premixing chamber. The first kerosene inlet, the kerosene channel and the plurality of second kerosene inlets are arranged in communication.

[0009] According to an embodiment of the present disclosure, the combustion shell is further provided with a first material inlet. The fuel premixing chamber is provided with a second material inlet in communication with the first material inlet, and the second material inlet is arranged in communication with the premixing channel.

[0010] According to an embodiment of the present disclosure, the burner further comprises a pressure regulating valve. The pressure regulating valve is arranged at the first kerosene inlet for regulating the pressure of kerosene entering the first kerosene inlet.

[0011] According to an embodiment of the present disclosure, the combustion shell is further provided with an air inlet. The air inlet is arranged in communication with the containing chamber.

[0012] According to an embodiment of the present disclosure, the third shell comprises an inner shell and an outer shell arranged outside the inner shell. The outer shell is provided with a liquid inlet; The inner shell and the outer shell form a cooling channel therebetween, and the cooling channel is arranged in communication with the liquid inlet.

[0013] According to an embodiment of the present disclosure, the inner shell has a plurality of baffle groups distributed along the circumference of the side close to the outer shell; The baffle groups include a first baffle and a second baffle; The length direction of the first baffle and the second baffle is the same as the length direction of the inner shell; The side of the first baffle close to the second shell and the side of the second baffle away from the second shell both have notches.

[0014] According to an embodiment of the present disclosure, the distance between the first baffle and the second baffle gradually increases along the radial direction of the inner shell.

[0015] According to a second aspect of the present disclosure, a heating device is provided, which includes the energy-saving burner with adjustable flame shape.

[0016] It should be understood that the above general description and the following detailed description are only exemplary and explanatory, and cannot limit the present disclosure. BRIEF DESCRIPTION OF DRAWINGS

[0017] The drawings incorporated into the specification and forming a part of the specification, show embodiments consistent with the present disclosure, and together with the specification, serve to explain the principles of the present disclosure. It is obvious that the drawings in the following description are only some embodiments of the present disclosure, and other drawings can be obtained by those skilled in the art without creative labor.

[0018] Figure 1 For an embodiment of the present disclosure, the overall structure of the burner is shown in the schematic diagram.

[0019] Figure 2 For an embodiment of the present disclosure, the structure of the burner is shown in the schematic diagram from another perspective.

[0020] Figure 3 For an embodiment of the present disclosure, the sectional view of the burner is shown.

[0021] Figure 4 For Figure 3 the enlarged view of part A.

[0022] Figure 5 For an embodiment of the present disclosure, the sectional view of the burner is shown from another perspective.

[0023] Figure 6 For Figure 5 the enlarged view of part B.

[0024] Figure 7For an embodiment of the present disclosure, a schematic view of a structure of a fuel premixing chamber.

[0025] Figure 8 For an embodiment of the present disclosure, a schematic view of a structure of a third housing.

[0026] Figure 9 For an embodiment of the present disclosure, a sectional view of the third housing.

[0027] Figure 10 For an embodiment of the present disclosure, a schematic view of an installation step of a burner.

[0028] Explanation of Reference Numerals: 1, combustion housing; 11, first housing; 111, first kerosene inlet; 112, first oxygen inlet; 113, kerosene passage; 114, first material inlet; 115, air inlet; 116, first water injection port; 12, second housing; 121, second sealing ring groove; 122, second water injection port; 13, third housing; 131, flame outlet; 132, inner housing; 133, outer housing; 1331, liquid inlet; 1332, cooling passage; 134, baffle group; 1341, first baffle; 1342, second baffle; 14, accommodation chamber; 15, notch; 2, fuel premixing chamber; 21, premixing passage; 22, second kerosene inlet; 23, second oxygen inlet; 24, material outlet; 25, second material inlet; 26, third sealing ring groove; 3, atomizer; 31, first sealing ring groove; 4, igniter; 41, spark plug; 5, pressure regulating valve; 6, oxygen one-way valve. DETAILED DESCRIPTION

[0029] Example embodiments now will be described more fully hereinafter with reference to the accompanying drawings. Example embodiments, however, can be implemented in many different forms and should not be construed as limited to the implementations set forth herein; rather, these implementations are provided so that this disclosure will be thorough and complete, and will fully convey the scope of example embodiments to those skilled in the art. Like reference numerals refer to like elements throughout the specification. Moreover, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this example embodiment belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and the present disclosure, and will not be interpreted in an overly literal sense unless expressly so defined herein.

[0030] Although relative terms are used in this specification, such as "upper", "lower", to describe one component's relationship to another component of the icon, these terms are used herein for convenience only and are not intended to limit the scope of the disclosure to any one example described herein. It is to be understood that, if the icon were inverted, then the described "upper" component would become the "lower" component. When a structure is "on" another structure, it can mean that the structure is formed integrally with the other structure or that the structure is "directly" on the other structure or that the structure is "indirectly" on the other structure via another structure.

[0031] In the related art, for an aero-engine core machine (it should be noted that the same applies to other mechanical components), overall testing focuses on the integrated performance of the components, and is also the only way to test the performance of the components (such as turbine working blades). However, this method has a high detection cost, and for aero-engine components, the working environment is harsh, and there are many influencing factors, so it is difficult to accurately measure the working state parameters of the aero-engine components.

[0032] Based on this, the disclosure provides an energy-saving burner with adjustable flame shape and a heating device. The burner and the heating device applying the burner can simulate the real service environment of the aero-engine while reducing the detection cost.

[0033] The structure of the burner will be described in detail below in combination with the related drawings: In the embodiment of the disclosure, referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 7 , the burner comprises a combustion shell 1, a fuel premixing chamber 2 and an atomizer 3; the combustion shell 1 has a first kerosene inlet 111, a first oxygen inlet 112 and a flame outlet 131; the fuel premixing chamber 2 is detachably arranged in the cavity of the combustion shell 1; the fuel premixing chamber 2 has a premixing channel 21, a second kerosene inlet 22 communicating with the first kerosene inlet 111, a second oxygen inlet 23 arranged in communication with the first oxygen inlet 112 and a material outlet 24, wherein the premixing channel 21, the second kerosene inlet 22, the second oxygen inlet 23 and the material outlet 24 are arranged in communication; one end of the atomizer 3 is arranged at the material outlet 24, and the other end is arranged in communication with the flame outlet 131; the igniter 4 is used for igniting the material sprayed by the atomizer 3.

[0034] Specifically, when the burner is needed to heat the detection component to simulate the service environment, aviation kerosene is supplied to the first kerosene inlet 111, the aviation kerosene enters the premixing channel 21 through the first kerosene inlet 111, oxygen is supplied to the first oxygen inlet 112, the oxygen enters the premixing channel 21, the oxygen and the aviation kerosene are fully mixed in the premixing channel 21, the mixed aviation kerosene and oxygen are atomized under the action of the atomizer 3, the igniter 4 is turned on, the igniter 4 ignites the mixture of oxygen and aviation kerosene sprayed by the atomizer 3, and the mixture of oxygen and aviation kerosene is combusted to heat the detection component.

[0035] In some embodiments, referring to Figure 3 , Figure 7 The side of the atomizer 3 close to the fuel premixing chamber 2 is provided with a plurality of first sealing ring grooves 31, and a first sealing ring can be arranged in the first sealing ring groove 31 (not specifically labeled in the present application). The peripheral side of the atomizer 3 is provided with a grid channel (not specifically labeled in the drawings), and the material in the premixing channel 21 can be fully atomized by passing through the grid channel under the pushing of high-pressure gas. It can be understood that the atomizer 3 described in the present application is used for atomizing the mixture of aviation kerosene and oxygen in the premixing channel 21, which is a technical field known to those skilled in the art, and will not be described here.

[0036] In the remaining embodiments, referring to Figure 1 , Figure 2 The first oxygen inlet 112 can also be provided with an oxygen one-way valve 6; the oxygen one-way valve 6 is used to connect the combustion shell 1 and the oxygen supply pipe, so as to ensure the one-way flow of oxygen while supplying oxygen, and prevent the phenomenon of backfire.

[0037] In some embodiments of the present disclosure, the combustion shell 1 comprises a first shell 11, a second shell 12 and a third shell 13 which are detachably connected in sequence; the first shell 11 and the second shell 12 form a containing chamber 14 for mounting the fuel premixing chamber 2; the first kerosene inlet 111 and the first oxygen inlet 112 are arranged on the first shell 11; and the flame outlet 131 is arranged on the third shell 13.

[0038] In some examples, the bottom of the first shell 11 can be provided with a threaded hole (not specifically labeled in the present application), and the first shell 11 can be fixed on the test platform through the threaded hole, facilitating the disassembly and installation of the burner during the test.

[0039] Further, referring to Figure 2 The first shell 11 can also be provided with a first water inlet 116; when the burner is working, cooling water can be added to the first water inlet 116, and the added cooling water can cool the first shell 11 to improve the service life of the first shell 11.

[0040] In some embodiments, the igniter 4 can include a spark plug 41, a high-voltage pack, and a cable (not shown in the drawings). The spark plug 41 is mounted on the second shell 12, and in some embodiments, the connection between the spark plug 41 and the second shell 12 can be insulated by a rubber pad. The spark plug 41 is located at the outlet of the atomizer 3 for igniting the fully atomized material. The high-voltage pack is connected to the spark plug 41 for converting low voltage to high voltage to provide high voltage to the spark plug 41. The cable is used to connect the high-voltage pack and the spark plug 41. When the detection component is heated, the high-voltage pack can be mounted on the test platform, and two cables (not shown in the drawings) can be provided. One cable is connected to the spark plug 41, and the other cable is fixed to the second shell 12 by a top screw.

[0041] As an example, one end of the second shell 12 can be connected to the first shell 11 by a bolt, and the other end of the second shell 12 can be connected to the third shell 13 by a bolt.

[0042] As another example, referring to Figure 2 、 Figure 3 , a second sealing ring groove 121 can be provided at the connection between the second shell 12 and the first shell 11, and a second sealing ring (not shown in the drawings) can be provided in the second sealing ring groove 121. The provided second sealing ring can prevent leakage of the atomized material.

[0043] In some examples, referring to Figure 7 , a third sealing ring groove 26 can be provided at the side of the fuel premixing chamber 2 close to the first shell 11 and the middle of the fuel premixing chamber 2, and a third sealing ring (not shown in the drawings) can be provided in the third sealing ring groove 26.

[0044] Further, in some embodiments, referring to Figure 3 , the second shell 12 has a second water inlet 122. During the operation of the burner, cooling water can be added to the second water inlet 122. The added cooling water can effectively cool the second shell 12 to ensure the service life of the burner.

[0045] Further, the shape and size of the flame can be adjusted by changing the size of the inner cavity of the second shell 12. It should be noted that the size of the inner cavity of the second shell 12 is not limited in the embodiments of the present disclosure.

[0046] In some embodiments of the present disclosure, referring to Figure 2 、 Figure 3 and Figure 4The first shell 11 has a kerosene channel 113; the second kerosene inlet 22 has a plurality of second kerosene inlets 22 which are uniformly distributed along the circumference of the fuel premixing chamber 2; wherein the first kerosene inlet 111, the kerosene channel 113 and the plurality of second kerosene inlets 22 are in communication. Specifically, when adding aviation kerosene into the premixing channel 21, aviation kerosene is first added to the first kerosene inlet 111, and then enters the kerosene channel 113. The aviation kerosene in the kerosene channel 113 enters the premixing channel 21 through the plurality of second kerosene inlets 22, thereby achieving the addition of aviation kerosene into the premixing channel 21. The plurality of second kerosene inlets 22 allows aviation kerosene to enter the premixing channel 21 from different directions of the fuel premixing chamber 2, thereby improving the mixing effect of oxygen and aviation kerosene, and further allowing the burner to fully combust.

[0047] In some embodiments of the present disclosure, referring to Figure 1 、 Figure 2 The combustion shell 1 further has a first material inlet 114; the fuel premixing chamber 2 has a second material inlet 25 which is in communication with the first material inlet 114, and the second material inlet 25 is in communication with the premixing channel 21.

[0048] As an example, the first material inlet 114 can be connected to sand, salt spray and other materials. When sand is sprayed onto the detection component through the first material inlet 114, the second material inlet 25 and the flame port, the service condition of the engine in the desert can be simulated. When salt spray is sprayed onto the detection component through the first material inlet 114, the second material inlet 25 and the flame port, the service condition of the engine on the ocean can be simulated. Of course, in other embodiments, the first material inlet 114 can be connected to other materials to simulate the service condition of the engine in different environments, which will not be described herein.

[0049] In some embodiments of the present disclosure, referring to Figure 3 、 Figure 4 The burner further comprises a pressure regulating valve 5; the pressure regulating valve 5 is arranged at the first kerosene inlet 111 and is used to regulate the pressure of kerosene entering the first kerosene inlet 111. More specifically, one end of the pressure regulating valve 5 is connected to the aviation kerosene delivery pump through a pipeline, and the other end is connected to the first kerosene inlet 111. When the aviation kerosene delivery pump delivers aviation kerosene, the amount of aviation kerosene added can be controlled by adjusting the pressure regulating valve 5, so as to adjust the size of the flame of the burner.

[0050] In some embodiments of the present disclosure, referring to Figure 5 、 Figure 6The combustion shell 1 is further provided with an air inlet 115; the air inlet 115 is in communication with the containing chamber 14. When the burner is in operation, external air can enter the containing chamber 14 through the air inlet 115, and the external air contacts the fuel premixing chamber 2 (the fuel premixing chamber 2 generates a certain amount of heat when the burner is in operation) to cool the fuel premixing chamber 2, which helps to improve the service life of the fuel premixing chamber 2, and further improves the service life of the burner.

[0051] In some embodiments of the present disclosure, referring to Figure 8 、 Figure 9 The third shell 13 comprises an inner shell 132 and an outer shell 133 arranged outside the inner shell 132; the outer shell 133 is provided with a liquid inlet 1331; the inner shell 132 and the outer shell 133 form a cooling channel 1332 therebetween, and the cooling channel 1332 is in communication with the liquid inlet 1331.

[0052] It can be understood that when the burner is in operation, the flame is sprayed out through the third shell 13, and the third shell 13 needs to withstand a large amount of heat. Therefore, the third shell 13 may be damaged after long-term use. Based on this, in the embodiments of the present disclosure, cooling liquid can be added into the liquid inlet 1331 when the burner is in operation. The cooling liquid enters the cooling channel 1332, and the cooling liquid moves in the cooling channel 1332 to cool the third shell 13, thereby improving the service life of the cooler.

[0053] In this embodiment, the inner shell 132 is provided with a plurality of baffle groups 134 near the side close to the outer shell 133; each baffle group 134 comprises a first baffle 1341 and a second baffle 1342; the length direction of the first baffle 1341 and the second baffle 1342 is the same as the length direction of the inner shell 132; and the side of the first baffle 1341 close to the second shell 12 and the side of the second baffle 1342 away from the second shell 12 are both provided with a notch 15. It can be understood that the notch 15 on the side of the first baffle 1341 close to the second shell 12, the notch 15 on the side of the second baffle 1342 away from the second shell 12, and the spacing between the first baffle 1341 and the second baffle 1342 form a section of the cooling channel 1332. The plurality of baffle groups 134 are connected to each other to form the cooling channel 1332. In the embodiments of the present disclosure, the cooling channel 1332 can increase the residence time of the cooling liquid in the inner shell 132 and the outer shell 133, thereby improving the cooling effect of the third shell 13.

[0054] As an example, in one embodiment, one end of the cooling channel 1332 can be "S" shaped. It should be noted that in the remaining embodiments, the shape of the cooling channel 1332 is not limited to this, and the present application does not repeat it.

[0055] In some embodiments of the present disclosure, the distance between the first baffle 1341 and the second baffle 1342 gradually increases along the radial direction of the inner shell 132. In this way, when the cooling liquid enters the cooling channel 1332 formed by the inner shell 132 and the outer shell 133, the flow rate of the cooling liquid between the outer shell 133 and the inner shell 132 can be further slowed down, thereby increasing the residence time of the cooling liquid between the outer shell 133 and the inner shell 132, and further improving the cooling effect on the third shell 13.

[0056] It has been verified that the gas flame environment generated by the combustor of the present application is consistent with the real service environment of the high-temperature parts of the aero-engine; the gas temperature is high, which can reach 1800℃ at the highest, meeting the examination requirements of conventional detection parts (the temperature of conventional examination parts is between 1100-1800℃). At the same time, the combustor provided by the present application adopts a modular design (the first shell 11, the second shell 12 and the second shell 12 are detachably connected with each other), which can effectively reduce the preparation cost, maintenance cost and the like.

[0057] In summary, the combustor and the heating equipment applying the same provided by the present application can perform certain examination on the high-temperature parts (for example, turbine blades, stationary vanes, moving vanes, turbine outer rings and turbine discs, etc.) before the whole engine (it is to be noted that the object of the combustor and the heating equipment provided by the present application is not limited to the engine, but can be other mechanical parts) is tested, which not only can timely find faults, but also can update the design system, shorten the development cycle, shorten the troubleshooting time, examine and verify the new materials, new processes and new structures before installation, reveal the cooling and failure mechanism, establish the failure model, form the design method, ensure the safe service and provide strong support for the development of the aero-engine.

[0058] The present application further provides a mounting method of the combustor, referring to Figure 10 The mounting method comprises: S1: determining the fuel premixing chamber 2 according to the size of the detection part.

[0059] S2: mounting the fuel premixing chamber 2 into the cavity of the first shell 11.

[0060] S3: connecting the atomizer 3 with the fuel premixing chamber 2.

[0061] S4: connecting the second shell 12 with the first shell 11.

[0062] S5: connecting the third shell 13 with the second shell 12.

[0063] S6: fixing the pressure regulating valve 5 at the first kerosene inlet 111 and fixing the oxygen one-way valve 6 at the first oxygen inlet 112.

[0064] Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the features disclosed herein. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.

Claims

1. An energy-saving burner with adjustable flame shape, characterized in that, The burner comprises a combustion shell, a fuel premixing chamber, an atomizer and an igniter; The combustion shell is provided with a first kerosene inlet, a first oxygen inlet and a flame outlet; The fuel premixing chamber is detachably arranged in the cavity of the combustion shell; the fuel premixing chamber is provided with a premixing passage, a second kerosene inlet communicated with the first kerosene inlet, a second oxygen inlet arranged in communication with the first oxygen inlet and a material outlet; the premixing passage, the second kerosene inlet, the second oxygen inlet and the material outlet are arranged in communication; One end of the atomizer is arranged at the material outlet, and the other end is arranged in communication with the flame outlet; The igniter is used for igniting the material sprayed by the atomizer.

2. The energy-saving burner with adjustable flame shape according to claim 1, characterized in that, The combustion shell comprises a first shell, a second shell and a third shell which are sequentially detachably connected; The first shell and the second shell form a containing chamber for mounting the fuel premixing chamber; The first kerosene inlet and the first oxygen inlet are arranged on the first shell; The flame outlet is arranged on the third shell.

3. The energy-saving burner with adjustable flame shape according to claim 2, characterized in that, The first shell is provided with a kerosene passage; The second kerosene inlet has a plurality of second kerosene inlets which are uniformly distributed along the circumference of the fuel premixing chamber; The first kerosene inlet, the kerosene passage and the plurality of second kerosene inlets are arranged in communication.

4. The energy saving burner with adjustable flame shape according to claim 1, characterized in that, The combustion shell is further provided with a first material inlet; The fuel premixing chamber is provided with a second material inlet arranged in communication with the first material inlet; the second material inlet is arranged in communication with the premixing passage.

5. The energy saving burner with adjustable flame shape according to claim 1, characterized in that, The burner further comprises a pressure regulating valve; The pressure regulating valve is arranged at the first kerosene inlet and is used for regulating the pressure of kerosene entering the first kerosene inlet.

6. The energy saving burner with adjustable flame shape according to claim 2, characterized in that, The combustion shell is further provided with an air inlet; The air inlet is arranged in communication with the containing chamber.

7. The energy saving burner with adjustable flame shape according to claim 2, characterized in that, The third shell comprises an inner shell and an outer shell arranged outside the inner shell; The outer shell is provided with a liquid inlet; The inner shell and the outer shell form a cooling passage therebetween; the cooling passage is arranged in communication with the liquid inlet.

8. The energy saving burner with adjustable flame shape according to claim 7, characterized in that, The inner shell is provided with a plurality of baffle groups distributed along the circumference thereof on the side close to the outer shell; The baffle group comprises a first baffle and a second baffle; The length direction of the first baffle and the second baffle is the same as the length direction of the inner shell; The side of the first baffle close to the second shell and the side of the second baffle away from the second shell are both provided with notches.

9. The energy saving burner with adjustable flame shape according to claim 8, characterized in that, In the radial direction of the inner shell, the distance between the first baffle and the second baffle gradually increases.

10. A heating apparatus, characterized by, The energy-saving burner with adjustable flame shape comprises the energy-saving burner with adjustable flame shape.

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