WO2022105214A1

WO2022105214A1 - Dual-shaft power generation gas turbine

Info

Publication number: WO2022105214A1
Application number: PCT/CN2021/099968
Authority: WO
Inventors: 靳新中
Original assignee: 至玥腾风科技集团有限公司
Priority date: 2020-11-18
Filing date: 2021-06-15
Publication date: 2022-05-27
Also published as: CN112502833A

Abstract

A dual-shaft power generation gas turbine, comprising a first rotor system and a second rotor system. The first rotor system comprises a first rotating shaft (100), a first motor (200), a compressor (300), a first turbine (400) and a combustion chamber (500). An exhaust end of the gas compressor (300) is in communication with an inlet end of the combustion chamber (500), and an exhaust end of the combustion chamber (500) is in communication with a gas inlet end of the first turbine (400). The second rotor system comprises a second rotating shaft (600), a second turbine (700), and a second motor (800). The first rotating shaft (100) and the second rotating shaft (600) are coaxially arranged. An exhaust end of the first turbine (400) is in communication with a gas inlet end of the second turbine (700).

Description

Two-shaft power generation gas turbine

technical field

The invention relates to a dual-shaft power generation gas turbine, which belongs to the technical field of gas turbines.

Background technique

Industrial gas turbines mainly include three components: compressor, combustion chamber and turbine. After the air enters the compressor, it is compressed into high temperature and high pressure air, and then supplied to the combustion chamber for fuel combustion.

In the prior art, each component of the gas turbine is arranged on one shaft. Since the compressor and the turbine are all on this shaft, the structure is simple and the economy is good. However, when the required power is large, the shaft length is long and the design is difficult. high. Theoretically, the compressor of the single-rotor structure micro gas turbine can be made into any number of stages to achieve a certain supercharging ratio. However, due to the structural limitation of the single rotor, all parts are installed on the same main shaft. When the speed of the single rotor suddenly drops, the high pressure part of the compressor will not have enough speed and the efficiency will be seriously reduced. At the same time, the low pressure of the compressor will Part of the load will rise sharply, and the low pressure compressor part will cause surge when overloaded, and in normal operation, surge is not allowed. In order to solve this problem, guide vanes are usually installed before the compressor or deflation is performed on the intermediate stage of the compressor, that is, a part of the pressurized air is emptied to reduce the load of the low-pressure part of the compressor. This method has obvious shortcomings, not only will the efficiency be greatly reduced, but also the effect on the compressor with high supercharging ratio is not very obvious.

In addition, the impellers used in the compressors of gas turbines are divided into open type, semi-open type and closed type. The characteristics of the three types of impellers are as follows:

(1) Open impeller: The friction loss and flow resistance are large, the impeller efficiency is the lowest, and it is easy to generate vibration, so it is not suitable to work at high speed.

(2) Semi-open impeller: The friction loss and flow resistance are smaller than that of the open impeller, the efficiency is higher, and it has a certain rigidity and strength, allowing it to work at a higher peripheral speed.

(3) Closed impeller: the friction loss and flow resistance are the smallest, and the efficiency is the highest, but due to the complex and heavy structure, and the huge stress on the blades when the wheel cover rotates, its strength is poor, and it is not suitable for high-speed conditions. use below.

Most of the impellers used in current compressors are semi-open impellers. The challenge that the compressor needs to overcome is how to obtain small friction loss and flow resistance, high efficiency, light weight and high strength.

At present, compressors generally use bearing sets composed of multiple radial bearings and thrust bearings, which often require a long enough shaft for installation. The problem is that the axial size of the compressor increases. If this type of compressor is used in micro In equipment such as gas turbine generator sets, the space occupied by the equipment will increase, and the overall weight will be increased, which is not conducive to integrated design, and the processing and assembly errors caused by the arrangement of multiple bearings will increase, making processing and assembly difficult.

SUMMARY OF THE INVENTION

In view of the above-mentioned prior art, the present invention provides a dual-shaft power generation gas turbine, which does not require a long rotating shaft, can easily ensure the coaxiality of parts on the shaft, is easier to process, has a high degree of integration, and has high reliability of the whole machine.

The present invention is achieved through the following technical solutions:

A dual-shaft power generation gas turbine includes a first rotor system and a second rotor system; the first rotor system includes a first rotating shaft, a first motor, a compressor, a first turbine and a combustion chamber, wherein the first motor, the compressor The compressor and the first turbine are sequentially sleeved on the first rotating shaft from front to back, the exhaust end of the compressor is communicated with the inlet end of the combustion chamber, and the exhaust end of the combustion chamber is communicated with the intake end of the first turbine;

The second rotor system includes a second rotating shaft, a second turbine and a second motor, wherein the second turbine and the second motor are sequentially sleeved on the second rotating shaft from front to back;

The first rotating shaft and the second rotating shaft are coaxially arranged, and the first rotating shaft is arranged before the second rotating shaft; the exhaust end of the first turbine is communicated with the intake end of the second turbine.

Further, the first motor is a heuristic integrated motor. When the compressor is started, it is driven by the integrated motor. The integrated motor first acts as a motor to drive the compressor to rotate, and when it is accelerated to be able to run independently, it is disengaged, and then acts as a generator. The first motor generates electricity.

Further, the combustion chamber is a rotating recirculation combustion chamber or an axial flow combustion chamber, the axis of the combustion chamber is coaxial with the first rotating shaft, is arranged around the first rotating shaft and is located at the periphery of the compressor or/and the first turbine.

Further, the first rotor system further includes a regenerator; the regenerator is provided with a first inlet, a first outlet, a second inlet and a second outlet; the outlet of the compressor and the first inlet of the regenerator communication, the first outlet of the regenerator communicates with the inlet end of the combustion chamber, the exhaust end of the first turbine communicates with the second inlet of the regenerator, and the second outlet of the regenerator communicates with the intake end of the second turbine . When working, the working medium (such as air) enters from the inlet of the compressor. After being compressed by the compressor, it enters the first inlet of the regenerator from its outlet, and flows out from the first outlet, enters the combustion chamber and enters the first turbine. The intake end pushes the first turbine to rotate to do work; after the working medium does work through the first turbine, it enters the second inlet of the regenerator from the exhaust end of the first turbine, and then flows from its second outlet after heat exchange in the regenerator. The gas flows out and enters the second turbine, and the outflowing gas pushes the second turbine to rotate to do work, which in turn drives the second motor to generate electricity.

Further, the compressor is a closed impeller compressor; the closed impeller compressor includes a rotating shaft, and a closed impeller and a motor are sleeved on the rotating shaft; the closed impeller includes a back cover, a blade, a sleeve and a front A cover, wherein the rear cover is arranged at the tail end of the sleeve body, and an integral through hole is arranged in the center of the rear cover and the sleeve body for sleeve installation and fixing on the rotating shaft; the blades are arranged around the sleeve body and rotate in the same direction, and one end of the blade is The outer wall of the sleeve is connected, and the other end is connected with the end face of the rear cover; the front cover is arranged on the blade, and the front cover is in the shape of a truncated cone; the air inlet surface of the front cover is a curved surface that smoothly transitions along the contour of the blade ridge, and the back air surface is provided with The grooves that match the ends of the blades, the blade ends corresponding to the grooves are embedded in the grooves for tight fitting connection; a flow channel is formed between the blades, the rear cover and the front cover; the tail of the front cover and the rear cover are separated by the blades There are spaced air outlets, and the gas flows out from the air outlet through the flow channel from the front of the blade.

Further, the rear cover, the blade and the sleeve body are integrally formed.

Further, the outer edge of the blade protrudes from the end face of the rear cover in the axial direction.

Further, the blade includes a longer main blade and a shorter splitter blade, and the main blade and the splitter blade are arranged at intervals in sequence. The front cover grooves are divided into main blade grooves and splitter blade grooves, which are respectively set at the ends of the main blades and the splitter blades.

Further, the leading edge of the front cover protrudes from the leading edge of the blade, or is flatter than the leading edge of the blade, or is shorter than the leading edge of the blade.

Further, the front cover is made of carbon fiber composite material.

Further, the closed impeller cover is provided with a stator, and the part of the stator facing the front cover is evenly opened with one or more circles of air holes, which can be decomposed into axial and radial airflow after air intake. The impeller is suspended in the stator and rotates stably, the axial airflow pushes the impeller backward, and the stator is used as an air bearing and also plays the role of a radial bearing and a thrust bearing.

Further, a thrust bearing and a thrust plate are arranged on the first rotating shaft or/and the second rotating shaft.

Further, at least one radial bearing is arranged on the first rotating shaft or/and the second rotating shaft. Specifically, for the first rotor system, the radial bearing can be arranged at the front end of the rotating shaft, which can solve the problem that the front end of the first rotating shaft cantilever is too long and the rotating shaft is offset due to the magnetic force of the motor. In addition, radial bearings can also be provided on one or both sides of the first electric machine, or between the compressor and the first turbine.

Further, the first turbines are arranged in two or more and are connected in series on the first rotating shaft; radial bearings may be arranged between adjacent turbines. During operation, the exhaust gas from the second outlet of the combustion chamber or the regenerator pushes each turbine to rotate in turn to do work.

Further, the second turbines are arranged in two or more and are connected in series on the second rotating shaft; radial bearings may be arranged between adjacent turbines. During operation, the exhaust gas of the first turbine pushes each of the second turbines to rotate in turn to do work.

Further, the power of the first motor is 20-30KW, the power of the second motor is 120-130KW, and the overall power of the gas turbine is 140-160KW.

The dual-shaft power-generating gas turbine of the present invention includes two power-generating shafts, and the two power-generating shafts are decoupled, and the rotational speed does not have to be the same, which facilitates flexible matching of the aerodynamic design of the turbine. The dual-shaft power generation gas turbine of the present invention includes two rotating shafts. Compared with using a longer rotating shaft, while ensuring high power, the required length of each rotating shaft is shorter, and the length of the rotating shaft is shortened (the less the number of bearings on the rotating shaft is , the shorter the length of the rotating shaft, the shorter the overall length of the equipment, the higher the integration), it is easy to ensure the coaxiality of the parts on the shaft, the processing is easier, the integration is high, and the reliability of the whole machine is high. When the drop pressure ratio of the compressor is high, two or more first turbines or/and second turbines can be arranged to make full use of the pressure difference generated by the compressor to obtain higher power generation efficiency. The compressor of the present invention adopts a closed impeller, which can obtain small friction loss and flow resistance, high efficiency, light weight and high strength.

The closed impeller compressor used in the present invention is provided with a detachable front cover, the front cover is in the shape of a truncated cone, the air inlet surface is a curved surface with a smooth transition along the contour of the blade ridge line, and the back air surface is provided with a surface that matches the end of the blade. When working, the friction loss is small, the flow resistance is small, and the efficiency is high; when working, the front cover and the blade are tightly engaged, and the gas flows out from the air outlet from the front of the blade through the flow channel, and the gas leakage is very small. The front cover is made of carbon fiber composite material. The impeller is light in overall weight and has high strength. The blade (metal material) will expand when rotating, while the front cover does not expand. Therefore, with the increase of rotation speed and time, the blade and the front cover will not expand. The occlusion between the grooves of the blades will become tighter and tighter (when the stator is provided as an air bearing, its intake air will also be applied to the front cover to further prevent the separation of the blades and the grooves of the front cover), which is suitable for high-speed rotation conditions. The provision of splitter vanes can not only reduce the blockage of the inlet air flow, but also improve the slip coefficient of the impeller outlet, which not only improves the efficiency of the impeller, but also improves the overall efficiency of the compressor due to the improved flow field at the impeller outlet. The closed impeller compressor of the present invention is provided with an oblique thrust structure, and the stator is used as an air bearing and plays the role of a radial bearing and a thrust bearing at the same time (gas is introduced into the gap between the stator and the impeller from the air hole, so that the gap is A uniform and stable air film is formed inside, so that the impeller rotates stably in the stator, so as to play the role of air bearing), which can reduce or even replace the original radial bearing and thrust bearing. When the stator is also used as a thrust bearing, if other radial bearings are installed on the rotating shaft, it is equivalent to having multiple radial bearings for support, the overall vibration is small, and the operation is stable. If there are no other radial bearings or only a small amount of radial bearings on the rotating shaft, the length of the rotating shaft can be shortened, it is easy to ensure the coaxiality of the parts on the shaft, the processing is easier, the integration is high, and the reliability of the whole machine is high.

Various terms and phrases used herein have their ordinary meanings as known to those skilled in the art. If the terms and phrases mentioned are inconsistent with the known meanings, the meanings expressed in the present invention shall prevail.

Description of drawings

FIG. 1 is a schematic diagram of the structure and principle of the dual-shaft power generation gas turbine of Example 1. FIG.

FIG. 2 is a schematic diagram of the structure and principle of the dual-shaft power generation gas turbine of Example 2. FIG.

100, the first shaft; 200, the first motor; 300, the compressor; 400, the first turbine; 500, the combustion chamber; 600, the second shaft; 700, the second turbine; 800, the second motor; 900, regenerator.

Figure 3: Schematic diagram of the structure of a closed impeller compressor.

Figure 4: Schematic diagram of the closed impeller.

Figure 5: Schematic diagram of the structure of the back cover, the blade and the sleeve body.

FIG. 6 : Front view of FIG. 5 .

FIG. 7 : Side view of FIG. 5 .

FIG. 8 : Sectional view at position A-A in FIG. 7 .

Among them, 1, shaft; 2, impeller; 201, rear cover; 202, blade; 203, sleeve body; 204, front cover; 205, runner; 206, air outlet; 3, stator; 301, air hole; 4, motor .

Detailed ways

The present invention will be further described below in conjunction with the examples. However, the scope of the present invention is not limited to the following examples. It will be understood by those skilled in the art that various changes and modifications can be made in the present invention without departing from the spirit and scope of the inventions.

Example 1 Dual-shaft power generation gas turbine

A dual-shaft power generation gas turbine includes a first rotor system and a second rotor system, as shown in FIG. 1 ; the first rotor system includes a first rotating shaft 100, a first motor 200, a compressor 300, a first turbine 400 and The combustion chamber 500, wherein the first motor 200, the compressor 300 and the first turbine 400 are sequentially sleeved on the first rotating shaft 100 from front to back, the exhaust end of the compressor 300 is communicated with the inlet end of the combustion chamber 500, and the combustion The exhaust end of the chamber 500 communicates with the intake end of the first turbine 400;

The second rotor system includes a second rotating shaft 600, a second turbine 700 and a second motor 800, wherein the second turbine 700 and the second motor 800 are sequentially sleeved on the second rotating shaft 600 from front to back;

The first rotating shaft 100 and the second rotating shaft 600 are coaxially disposed, and the first rotating shaft 100 is disposed before the second rotating shaft 600 ; the exhaust end of the first turbine 400 communicates with the intake end of the second turbine 700 .

The first motor 200 may be a heuristic integrated motor. When the compressor 300 is started, it is driven by an integrated motor that drives the compressor 300 to rotate first as a motor, and then disengages after being accelerated to be able to operate independently, and then acts as a generator, and the first turbine 400 rotates to drive the first shaft. 100 rotates to drive the first motor 200 to generate electricity.

The combustion chamber 500 may be a rotating recirculation combustion chamber or an axial flow combustion chamber. The axis of the combustion chamber 500 is coaxial with the first rotating shaft 100 , and is arranged around the first rotating shaft 100 and located at the compressor 300 or/and the first turbine 400 . the periphery.

The first turbines 400 may be arranged in two or more and connected in series on the first rotating shaft 100; radial bearings may be arranged between adjacent turbines. During operation, the exhaust gas from the combustion chamber 500 or the second outlet of the regenerator 900 pushes each turbine to rotate in turn to do work.

The second turbines 600 may be arranged in two or more and connected in series on the second rotating shaft 600; radial bearings may be arranged between adjacent turbines. During operation, the exhaust gas of the first turbine 400 pushes each of the second turbines 600 to rotate in turn to perform work.

The power of the first motor 200 is 20-30KW, the power of the second motor 800 is 120-130KW, and the overall power of the gas turbine is 140-160KW.

During operation, the working medium (such as air) enters from the inlet of the compressor 300, and after being compressed by the compressor 300, enters the combustion chamber 500 from its outlet, and enters the intake end of the first turbine 400 after combustion, and pushes the first turbine 400 to rotate to do work. After the working medium does work by the first turbine 400, it enters the second turbine 700 from the exhaust end of the first turbine 400, and the outflow gas pushes the second turbine 700 to rotate to do work, thereby driving the second motor 800 to generate electricity.

Example 2 Dual-shaft power generation gas turbine

A dual-shaft power generation gas turbine includes a first rotor system and a second rotor system, as shown in FIG. 2; the first rotor system includes a first rotating shaft 100, a first motor 200, a compressor 300, a first turbine 400, The combustion chamber 500 and the regenerator 900, wherein the first motor 200, the compressor 300 and the first turbine 400 are sequentially sleeved on the first rotating shaft 100 from front to back;

The first rotating shaft 100 and the second rotating shaft 600 are coaxially disposed, and the first rotating shaft 100 is disposed before the second rotating shaft 600;

The regenerator 900 is provided with a first inlet, a first outlet, a second inlet and a second outlet; the outlet of the compressor 300 is communicated with the first inlet of the regenerator 900, and the first outlet of the regenerator 900 is connected to the combustion chamber. The inlet end of the chamber 500 is communicated with the inlet end of the combustion chamber 500 and the intake end of the first turbine 400 is communicated; the exhaust end of the first turbine 400 is communicated with the second inlet of the regenerator 900, The second outlet communicates with the intake end of the second turbine 700 .

During operation, the working medium (such as air) enters from the inlet of the compressor 300. After being compressed by the compressor 300, it enters the first inlet of the regenerator 900 from its outlet, and flows out from the first outlet, and enters the combustion chamber 500 after being burned. The intake end of the first turbine 400 pushes the first turbine 400 to rotate to do work; after the working fluid passes through the first turbine 400 to do work, it enters the second inlet of the regenerator 900 from the exhaust end of the first turbine 400, and then enters the second inlet of the regenerator 900 at the regenerator. After heat exchange in the 900, the gas flows out from its second outlet and enters the second turbine 700. The outflowing gas pushes the second turbine 700 to rotate to do work, and then drives the second motor 800 to generate electricity.

Example 3 Dual-shaft power generation gas turbine

The difference from Embodiment 1 and Embodiment 2 is: the compressor 300 in Embodiment 1 and Embodiment 2 is a closed impeller compressor; the closed impeller compressor includes a rotating shaft 1, and a closed impeller is sleeved on the rotating shaft 1 2 and the motor 4, the closed impeller 2 is equipped with a stator 3 on the outer cover, as shown in Figure 3.

The closed impeller includes a rear cover 201 , blades 202 , a sleeve body 203 and a front cover 204 , as shown in FIGS. 4 to 8 , wherein the rear cover 201 is disposed at the rear end of the sleeve body 203 , and the rear cover 201 and the sleeve body 203 An integrated through hole in the center is used to be sleeved and fixed on the rotating shaft 1; the blade 202 is arranged around the sleeve body 203 and rotates in the same direction, one end of the blade 202 is connected to the outer wall of the sleeve body 203, and the other end is connected to the end face of the rear cover 201; The front cover 204 is covered on the blade 202, and the front cover 204 is in the shape of a truncated truncated ring; the intake surface of the front cover 204 is a curved surface that smoothly transitions along the contour of the ridge line of the blade 202, and the back air surface is provided with a surface that matches the end of the blade 202. Grooves, the ends of the blades 202 corresponding to the grooves are embedded in the grooves for tight fitting connection; a flow channel 205 is formed between the blades 202 , the rear cover 201 and the front cover 204 ; the tail of the front cover 204 and the rear cover 201 The air outlets 206 are spaced apart, and the gas flows out from the air outlet 206 through the flow channel 205 from the front of the blade 202 .

The rear cover 201 , the blades 202 and the sleeve body 203 are integrally formed, as shown in FIGS. 5 to 8 .

The outer edge of the blade 202 protrudes from the end surface of the rear cover 201 in the axial direction.

The blade 202 includes a longer main blade and a shorter splitter blade, and the main blade and the splitter blade are arranged at intervals in sequence. The grooves of the front cover 204 are divided into main blade grooves and splitter blade grooves, which are respectively provided at the ends of the main blade and the splitter blade.

The leading edge of the front cover 204 protrudes from the leading edge of the blade 202 , or is flatter than the leading edge of the blade 202 , or shorter than the leading edge of the blade 202 .

The front cover 204 may be made of carbon fiber composite material.

The part of the stator 3 facing the front cover 204 is evenly opened with one or more circles of air holes 301, which can be decomposed into axial and radial airflow after air intake, and the radial airflow will make the impeller suspend in the stator 3 to stabilize Rotation, the axial airflow pushes the impeller backwards, and the stator 3 acts as an air bearing and also acts as a radial bearing and a thrust bearing.

The above-mentioned closed impeller compressor is provided with a detachable front cover, the front cover is in the shape of a truncated cone, the air inlet surface is a curved surface with a smooth transition along the contour of the blade ridge line, and the back air surface is provided with a groove that matches the end of the blade. When working, the friction loss is small, the flow resistance is small, and the efficiency is high; when working, the front cover and the blade are tightly engaged, and the gas flows out from the air outlet through the flow channel at the front of the blade, and the gas leakage is very small. The front cover is made of carbon fiber composite material. The impeller is light in overall weight and has high strength. The blade (metal material) will expand when rotating, while the front cover does not expand. Therefore, with the increase of rotation speed and time, the blade and the front cover will not expand. The occlusion between the grooves will become tighter and tighter, which is suitable for high-speed rotation conditions. The provision of splitter vanes can not only reduce the blockage of the inlet air flow, but also improve the slip coefficient of the impeller outlet, which not only improves the efficiency of the impeller, but also improves the overall efficiency of the compressor due to the improved flow field at the impeller outlet. Equipped with an oblique thrust structure, the stator is used as an air bearing and plays the role of a radial bearing and a thrust bearing at the same time (gas is introduced into the gap between the stator and the impeller from the air hole, so that a uniform and stable air film is formed in the gap, so that the The impeller rotates stably in the stator, thus playing the role of air bearing), which can reduce or even replace the original radial bearing and thrust bearing. When the stator is also used as a thrust bearing, if other radial bearings are installed on the rotating shaft, it is equivalent to having multiple radial bearings for support, the overall vibration is small, and the operation is stable. If there are no other radial bearings or only a small amount of radial bearings on the rotating shaft, the length of the rotating shaft can be shortened, it is easy to ensure the coaxiality of the parts on the shaft, the processing is easier, the integration is high, and the reliability of the whole machine is high. In addition, the air intake of the air hole will be applied to the front cover, which can better prevent the separation of the blade and the groove of the front cover, and is more suitable for high-speed rotation conditions.

Example 4 Dual-shaft power generation gas turbine

The difference from Example 1, Example 2, and Example 3 is:

A thrust bearing and a thrust plate are arranged on the first rotating shaft 100 or/and the second rotating shaft 600 .

At least one radial bearing is arranged on the first rotating shaft 100 or/and the second rotating shaft 600 . Specifically, for the first rotor system, the radial bearing can be arranged at the front end of the rotating shaft, which can solve the problem that the front end of the first rotating shaft 100 cantilever is too long and the rotating shaft is offset due to the magnetic force of the motor. In addition, radial bearings may also be provided on one side or both sides of the first motor 200 , or between the compressor 300 and the first turbine 400 .

The foregoing examples are provided to those skilled in the art to fully disclose and describe how to make and use the claimed embodiments, and are not intended to limit the scope of the disclosure herein. Modifications obvious to those skilled in the art are intended to be within the scope of the appended claims.

Claims

A dual-shaft power generation gas turbine, characterized in that it includes a first rotor system and a second rotor system; the first rotor system includes a first rotating shaft, a first motor, a compressor, a first turbine, and a combustion chamber, wherein the first rotor system A motor, a compressor and a first turbine are sequentially sleeved on the first rotating shaft from front to back. The exhaust end of the compressor is communicated with the inlet end of the combustion chamber, and the exhaust end of the combustion chamber is connected with the intake end of the first turbine. connected;

The second rotor system includes a second rotating shaft, a second turbine and a second motor, wherein the second turbine and the second motor are sequentially sleeved on the second rotating shaft from front to back;

The first rotating shaft and the second rotating shaft are coaxially arranged, and the first rotating shaft is arranged before the second rotating shaft; the exhaust end of the first turbine is communicated with the intake end of the second turbine.
The dual-shaft power generation gas turbine according to claim 1, characterized in that: the first motor is an heuristic integrated motor; or/and: the combustion chamber is a rotating recirculation combustion chamber or an axial flow combustion chamber, and the combustion chamber is The shaft center is coaxial with the first rotating shaft, is arranged around the first rotating shaft and is located at the periphery of the compressor or/and the first turbine.
The dual-shaft power generation gas turbine according to claim 1, wherein the first rotor system further comprises a regenerator; the regenerator is provided with a first inlet, a first outlet, a second inlet and a second outlet ; The outlet of the compressor is communicated with the first inlet of the regenerator, the first outlet of the regenerator is communicated with the inlet end of the combustion chamber, the exhaust end of the first turbine is communicated with the second inlet of the regenerator, and the regenerator is communicated with the second inlet of the regenerator. The second outlet of the second turbine communicates with the intake end of the second turbine.
The dual-shaft power generation gas turbine according to claim 1, 2 or 3, characterized in that: the compressor is a closed impeller compressor; the closed impeller compressor comprises a rotating shaft, and a closed impeller and a motor are sleeved on the rotating shaft ; The closed impeller includes a rear cover, a blade, a sleeve body and a front cover, wherein the rear cover is arranged at the rear end of the sleeve body, and the rear cover and the center of the sleeve body are provided with an integral through hole for sleeved and fixed on the rotating shaft The blades are arranged around the sleeve body and rotate in the same direction, one end of the blade is connected with the outer wall of the sleeve, and the other end is connected with the end face of the rear cover; the front cover is set on the blade, and the front cover is in the shape of a circular cone; The surface is a curved surface with a smooth transition along the contour of the ridge line of the blade, and the back air surface is provided with grooves that match the ends of the blades, and the ends of the blades corresponding to the grooves are embedded in the grooves for tight connection; the blades, the rear cover and the front cover A flow channel is formed between the front cover and the rear cover. There are air outlets separated by blades, and the gas flows out from the air outlet from the front of the blades through the flow channel.
The dual-shaft power generation gas turbine according to claim 4, wherein the rear cover, the blade and the sleeve are integrally formed;

Or/and: the outer edge of the blade protrudes from the end face of the rear cover in the axial direction;

Or/and: the blade includes a longer main blade and a shorter branch blade, and the main blade and the branch blade are arranged at intervals in sequence. The front cover grooves are divided into main blade grooves and splitter blade grooves, which are respectively set at the ends of the main blades and the splitter blades;

or/and: the leading edge of the front cover protrudes from the leading edge of the blade, or is flat to the leading edge of the blade, or is shorter than the leading edge of the blade;

or/and: the front cover is made of carbon fiber composite material.
The dual-shaft power generation gas turbine according to claim 4, characterized in that: the closed impeller cover is provided with a stator, and the part of the stator facing the front cover is evenly opened with one or more circles of air holes, which can be decomposed into Axial and radial airflow, the radial airflow will make the impeller suspended in the stator and rotate stably, the axial airflow will push the impeller backward, and the stator acts as an air bearing and plays the role of a radial bearing and a thrust bearing at the same time.
The dual-shaft power generation gas turbine according to claim 1, 2 or 3, wherein a thrust bearing and a thrust plate are arranged on the first rotating shaft or/and the second rotating shaft.
The dual-shaft power generation gas turbine according to claim 1, 2 or 3, wherein: at least one radial bearing is arranged on the first rotating shaft or/and the second rotating shaft;

or/and: for the first rotor system, the radial bearing is provided at the front end of the rotating shaft;

Or/and: the radial bearing is arranged on one side or both sides of the first electric machine, or between the compressor and the first turbine.
The dual-shaft power generation gas turbine according to claim 1, 2 or 3, characterized in that: the first turbines are arranged in two or more and are connected in series on the first rotating shaft; adjacent turbines are arranged or not arranged radial bearing;

Or/and: the second turbines are arranged in two or more and are connected in series on the second rotating shaft; radial bearings are arranged or not arranged between adjacent turbines.
The dual-shaft power generation gas turbine according to claim 1, 2 or 3, wherein the power of the first motor is 20-30KW, the power of the second motor is 120-130KW, and the overall power of the gas turbine is 140-160KW.