Micro gas turbine equipment

Abstract

The micro gas turbine equipment comprises a gas compressor, a combustion chamber, a turbine chamber, an exhaust nozzle and a waste heat recovery assembly, the gas compressor, the combustion chamber, the turbine chamber and the exhaust nozzle are sequentially connected, a partition plate is arranged between the gas compressor and the combustion chamber, and the waste heat recovery assembly comprises a gas collection chamber, a first heat exchange sleeve and a second heat exchange sleeve. The fuel gas collecting chamber is connected with the exhaust nozzle, the combustion chamber is sleeved with the first heat exchange sleeve and the second heat exchange sleeve, the fuel gas collecting chamber is connected with the first heat exchange sleeve through a fuel gas pipeline, and the fuel gas collecting chamber is connected with the second heat exchange sleeve through a fuel gas pipeline. According to the technical scheme, waste heat of high-temperature gas is recycled through the waste heat recycling assembly, compressed air and fuel are preheated, the working efficiency is improved, the waste heat recycling assembly is directly installed on an outer shell of the micro gas turbine, the structure is compact, the size is small, miniaturization of the micro gas turbine is guaranteed, and the occupied area of the micro gas turbine is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a micro gas turbine device. Background Art

[0002] Micro gas turbines are a recently developed type of small heat engine with a single unit power range of 25 to 300 kW. Their basic technical features are the use of radial turbine machinery (a centrifugal turbine and a centrifugal compressor) and a regenerative cycle. A gas turbine is a rotary power machine that uses a continuously flowing gas as a working fluid to convert thermal energy into mechanical energy. A gas turbine primarily consists of three components: a compressor, a combustion chamber, and a turbine assembly. The operation of a gas turbine is as follows: the compressor continuously draws air from the atmosphere and compresses it. The compressed air enters the combustion chamber, where it mixes with injected fuel and combusts to produce high-temperature combustion gas. This gas then flows into the gas turbine assembly, where it expands and generates work, driving the turbine impeller and the compressor impeller. The heated high-temperature combustion gas significantly increases its work capacity, allowing the gas turbine assembly to generate surplus work as mechanical output while driving the compressor. Gas turbines play a vital role in offshore oil and natural gas extraction, processing, and transportation. Compared with medium and large gas turbines, micro gas turbines have a wider range of applications and greater demand. They are the best way to provide small-scale distributed power generation and combined heating, cooling and power, and are widely used in industrial drives, mobile power supplies, and vehicle and ship power.

[0003] The temperature of the flue gas discharged from the continuous operation of the micro gas turbine is generally very high, currently generally around 500℃. If such high-temperature flue gas is not treated and directly discharged into the atmosphere, it will not only lead to waste of resources, but also aggravate the greenhouse effect and cause damage to the atmospheric environment. The thermal efficiency of the micro gas turbine is less than 20%, which will waste a lot of gas thermal energy. In order to improve the utilization rate of the micro gas turbine thermal energy, a waste heat boiler is usually installed at the exhaust outlet of the turbine assembly. The waste heat boiler has many equipment and is large in size, which will increase the overall footprint of the gas turbine equipment and increase the operation and maintenance costs. Summary of the Invention

[0004] Technical issues solved:

[0005] In response to the shortcomings of the existing technology, the present invention provides a micro gas turbine device, which recovers the waste heat of high-temperature fuel gas through a waste heat recovery component, preheats the compressed air and fuel, and improves work efficiency. The waste heat recovery component is directly installed on the outer casing of the micro gas turbine. It has a compact structure and a small size, which ensures the miniaturization of the micro gas turbine and reduces the footprint of the micro gas turbine, thereby solving the technical problems mentioned in the background technology.

[0006] Technical solution:

[0007] To achieve the above object, the present invention is implemented through the following technical solutions:

[0008] The exhaust gas fan of the gas evaporation machine is connected with the exhaust gas fan of the gas evaporation machine through the exhaust gas fan of the gas evaporation machine. One end of the first row of pipes and the second row of pipes are both connected to a main row pipe, and the main row pipe is used to discharge the gas after heat exchange. The first heat exchange jacket is equipped with a first spiral heat exchange plate and a second spiral heat exchange plate, and the second heat exchange jacket is equipped with a third spiral heat exchange plate and a fourth spiral heat exchange plate. An air flow channel and a gas flow channel are formed between the first spiral heat exchange plate and the second spiral heat exchange plate, and a fuel flow channel and a gas flow channel are formed between the third spiral heat exchange plate and the fourth spiral heat exchange plate. The air flow channel and the gas flow channel of the first heat exchange jacket are both arranged as a spiral structure, and the fuel flow channel and the gas flow channel of the second heat exchange jacket are both arranged as a spiral structure. The air compressed by the compressor flows in the air flow channel of the first heat exchange jacket, and the fuel flows in the fuel flow channel of the second heat exchange jacket. The compressed air and the high-temperature gas exchange heat in the process of flowing inside the first heat exchange jacket, and the fuel and the high-temperature gas exchange heat in the process of flowing inside the second heat exchange jacket.

[0009] In one possible implementation, the compressor is equipped with an impeller assembly, one side of the impeller assembly forms an air inlet, one end of the impeller assembly is connected to the main shaft, the impeller assembly of the compressor and the turbine assembly of the turbine chamber are installed on the same shaft to form the rotor of the micro gas turbine. The compressed air is mixed with the fuel and burned to become high-temperature combustion gas, which then flows into the turbine assembly in the turbine chamber to expand and perform work, pushing the impeller of the turbine assembly to rotate together with the impeller assembly of the compressor.

[0010] In one possible implementation, a burner is provided on the inner wall of the combustion chamber, one end of the burner is connected to the fuel outlet of the second heat exchange sleeve, the preheated fuel enters the combustion chamber through the fuel outlet of the second heat exchange sleeve, and the compressed air is mixed with the fuel and burns inside the combustion chamber.

[0011] In one possible implementation, a gas inlet is provided on the inner wall of the combustion chamber, and the gas inlet is connected to the air outlet of the first heat exchange sleeve. The preheated compressed air enters the combustion chamber through the gas inlet, mixes with the fuel, and burns.

[0012] In one possible implementation, the turbine chamber is equipped with a turbine assembly, which includes turbine blades. The working diameter of the turbine blades is larger than the blade area at the compressor outlet, which preliminarily ensures that the output torque of the turbine is greater than the torque required by the compressor under the same pressure, and the output power of the turbine assembly is greater than the power required by the compressor, ensuring that the micro gas turbine can output power to the outside while driving the compressor.

[0013] In one possible implementation, a gas outlet is provided at the tail end of the tail nozzle, and the gas outlet of the tail nozzle is connected to the air inlet of the gas collection chamber. The gas carrying a certain amount of waste heat enters the tail nozzle and enters the interior of the gas collection chamber through the gas outlet of the tail nozzle.

[0014] In a possible implementation, the gas pipeline includes a first diversion pipe and a second diversion pipe. After entering the gas collection chamber, the high-temperature gas flows into the gas pipeline again and is diverted to the first diversion pipe and the second diversion pipe through the gas pipeline.

[0015] In one possible implementation, one end of the first diverter pipe is connected to the gas inlet of the first heat exchange jacket, and one end of the second diverter pipe is connected to the gas inlet of the second heat exchange jacket. A portion of the high-temperature gas enters the interior of the first heat exchange jacket through the first diverter pipe and flows in the gas flow channel of the first heat exchange jacket, and another portion of the high-temperature gas enters the interior of the second heat exchange jacket through the second diverter pipe and flows in the gas flow channel of the second heat exchange jacket.

[0016] In one possible implementation, the gas pipeline includes an annular tube, multiple groups of gas collecting pipes are provided on the inner ring of the annular tube, and a gas delivery pipe is provided on the outer ring of the annular tube. The multiple groups of gas collecting pipes are connected to the gas pipeline, the gas pipeline is connected to the gas delivery pipe, and the gas delivery pipe is connected to the first heat exchange jacket. The multiple groups of gas collecting pipes are evenly spaced along the circumferential direction of the annular tube, and the multiple groups of gas collecting pipes are evenly distributed at the tail end of the compressor.

[0017] In one possible implementation, multiple groups of the gas collection pipes are embedded in the interior of the compressor and are located at the tail end of the impeller assembly. One end of the gas supply pipe is connected to the air inlet of the first heat exchange jacket. The partition is set so that the compressed air does not directly enter the combustion chamber, but enters the multiple groups of gas collection pipes distributed at the tail end of the compressor. The compressed air is concentrated into the annular pipe through the multiple groups of gas collection pipes, and then enters the gas supply pipe through the annular pipe, and then enters the first heat exchange jacket through the gas supply pipe to preheat the compressed air.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. The present invention adds a waste heat recovery component to the micro gas turbine, which recovers the waste heat of the high-temperature fuel gas through the waste heat recovery component. The waste heat of the high-temperature fuel gas is used to preheat the compressed air before combustion, and the fuel before combustion. Therefore, the compressed air and fuel are preheated to a certain temperature before entering the combustion chamber for combustion. The compressed air and fuel both carry a certain amount of initial thermal energy, which enables the fuel to be fully burned and reduces fuel consumption, thereby improving the working efficiency of the micro gas turbine, reducing operating costs, and reducing energy consumption.

[0020] 2. The present invention replaces the waste heat boiler with a waste heat recovery component with a simple structure. The waste heat recovery component is directly installed on the outer casing of the micro gas turbine. It has a compact structure and a small size. While improving the working efficiency of the micro gas turbine, it fully utilizes the thermal energy of the gas, ensures the miniaturization of the micro gas turbine, and reduces the footprint of the micro gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention and implement it according to the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention with reference to the accompanying drawings.

[0022] Figure 1 A schematic diagram of the structure of a side view of the present invention;

[0023] Figure 2 is another side view structural schematic diagram of the present invention;

[0024] Figure 3 It is the front view of the present invention;

[0025] Figure 4 Schematic diagram of the internal structure of the present invention;

[0026] Figure 5 It is a schematic structural diagram of the main shaft, impeller assembly and turbine assembly of the present invention;

[0027] Figure 6 This is a flow diagram of air inside the first heat exchange jacket of the present invention;

[0028] Figure 7 This is a flow diagram of the gas inside the first heat exchange jacket of the present invention;

[0029] Figure 8 This is a flow diagram of the fuel inside the second heat exchange jacket of the present invention;

[0030] Figure 9 This is a flow diagram of the gas inside the second heat exchange jacket of the present invention;

[0031] Figure 10 Schematic diagram of the structure of the gas pipeline of the present invention.

[0032] In the figure: 1. compressor; 2. combustion chamber; 3. turbine chamber; 4. tail nozzle; 5. main shaft; 6. waste heat recovery assembly; 7. partition; 11. air inlet; 12. impeller assembly; 21. burner; 22. gas inlet; 31. turbine assembly; 41. gas outlet; 61. gas collecting chamber; 62. first heat exchange jacket; 63. second heat exchange jacket; 64. gas pipeline; 65. gas pipeline; 66. fuel pipeline; 67. first row of pipes; 68. second row of pipes; 69. main row of pipes; 621. first spiral heat exchange fin; 622. second spiral heat exchange fin; 631. third spiral heat exchange fin; 632. fourth spiral heat exchange fin; 641. first diverter pipe; 642. second diverter pipe; 651. annular pipe; 652. gas collecting pipe; 653. gas transmission pipe. DETAILED DESCRIPTION

[0033] The embodiment of the present application provides a micro gas turbine device, which recovers the waste heat of high-temperature fuel gas through a waste heat recovery component, preheats the compressed air and fuel, and improves work efficiency. The waste heat recovery component is directly installed on the outer casing of the micro gas turbine, has a compact structure and a small size, ensures the miniaturization of the micro gas turbine, reduces the footprint of the micro gas turbine, and solves the technical problems mentioned in the background technology.

[0034] The technical solution in the embodiments of the present application is to solve the problems of the above-mentioned background technology, and the overall idea is as follows:

[0035] Example 1:

[0036] See also Figure 1-10The present invention provides a technical solution: a micro gas turbine device, including a compressor 1, a combustion chamber 2, a turbine chamber 3, a tail nozzle 4 and a waste heat recovery component 6. The compressor 1 is responsible for sucking air from the surrounding atmosphere, and supplying it to the combustion chamber 2 after pressurization. The fuel and compressed air are burned inside the combustion chamber 2, and the high-temperature gas then flows into the turbine chamber 3 to perform work. Finally, the high-temperature gas is discharged through the tail nozzle 4 and collected by the waste heat recovery component 6. The heat of the high-temperature gas is recovered by the waste heat recovery component 6. The compressor 1, the combustion chamber 2, the turbine chamber 3 and the tail nozzle 4 are used to absorb air from the surrounding atmosphere, and the air is supplied to the combustion chamber 2 after pressurization. The fuel and compressed air are burned inside the combustion chamber 2, and the high-temperature gas then flows into the turbine chamber 3 to perform work. Finally, the high-temperature gas is discharged through the tail nozzle 4 and collected by the waste heat recovery component 6. The nozzles 4 are connected in sequence, a partition 7 is provided between the compressor 1 and the combustion chamber 2, the waste heat recovery assembly 6 includes a gas collection chamber 61, a first heat exchange jacket 62 and a second heat exchange jacket 63, the gas collection chamber 61 is connected to the tail nozzle 4, the first heat exchange jacket 62 and the second heat exchange jacket 63 are both sleeved on the outside of the combustion chamber 2, the gas collection chamber 61 and the first heat exchange jacket 62 are connected by a gas pipeline 64, the gas collection chamber 61 and the second heat exchange jacket 63 are connected by a gas pipeline 64, the tail end of the compressor 1 and the first heat exchange jacket 62 are connected by a gas pipe. The exhaust gas after heat exchange by the first heat exchange jacket 62 is discharged through the first exhaust pipe 67, and the exhaust gas after heat exchange by the second heat exchange jacket 63 is discharged through the second exhaust pipe 68. The exhaust gas after heat exchange by the first heat exchange jacket 62 is concentrated into the exhaust pipe 69 and discharged through the exhaust pipe 69. The first spiral heat exchange fin 621 and the second spiral heat exchange fin 622, the second heat exchange sleeve 63 is equipped with a third spiral heat exchange fin 631 and a fourth spiral heat exchange fin 632, an air flow channel and a gas flow channel are formed between the first spiral heat exchange fin 621 and the second spiral heat exchange fin 622, a fuel flow channel and a gas flow channel are formed between the third spiral heat exchange fin 631 and the fourth spiral heat exchange fin 632, the air flow channel and the gas flow channel of the first heat exchange sleeve 62 are both set to a spiral structure, and the fuel flow channel and the gas flow channel of the second heat exchange sleeve 63 are both set to a spiral structure.

[0037] Among them, a waste heat recovery component 6 is added to the micro gas turbine, and the gas collection chamber 61 of the waste heat recovery component 6 is connected to the tail nozzle 4. The high-temperature gas discharged through the gas outlet 41 at the tail end of the tail nozzle 4 is concentrated into the interior of the gas collection chamber 61, and then diverted to the interior of the first heat exchange jacket 62 and the second heat exchange jacket 63 through the gas pipeline 64.

[0038] Compressor 1 continuously draws air from the atmosphere and compresses it. The compressed air is discharged to the tail end of compressor 1 and enters the gas pipeline 65. The compressed air and the high-temperature fuel gas flow through different flow channels inside the first heat exchange jacket 62. During the flow, heat is exchanged between the compressed air and the high-temperature fuel gas, and the high-temperature fuel gas is used to preheat the compressed air before combustion.

[0039] The fuel for combustion enters the second heat exchange jacket 63 through the fuel pipeline 66. The fuel and the high-temperature gas flow in different flow channels inside the second heat exchange jacket 63 respectively. During the flow process, heat exchange occurs between the fuel and the high-temperature gas, and the high-temperature gas is used to preheat the fuel before combustion.

[0040] The waste heat of the high-temperature fuel gas is recovered by the added waste heat recovery component 6, and the compressed air is preheated before combustion by the waste heat of the high-temperature fuel gas, and the fuel is preheated before combustion, so that the compressed air and fuel are preheated to a certain temperature before entering the combustion chamber 2, thereby improving the working performance of the gas turbine, improving the utilization rate of the waste heat of the gas turbine exhaust, and reducing energy consumption.

[0041] In some examples, the compressor 1 has a built-in impeller assembly 12 , one side of the impeller assembly 12 forms an air inlet 11 , and one end of the impeller assembly 12 is connected to the main shaft 5 .

[0042] Among them, the impeller assembly 12 of the compressor 1 and the turbine assembly 31 of the turbine chamber 3 are installed on the same shaft to form the rotor of the micro gas turbine. The compressed air is mixed with the fuel and burned to become high-temperature combustion gas, which then flows into the turbine assembly 31 in the turbine chamber 3 to expand and do work, pushing the impeller of the turbine assembly 31 to rotate together with the impeller assembly 12 of the compressor 1.

[0043] In some examples, a burner 21 is provided on the inner wall of the combustion chamber 2, and one end of the burner 21 is connected to the fuel outlet of the second heat exchange sleeve 63. The preheated fuel enters the combustion chamber 2 through the fuel outlet of the second heat exchange sleeve 63, and the compressed air is mixed with the fuel and burns inside the combustion chamber 2.

[0044] In some examples, a gas inlet 22 is provided on the inner wall of the combustion chamber 2 , and the gas inlet 22 is connected to the air outlet of the first heat exchange sleeve 62 . The preheated compressed air enters the combustion chamber 2 through the gas inlet 22 , mixes with the fuel, and burns.

[0045] In some examples, the turbine chamber 3 houses a turbine assembly 31 .

[0046] Among them, the turbine assembly 31 includes turbine blades, and the working diameter of the turbine blades is larger than the blade area at the outlet of the compressor 1, which preliminarily ensures that the output torque of the turbine is greater than the torque required by the compressor 1 under the same pressure, that is, the output power of the turbine assembly 31 is greater than the power required by the compressor 1, ensuring that the micro gas turbine can output power to the outside while driving the compressor 1.

[0047] In some examples, a gas outlet 41 is provided at the tail end of the tail nozzle 4, and the gas outlet 41 of the tail nozzle 4 is connected to the air inlet of the gas collection chamber 61. The gas carrying a certain amount of waste heat enters the tail nozzle 4 and enters the interior of the gas collection chamber 61 through the gas outlet 41 of the tail nozzle 4.

[0048] In some examples, the gas pipeline 64 includes a first diversion pipe 641 and a second diversion pipe 642 . After entering the gas collection chamber 61 , the high-temperature gas flows into the gas pipeline 64 and is diverted to the first diversion pipe 641 and the second diversion pipe 642 through the gas pipeline 64 .

[0049] In some examples, one end of the first diversion pipe 641 is connected to the gas inlet of the first heat exchange jacket 62 , and one end of the second diversion pipe 642 is connected to the gas inlet of the second heat exchange jacket 63 .

[0050] Among them, Figure 6 、 Figure 7 、 Figure 8 and Figure 9 As shown, a portion of the high-temperature gas enters the interior of the first heat exchange jacket 62 through the first diverter pipe 641 and flows in the gas flow channel of the first heat exchange jacket 62, and another portion of the high-temperature gas enters the interior of the second heat exchange jacket 63 through the second diverter pipe 642 and flows in the gas flow channel of the second heat exchange jacket 63. The air compressed by the compressor 1 flows in the air flow channel of the first heat exchange jacket 62, and the fuel enters the second heat exchange jacket 63 and flows in the fuel flow channel. The compressed air and the high-temperature gas exchange heat during the flow inside the first heat exchange jacket 62, and the fuel and the high-temperature gas exchange heat during the flow inside the second heat exchange jacket 63.

[0051] By adopting the above technical solutions:

[0052] A waste heat recovery component 6 is added to the micro gas turbine to recover the waste heat of the high-temperature fuel gas through the waste heat recovery component 6. The waste heat of the high-temperature fuel gas is used to preheat the compressed air before combustion, and the fuel before combustion. Therefore, the compressed air and the fuel are preheated to a certain temperature before entering the combustion chamber 2 for combustion. The compressed air and the fuel both carry a certain amount of initial heat energy, so that the fuel can be fully burned and the fuel consumption can be reduced, thereby improving the working efficiency of the micro gas turbine and reducing the operating cost.

[0053] The waste heat boiler is replaced by a waste heat recovery component 6 with a simple structure. The waste heat recovery component 6 is directly installed on the outer casing of the micro gas turbine. It has a compact structure and a small size. While improving the working efficiency of the micro gas turbine, it fully utilizes the thermal energy of the gas, ensures the miniaturization of the micro gas turbine, and reduces the footprint of the micro gas turbine.

[0054] Example 2:

[0055] Based on Example 1, this example introduces a specific structure of a gas pipeline 65 in a micro gas turbine device. The gas pipeline 65 includes an annular tube 651, and multiple groups of gas collection pipes 652 are arranged on the inner circle of the annular tube 651, and a gas transmission pipe 653 is arranged on the outer circle of the annular tube 651.

[0056] Among them, multiple groups of gas collection pipes 652 are connected to the gas pipeline 65, the gas pipeline 65 is connected to the gas delivery pipe 653, the gas delivery pipe 653 is connected to the first heat exchange jacket 62, and the multiple groups of gas collection pipes 652 are evenly distributed along the circumferential direction of the annular pipe 651, and the multiple groups of gas collection pipes 652 are evenly distributed at the tail end of the compressor 1.

[0057] In some examples, multiple groups of gas collection pipes 652 are embedded in the interior of the compressor 1 and located at the tail end of the impeller assembly 12 , and one end of the gas delivery pipe 653 is connected to the air inlet of the first heat exchange jacket 62 .

[0058] Among them, the compressor 1 continuously inhales air from the atmosphere and compresses the air, and the compressed air is discharged to the tail end of the compressor 1. The setting of the partition 7 makes the compressed air not directly enter the combustion chamber 2, but enter the multiple groups of gas collection pipes 652 distributed at the tail end of the compressor 1, and enter the annular pipe 651 through the multiple groups of gas collection pipes 652, and then enter the air supply pipe 653 through the annular pipe 651, and enter the first heat exchange jacket 62 through the air supply pipe 653, and flow and exchange heat in the air flow channel inside the first heat exchange jacket 62. Finally, the compressed air after heat exchange enters the combustion chamber 2 through the gas inlet 22 for combustion. The setting of the gas pipeline 65 and the partition 7 enables the compressed air to be heat-exchanged and heated before being put into combustion. The compressed air has a certain initial temperature, thereby improving the waste heat utilization rate of the micro gas turbine and the working efficiency of the micro gas turbine.

[0059] Finally, it should be noted that the above embodiments are merely examples for the purpose of illustrating the present invention and are not intended to limit the embodiments. Those skilled in the art will readily appreciate that other variations or modifications based on the above description are possible. It is not necessary and impossible to provide an exhaustive list of all embodiments. However, obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A micro gas turbine device comprising a compressor (1), a combustion chamber (2), a turbine chamber (3), a tail nozzle (4) and a waste heat recovery component (6), characterized in that: The compressor (1), the combustion chamber (2), the turbine chamber (3) and the tail nozzle (4) are connected in sequence. A partition (7) is provided between the compressor (1) and the combustion chamber (2). The waste heat recovery component (6) includes a gas collection chamber (61), a first heat exchange jacket (62) and a second heat exchange jacket (63). The gas collection chamber (61) is connected to the tail nozzle (4). The first heat exchange jacket (62) and the second heat exchange jacket (63) are both sleeved on the outside of the combustion chamber (2). The gas collection chamber (61) and the first heat exchange jacket (62) are connected via a gas pipeline (64). The gas collection chamber (61) and the second heat exchange jacket (63) are connected via a gas pipeline (64). The tail end of the compressor (1) is connected to the first heat exchange jacket (62) via a gas pipeline (65). The second heat exchange jacket (63) is provided with a fuel pipeline (66) and a second row of pipes (68); the first heat exchange jacket (62) is provided with a first row of pipes (67); one end of the first row of pipes (67) and the second row of pipes (68) are both connected to a main row of pipes (69); the main row of pipes (69) is used to discharge the gas after heat exchange; the first heat exchange jacket (62) is provided with a first spiral heat exchange fin (621) and a second spiral heat exchange fin (622); the second heat exchange jacket (63) is provided with a third spiral heat exchange fin (631) and a fourth spiral heat exchange fin (632); an air flow channel and a gas flow channel are formed between the first spiral heat exchange fin (621) and the second spiral heat exchange fin (622); a fuel flow channel and a gas flow channel are formed between the third spiral heat exchange fin (631) and the fourth spiral heat exchange fin (632).

2. A micro gas turbine device according to claim 1, characterized in that: The compressor (1) is equipped with an impeller assembly (12), one side of the impeller assembly (12) forms an air inlet (11), and one end of the impeller assembly (12) is connected to a main shaft (5).

3. The micro gas turbine device according to claim 1, characterized in that: A burner (21) is provided on the inner wall of the combustion chamber (2), and one end of the burner (21) is connected to the fuel outlet of the second heat exchange jacket (63).

4. A micro gas turbine device according to claim 1, characterized in that: A gas inlet (22) is provided on the inner wall of the combustion chamber (2), and the gas inlet (22) is connected to the air outlet of the first heat exchange jacket (62).

5. The micro gas turbine device according to claim 1, characterized in that: The turbine chamber (3) has a built-in turbine assembly (31).

6. The micro gas turbine device according to claim 1, characterized in that: A gas outlet (41) is provided at the tail end of the tail nozzle (4), and the gas outlet (41) of the tail nozzle (4) is communicated with the gas inlet of the gas collection chamber (61).

7. The micro gas turbine device according to claim 1, characterized in that: The gas pipeline (64) includes a first diversion pipe (641) and a second diversion pipe (642).

8. The micro gas turbine device according to claim 7, characterized in that: One end of the first diverter pipe (641) is connected to the gas inlet of the first heat exchange jacket (62), and one end of the second diverter pipe (642) is connected to the gas inlet of the second heat exchange jacket (63).

9. The micro gas turbine device according to claim 1, characterized in that: The gas pipeline (65) comprises an annular tube (651), a plurality of gas collecting tubes (652) are arranged on the inner ring of the annular tube (651), and a gas delivery tube (653) is arranged on the outer ring of the annular tube (651).

10. The micro gas turbine device according to claim 9, characterized in that: The plurality of gas collecting pipes (652) are embedded in the interior of the compressor (1) and located at the tail end of the impeller assembly (12). One end of the gas delivery pipe (653) is connected to the air inlet of the first heat exchange jacket (62).

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