Miniature turbine generator capable of combusting various kinds of fuel oil and gas distribution control method of miniature turbine generator

Abstract

The generator comprises a heat exchanger and a controllable rotational flow assembly, a fuel oil flow channel, an air inlet flow channel and an air outlet flow channel are formed in the heat exchanger, an oil temperature detector is arranged at the front end of a fuel oil distribution system, and the controllable rotational flow assembly is arranged at the rear end of the fuel oil distribution system. The controllable rotational flow assembly comprises a controllable rotational flow ring and a ring body driving mechanism, the controllable rotational flow ring is sleeved with the inner ring wall face of the annular combustion chamber and can rotate, the controllable rotational flow ring comprises a ring body and guide vanes, rotational flow adjusting holes are annularly and evenly distributed in the ring body, and the guide vanes are axially arranged on one side edges of the rotational flow adjusting holes. The oil temperature detector extends from the side edge to the upper part of the rotational flow adjusting hole, extends into the rotational flow hole, has rotational flow guide inclination, and feeds back an oil temperature signal to the ring body driving mechanism; according to the generator and the control method thereof, through the design that regenerative heating and rotational flow are matched, the containment of the micro turbine generator to high-viscosity fuel oil can be enhanced, and the ignition and combustion performance of the high-viscosity fuel oil is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of turbo generators, and specifically refers to a micro turbo generator capable of burning multiple fuels and its gas volume distribution control method. Background Art

[0002] In the fields of distributed energy and mobile power, micro turbo generators are becoming a new solution to subvert traditional technologies. With characteristics such as compact structure, high power density, and fast response speed, it shows unique advantages in unmanned aerial vehicle power systems, vehicle-mounted hybrid power generation, and discrete power supply scenarios. Compared with traditional generators, micro turbo generators do not require a complex crankshaft structure, have less vibration, and stronger fuel adaptability, especially suitable for application scenarios sensitive to space. However, the fuel adaptability of this technology is insufficient. Due to poor atomization effect of high-viscosity fuel, its combustion efficiency is less than satisfactory.

[0003] The evaporation tube combustion chamber can achieve better fuel atomization and evaporation effects under low-pressure conditions. The atomization and evaporation characteristics of the fuel directly affect the combustion sufficiency and combustion efficiency of the combustion chamber. After the fuel is atomized and evaporated through the evaporation tube, air is injected through the swirl holes, main combustion holes, supplementary combustion holes, etc. distributed on the combustion chamber wall surface to form stable combustion with the fuel. In this process, the fuel temperature, the flow channel organization in the axial and radial directions of the combustion chamber not only determine the combustion stability and emission level, but also affect the uniformity of the temperature field distribution, thus affecting the life of the turbine blades and the power generation efficiency.

[0004] There is little research on burning high-viscosity fuel and adjusting the reasonable swirl organization of the combustion chamber according to the real-time temperature and viscosity of the preheated fuel in the existing turbo generators. The atomization and evaporation effect of high-viscosity fuel in the evaporation tube is poor, and it is difficult to form finer liquid droplet particles, deteriorating the combustion effect in the combustion chamber; by heating, the viscosity of high-viscosity fuel can be reduced, but setting up a dedicated fuel heater will increase the overall structure of the generator and increase additional energy consumption. Therefore, considering using the regenerative heat technology to heat the high-viscosity fuel, the internal swirl organization of the existing turbo generators placed in the combustion chamber is basically fixed and unchanged, and it is impossible to match the appropriate swirl dynamic organization by real-time monitoring of the fuel preheating temperature, which limits the fuel inclusiveness of the turbo generator. Summary of the Invention

[0005] The purpose of the present invention is to overcome the defects in the prior art and provide a micro turbo generator capable of burning multiple fuels and its gas volume distribution control method to overcome one or more problems caused by the limitations and defects of the related technologies to a certain extent.

[0006] To achieve the above purpose, the technical solution of the present invention is as follows:

[0007] A micro turbine generator capable of burning multiple fuels, comprising an outer casing, an inner casing, a fuel distribution system, an annular combustion chamber and a compressor impeller. An air flow passage located behind the compressor impeller is formed between the outer casing and the inner casing. It further includes a heat exchanger and a controllable swirl component;

[0008] The heat exchanger is arranged on the air flow passage. A fuel flow passage, an air inlet flow passage and an exhaust flow passage are arranged in the heat exchanger. The fuel in the fuel flow passage and the intake air are heated by the exhaust heat. The front end of the fuel flow passage is connected to a fuel supply pipe, and the rear end is connected to the fuel distribution system. An oil temperature detector is arranged at the front end of the fuel distribution system;

[0009] The controllable swirl component includes a controllable swirl ring and a ring body driving mechanism. The controllable swirl ring is sleeved inside the inner wall of the annular combustion chamber and can rotate. The controllable swirl ring includes a ring body and guide vanes. Swirl adjustment holes are evenly distributed in a ring shape on the ring body, and the swirl adjustment holes correspond to the swirl holes on the inner wall surface one by one. The guide vanes are arranged axially on one side edge of the swirl adjustment holes, extend from the side edge upward to the swirl adjustment holes and extend into the swirl holes. The guide vanes have a swirl guiding slope adapted to the swirl angle. The oil temperature detector feeds back the oil temperature signal to the ring body driving mechanism, and the ring body driving mechanism drives the controllable swirl ring to rotate to adjust the overlapping degree of the swirl adjustment holes and the corresponding swirl holes.

[0010] Further, the air inlet flow passage is a spiral flow passage, and its flow-around spiral angle is adapted to the swirl angle.

[0011] Further, the heat exchanger is an integrally formed structure, which includes air flow distribution areas at both ends and a heat exchange area in the middle. The heat exchange area is provided with corrugated tube plates. Several spiral grooves are evenly distributed on the inner and outer surfaces of the corrugated tube plates. Several corrugated tube plates with different tube diameters are sleeved on each other, and the spiral grooves of adjacent corrugated tube plates are buckled with each other to form a self-enclosed spiral flow passage. Several spiral flow passages located in the same radial direction form an air inlet flow passage group or an exhaust flow passage group. The air inlet flow passage group and the exhaust flow passage group are arranged alternately. The air flow passages at the front and rear ends of the heat exchanger are separated by an intake and exhaust separation ring to form an intake air passage and an exhaust air passage. The intake air passage is connected to the air inlet flow passage group, and the exhaust air passage is connected to the exhaust flow passage group.

[0012] Further, an air flow distribution area is provided with a connecting end ring and an air flow distribution ring. The air flow distribution ring includes an exhaust distribution flow channel and an intake distribution flow channel which are fitted together. The exhaust distribution flow channel includes an outer exhaust distribution ring and several exhaust distribution bars radially arranged in a radial direction. The exhaust distribution bars communicate with several spiral flow channels in the exhaust flow channel group. The intake distribution flow channel includes an inner intake distribution ring and several intake distribution bars radially arranged in a radial direction. The intake distribution bars communicate with several spiral flow channels in the intake flow channel group. The connecting end ring and the intake and exhaust separation ring enclose an outer exhaust communication area and an inner intake communication area. An intake block for blocking the intake distribution bars located in this area is provided in the exhaust communication area, and an exhaust block for blocking the exhaust distribution bars located in this area is provided in the intake communication area.

[0013] Further, the fuel flow channel includes a heat exchange oil channel and distribution oil channels located at both ends of the heat exchange oil channel. The heat exchange oil channel is one of the groups or any one of the spiral flow channels in adjacent multiple groups or groups of intake flow channels. The distribution oil channel is self - enclosed and penetrates through the air flow distribution area, and its confluence communicates with the end of the heat exchange oil channel.

[0014] A gas volume distribution control method for a micro - turbine generator includes the following:

[0015] a. Obtain the real - time viscosity x of the fuel used according to the real - time temperature feedback by the oil temperature detector. When x > 2k, the adjustable angle θ of the controllable swirl ring is 0°, that is, the swirl holes are in a fully open state, and the overlap degree at this time is 100%. Here, k is the standard viscosity of the standard fuel.

[0016] b. When 0.5k < x ≤ 2k, the adjustable angle θ of the controllable swirl ring = (6 - 3x / k)°.

[0017] c. When x ≥ 0.5k, the adjustable angle θ of the controllable swirl ring = 4.5°.

[0018] Compared with the prior art, a micro - turbine generator capable of burning multiple fuels and its gas volume distribution control method of the present invention have the following beneficial effects:

[0019] By arranging an annular heat exchanger shared by oil and gas between the inner and outer casings of the turbo generator and using high-temperature exhaust gas to heat the incoming air and fuel, the high-viscosity fuel can maintain a relatively high temperature when entering the evaporation tube, reducing the fuel viscosity to a certain extent, making the atomization and evaporation process of the fuel in the evaporation tube more efficient, effectively reducing the fuel droplet diameter at the outlet of the evaporation tube, and improving the combustion effect. At the same time, a controllable swirl hole ring is arranged on the inner wall surface of the combustion chamber to collect the temperature and viscosity of the fuel in real time, and the opening degree of the swirl holes is adjusted according to the gas volume distribution control method to make the swirl intake air match the real-time viscosity of the fuel, flexibly providing an ideal swirl effect for fuels of different oil products and fuels in different viscosity states, enhancing the inclusiveness of the micro turbo generator for high-viscosity fuel, and improving the ignition and combustion performance of the high-viscosity fuel in the engine, overcoming the characteristics of large droplet diameter, difficult atomization and evaporation, and poor combustion characteristics of the high-viscosity fuel in the evaporation tube. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is a schematic structural diagram of the turbo generator disclosed by the present invention;

[0021] Figure 2 is Figure 1 a three-dimensional structural diagram of the heat exchange area in

[0022] Figure 3 is Figure 1 an assembly structural diagram of the controllable swirl component in

[0023] Figure 4 is Figure 3 a structural diagram of the controllable swirl component assembled on the inner wall surface of the annular combustion chamber in

[0024] Figure 5 is Figure 3 a three-dimensional structural diagram of the controllable swirl ring in

[0025] Figure 6 is Figure 1 a structural diagram of the air flow distribution ring in the air flow distribution area in

[0026] Figure 7 is Figure 1 a structural diagram of the connecting end ring in the air flow distribution area in

[0027] In the figure: 1. Generator; 2. Compressor impeller; 3. Fuel supply pipe; 31. Oil temperature detector; 4. Heat exchanger;

[0028] 41. Heat exchange area; 411. Inlet air flow channel; 412. Exhaust air flow channel; 413. Corrugated tube plate; 42. Air flow distribution area;

[0029] 421. Air flow distribution ring; 421a. Exhaust air distribution flow channel; 421b. Inlet air distribution flow channel; 421c. Fuel flow channel;

[0030] 422. Connecting end ring; 422a. Intake air block; 422b. Exhaust air block; 422c. Intake and exhaust separation ring; 5. Outer casing; 51. Exhaust passage; 52. Intake passage; 6. Inner casing; 7. Fuel distribution system; 8. Annular combustion chamber; 81. Inner ring wall surface; 811. Swirl hole; 9. Controllable swirl component; 91. Ring body drive mechanism; 911. Steering gear; 912. Drive link; 92. Controllable swirl ring; 921. Ring body; 922. Guide vane; 923. Swirl adjustment hole; 924. Driving rotation pin; 10. Turbine. Detailed implementation mode

[0031] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only the best embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0032] This embodiment provides a micro turbine generator that can combust multiple fuels. The micro turbine generator has a regenerative structure. As Figures 1-7 shown, it includes a generator 1, an outer casing 5, an inner casing 6, a linkage shaft, a fuel distribution system 7, a turbine 10, an annular combustion chamber 8, and a compressor impeller 2. After air enters the outer casing 5, it is compressed and conveyed by the compressor impeller 2. An air flow passage is formed between the outer casing 5 and the inner casing 6 behind the compressor impeller 2. Both intake air and exhaust air flow through the air flow passage. A heat exchanger 4 is located in the air flow passage. The air flow passages at the front and rear ends of the heat exchanger 4 are separated by an intake and exhaust separation ring 422c to form an intake passage 52 and an exhaust passage 51. The front intake passage 52 communicates with the compressor impeller 2, and the rear intake passage 52 communicates with the inner ring wall surface 81 and the outer ring wall surface of the annular combustion chamber 8. The front end of the exhaust passage 51 communicates with the pipe shaft, and the rear end communicates with the exhaust port;

[0033] As Figure 1 shown, a fuel flow passage 421c, an intake air flow passage 411, and an exhaust air flow passage 412 are provided in the heat exchanger 4. The fuel and air flows in the heat exchanger 4 flow in reverse to the high-temperature exhaust gas flow respectively. The fuel absorbs heat to reduce its viscosity and improve its atomization effect in the fuel injection pipe of the fuel distribution system 7. The air absorbs heat to further enhance the atomization and evaporation effect of the fuel in the fuel injection pipe. A swirl air flow forms a swirl at the nozzle of the fuel injection pipe to shear the oil mist particles at the nozzle and intensify the atomization and fragmentation of the fuel. The front end of the fuel flow passage 421c communicates with the fuel supply pipe 3, and the rear end communicates with the fuel distribution system 7 through a connecting oil pipe. An oil temperature detector 31 is provided on the connecting oil pipe to collect the fuel temperature at the front end of the fuel distribution system 7 in real time;

[0034] The controllable swirl component 9 is used to adjust the intake air volume of the swirl air in the swirl holes 811, so as to form a variable swirl structure at the outlet of the fuel injection pipe, adapting to the requirements of different oil products for the swirl air flow in the annular combustion chamber 8 under different working conditions. The controllable swirl component 9 includes a controllable swirl ring 92 and a driving mechanism 91 for the ring body 921. Referring again to Figures 3-5 , the controllable swirl ring 92 is sleeved on the inner wall surface 81 of the annular combustion chamber 8. The two ends of the controllable swirl ring 92 are positioned in the area of the swirl holes 811 by positioning posts. Its outer peripheral surface is attached to the inner wall surface 81 and can rotate relatively. The controllable swirl ring 92 includes a ring body 921 and guide vanes 922. The swirl adjustment holes 923 are evenly distributed in a ring on the ring body 921. The swirl adjustment holes 923 correspond to the swirl holes 811 on the inner wall surface 81 one by one, and should be greater than or equal to the swirl holes 811. The guide vanes 922 are arranged axially along one side edge of the swirl adjustment holes 923. They extend from the side edge upward to the swirl adjustment holes 923 and extend into the corresponding swirl holes 811. The guide vanes 922 have a swirl guiding slope adapted to the swirl angle. The swirl angle is a preset angle of the turbogenerator. The width of the guide vanes 922 is the same as the width of the swirl holes 811;

[0035] The driving mechanism 91 for the ring body 921 includes a servo 911, a crankshaft and a driving connecting rod 912. The servo 911 is installed on the outer casing 5. A driving rotation pin 924 is arranged axially on the inner ring surface of the ring body 921. An operation hole with a closed structure is arranged between the inner casing 6 and the outer casing 5. The driving connecting rod 912 passes through the operation hole and is rotatably connected to the driving rotation pin 924 and the crankshaft of the servo 911 respectively. A sealing chamber cover is arranged on the outer casing 5 to install the servo 911 and close the operation hole; The servo 911 drives the ring body 921 to rotate around the axis of the annular combustion chamber 8 according to the oil temperature signal fed back by the oil temperature detector 31, adjusting the overlap degree of the swirl adjustment holes 923 and the corresponding swirl holes 811.

[0036] As a further technical solution of this embodiment, in order to increase the swirl air volume, the heat exchanger 4 is used to heat the incoming air while rectifying it. The incoming air flow channel 411 in the heat exchanger 4 is a spiral flow-around channel, and its flow-around spiral angle is adapted to the swirl angle, enhancing the heat exchange effect through flow-around and forming a swirl air flow in the intake air channel 52;

[0037] As a further specific design, both the intake air flow channel 411 and the exhaust air flow channel 412 are spiral flow channels. The heat exchanger 4 is a 3D printed one-piece structure, which includes air flow distribution areas 42 at both ends and a heat exchange area 41 in the middle. The heat exchange area 41 is provided with several corrugated tube plates 413 with different tube diameters, an outer shell plate, and an inner shell plate. The inner and outer surfaces of the corrugated tube plates 413 are evenly distributed with several spiral grooves. The several corrugated tube plates 413 with different tube diameters are sequentially nested with each other, and the spiral grooves of adjacent corrugated tube plates 413 are buckled with each other to form a self-closed spiral flow channel. The outer shell plate and the inner shell plate respectively cover the notch of the spiral groove of the adjacent corrugated tube plate 413 to form two semi-spiral flow channels;

[0038] Among them, in order to increase the heat exchange area, several spiral flow channels located in the same radial direction are a group of intake air flow channels 411 or a group of exhaust air flow channels 412. The group of intake air flow channels 411 and the group of exhaust air flow channels 412 are arranged alternately. The air in the intake air passage 52 is distributed to the group of intake air flow channels 411 by the air flow distribution area 42, and the high-temperature exhaust gas in the exhaust air passage 51 is distributed to the group of exhaust air flow channels 412 by the air flow distribution area 42;

[0039] The air flow distribution area 42 is provided with an air flow distribution ring 421 and a communication end ring 422, and their structures are respectively as Figure 6 and Figure 7 shown. Among them, the air flow distribution ring 421 includes an exhaust distribution flow channel 421a and an intake distribution flow channel 421b that are nested with each other. The exhaust distribution flow channel 421a includes an outer exhaust distribution ring and several exhaust distribution strips that radially extend from the inner side of the exhaust distribution ring to the axis in a radial pattern. The exhaust distribution strips are connected in series to several spiral flow channels in the group of exhaust air flow channels 412. The width of the exhaust distribution ring is adapted to the height of half of the outer spiral flow channel. The intake distribution flow channel 421b includes an inner intake distribution ring and several intake distribution strips that radially extend from the outer side of the intake distribution ring to the outside in a radial pattern. The intake distribution strips are connected in series to several spiral flow channels in the group of intake air flow channels 411. The width of the intake distribution ring is adapted to the height of half of the inner spiral flow channel;

[0040] The communication end ring 422 and the intake and exhaust separation ring 422c enclose an outer exhaust communication area and an inner intake communication area. The intake communication area communicates with the intake distribution flow channel 421b, and the exhaust communication area communicates with the exhaust distribution flow channel 421a. An intake plug 422a for blocking the intake distribution strips located in this area is provided in the exhaust communication area, and an exhaust plug 422b for blocking the exhaust distribution strips located in this area is provided in the intake communication area.

[0041] Among them, the fuel flow channel 421c includes a heat exchange oil channel and distribution oil channels located at both ends of the heat exchange oil channel. The ends of the distribution oil channels extend outward to form interfaces. The distribution oil channels are self-sealing and penetrate through the air flow distribution area 42. The ends of one or more heat exchange oil channels are converged and connected. According to the flux of the spiral flow channels, one set or any adjacent multiple sets of the intake air flow channels 411 or the spiral flow channels in the intake air flow channels 411 are used as the heat exchange oil channels. Both ends of the heat exchange oil channels are connected and communicated with the distribution oil channels, and a self-sealing fuel channel sealed outside the intake air system is formed;

[0042] It should be noted that on the intake air channel 52 located at the rear end of the heat exchanger 4, all the reinforcing rib plate structures should be provided with a guiding slope adapted to the swirl angle to reduce the intake air resistance of the swirling air flow.

[0043] A gas volume distribution control method for a micro turbine generator, based on the structure of the micro turbine generator disclosed in the present invention, includes the following content:

[0044] Collect the temperature-viscosity characteristic curve of the fuel used. Obtain the real-time viscosity x of the fuel used according to the real-time temperature fed back by the oil temperature detector 31. k is the standard viscosity of the standard fuel. The standard fuel used is aviation kerosene, and its reference viscosity at room temperature is used as the standard viscosity. When x = k, the adjustment angle θ of the controllable swirl ring 92 is 3°. At this time, the opening degree of the swirl hole 811 is the same as the size of the swirl hole area of the original combustion chamber. Thus, the gas volume distribution is based on the standard viscosity, and the overlap degree between the swirl adjustment hole 923 and the swirl hole 811 at different real-time viscosities is adjusted according to the following algorithm;

[0045] a. When x > 2k, the viscosity of the fuel used is relatively high, and its evaporation and atomization effect in the evaporation tube is insufficient. At this time, the adjustment angle θ of the controllable swirl ring 92 is 0°, that is, the swirl hole 811 is in the fully open state. At this time, the overlap degree is 100%. The intake air volume of the swirl hole 811 is increased, the swirl intensity at the outlet of the evaporation tube of the evaporation tube type annular combustion chamber 8 is increased, the fuel residence time at the outlet of the evaporation tube is increased, and at the same time, the shear force of the strengthened swirl air flow will also be enhanced, intensifying the fuel atomization and fragmentation, so that the engine is more likely to be ignited and started, and the combustion quality in the annular combustion chamber 8 is improved;

[0046] b. As the heat exchange effect gradually increases, the temperature of the fuel used continuously rises, and its viscosity will gradually decrease. When 0.5k < x ≤ 2k, the adjustment angle θ of the controllable swirl ring 92 = (6 - 3x / k)°. The variable opening adjustment is beneficial to ensuring the flame stability during the combustion process;

[0047] c. The gradually increasing fuel temperature and the incoming air temperature enhance the atomization and evaporation effect of the evaporation tube. At this time, the fuel used no longer requires a high-intensity swirling air flow to achieve a good atomization and evaporation effect, and an overly strong swirling air flow will also cause the fuel and the flame to stay, affecting the propagation and stability of the flame inside the annular combustor 8. Therefore, when x≥0.5k, the controllable swirl ring 92 is adjusted to the minimum opening, and its adjustment angle θ = 4.5°.

[0048] The orientation terms such as "side", "end", "inner", "outer", "front", and "rear" mentioned in this article are described based on the orientation or positional relationship shown in Figures 1-7 or the fluid flow direction shown in. These terms are mainly used to better describe the present invention and its embodiments, and are not used to limit that the indicated device, element, or component must have a specific orientation, or be constructed and operated in a specific orientation;

[0049] Moreover, in addition to being used to represent the orientation or positional relationship, some of the above terms may also be used to represent other meanings. For example, the terms "upper" and "inner" may also be used to represent a certain attachment relationship or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in the present invention can be understood according to specific circumstances.

[0050] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A micro turbine generator capable of burning multiple fuels, comprising an outer casing, an inner casing, a fuel distribution system, an annular combustion chamber, and a compressor impeller. An air flow passage located behind the compressor impeller is formed between the outer casing and the inner casing. It is characterized in that: It further includes a heat exchanger and a controllable swirl assembly; The heat exchanger is arranged on the air flow channel. A fuel flow channel, an intake air flow channel and an exhaust gas flow channel are arranged in the heat exchanger. The intake air and the fuel in the fuel flow channel are heated by the exhaust heat. The front end of the fuel flow channel is connected to a fuel supply pipe, and the rear end is connected to a fuel distribution system. An oil temperature detector is arranged at the front end of the fuel distribution system; The controllable swirl assembly includes a controllable swirl ring and a ring body driving mechanism. The controllable swirl ring is sleeved on the inner wall surface of the annular combustion chamber and can rotate. The controllable swirl ring includes a ring body and guide vanes. Swirl adjustment holes are annularly and evenly distributed on the ring body. The swirl adjustment holes correspond to the swirl holes on the inner wall surface one by one. The guide vanes are axially arranged on one side edge of the swirl adjustment holes. They extend from the side edge upward to the swirl adjustment holes and extend into the swirl holes. The guide vanes have a swirl guiding slope adapted to the swirl angle; The oil temperature detector feeds back the oil temperature signal to the ring body driving mechanism, and the ring body driving mechanism drives the controllable swirl ring to rotate to adjust the overlap degree of the swirl adjustment holes and the corresponding swirl holes.

2. The microturbine generator capable of burning multiple fuels according to claim 1, wherein: The intake air flow channel is a spiral flow-around channel, and its flow-around spiral angle is adapted to the swirl angle.

3. The microturbine generator capable of burning multiple fuels according to claim 2, wherein: The heat exchanger is an integrally formed structure, which includes air flow distribution areas at both ends and a heat exchange area in the middle. The heat exchange area is provided with corrugated barrel plates. Several spiral grooves are evenly distributed on the inner and outer surfaces of the corrugated barrel plates. The corrugated barrel plates with several different barrel diameters are sleeved on each other. The spiral grooves of adjacent corrugated barrel plates are buckled with each other to form a self-closed spiral flow-around channel. Several spiral flow-around channels located in the same radial direction are a group of intake air flow channels or a group of exhaust gas flow channels. The group of intake air flow channels and the group of exhaust gas flow channels are arranged alternately. The air flow channels at the front and rear ends of the heat exchanger are separated by an intake and exhaust separation ring to form an intake air channel and an exhaust gas channel. The intake air channel is connected to the group of intake air flow channels, and the exhaust gas channel is connected to the group of exhaust gas flow channels.

4. The micro turbine generator capable of burning multiple fuels according to claim 3, characterized in that: The air flow distribution area is provided with a connecting end ring and an air flow distribution ring. The air flow distribution ring includes an exhaust gas distribution flow channel and an intake air distribution flow channel that are spliced with each other. The exhaust gas distribution flow channel includes an outer exhaust gas distribution ring and several exhaust gas distribution strips radially arranged in a radial shape. The exhaust gas distribution strips are connected to several spiral flow-around channels in the group of exhaust gas flow channels. The intake air distribution flow channel includes an inner intake air distribution ring and several intake air distribution strips radially arranged in a radial shape. The intake air distribution strips are connected to several spiral flow-around channels in the group of intake air flow channels; The connecting end ring and the intake and exhaust separation ring enclose an outer exhaust gas connection area and an inner intake air connection area. An intake air plug for blocking the intake air distribution strips located in this area is arranged in the exhaust gas connection area, and an exhaust gas plug for blocking the exhaust gas distribution strips located in this area is arranged in the intake air connection area.

5. The microturbine generator capable of burning multiple fuels according to claim 4, characterized in that: The fuel flow channel includes a heat exchange oil channel and distribution oil channels located at both ends of the heat exchange oil channel. The heat exchange oil channel is one or more adjacent groups of the intake air flow channel groups or any one of the spiral flow channels in the intake air flow channel groups. The distribution oil channels are self-closed and penetrate through the air flow distribution area, and their confluences are connected to the ends of the heat exchange oil channel.

6. A gas volume distribution control method for a micro turbine generator, based on the micro turbine generator capable of burning multiple fuels according to any one of claims 1 to 5, characterized in that, It includes the following contents: a. Obtain the real-time viscosity x of the fuel used according to the real-time temperature fed back by the oil temperature detector. When x > 2k, the adjustment angle θ of the controllable swirl ring is 0°, that is, the swirl holes are in the fully open state, and the overlapping degree at this time is 100%. Here, k is the standard viscosity of the standard fuel. b. When 0.5k < x ≤ 2k, the adjustment angle θ of the controllable swirl ring is θ = (6 - 3x / k)°. c. When x ≥ 0.5k, the adjustment angle θ of the controllable swirl ring is θ = 4.5°.

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