CN112502833A

CN112502833A - Double-shaft power generation gas turbine

Info

Publication number: CN112502833A
Application number: CN202011288826.4A
Authority: CN
Inventors: 靳新中
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-11-18
Filing date: 2020-11-18
Publication date: 2021-03-16
Also published as: WO2022105214A1

Abstract

The invention discloses a double-shaft power generation gas turbine, which comprises a first rotor system and a second rotor system; the first rotor system comprises a first rotating shaft, a first motor, a gas compressor, a first turbine and a combustion chamber, wherein the gas exhaust end of the gas compressor is communicated with the inlet end of the combustion chamber, and the gas exhaust end of the combustion chamber is communicated with the gas inlet end of the first turbine; the second rotor system comprises a second rotating shaft, a second turbine and a second motor; the first rotating shaft and the second rotating shaft are coaxially arranged; the exhaust end of the first turbine is in communication with the intake end of the second turbine. The invention comprises two power generation shafts, the two power generation shafts are decoupled, the rotating speeds are not necessarily the same, and the pneumatic design of the turbine can be flexibly matched conveniently. The length of the rotating shaft is short, the coaxiality of parts on the shaft is easily guaranteed, the processing is easier, the integration level is high, and the reliability of the whole machine is high. When the pressure drop ratio of the compressor is high, two or more turbines can be arranged to fully utilize the pressure difference generated by the compressor and obtain high power generation efficiency.

Description

Double-shaft power generation gas turbine

Technical Field

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

Background

The industrial gas turbine mainly comprises three parts of a compressor, a combustion chamber and a turbine. After entering the compressor, the air is compressed into high-temperature and high-pressure air, then the air is supplied to a combustion chamber for fuel combustion, and the generated high-temperature and high-pressure gas expands in a turbine to do work.

In the prior art, each part of the gas turbine is arranged on a shaft, and the gas compressor and the turbine are arranged on the shaft, so that the gas turbine has a simple structure and good economical efficiency, but when the required power is higher, the shaft length is longer, and the design difficulty is high. Theoretically, the compressor of the micro gas turbine with the single-rotor structure can be made into any number of stages to achieve a certain pressure increase ratio. However, the structural limitation of the single rotor enables all parts to be arranged on the same main shaft, when the rotating speed of the single rotor suddenly drops, the high-pressure part of the air compressor can seriously drop in efficiency because the rotating speed cannot be enough, meanwhile, the load of the low-pressure part of the air compressor can sharply rise, the low-pressure air compressor can cause surging when the low-pressure air compressor is in overload operation, and the surging is not allowed in normal operation. To solve this problem, guide vanes are usually added before the compressor or bleed air is used in the middle stage of the compressor, i.e. a part of the pressurized air is bled off to reduce the load of the low-pressure part of the compressor. The method has obvious defects, not only can greatly reduce the efficiency, but also has not very obvious effect on the compressor with high pressure ratio.

In addition, the used impeller of compressor is divided into open type, half open type and closed type among the present gas turbine, and the characteristics of three kinds of impellers are as follows:

(1) open impeller: the friction loss and the flow resistance are large, the impeller efficiency is the lowest, the vibration is easy to generate, and the impeller is not suitable for working at high rotating speed.

(2) Semi-open impeller: the friction loss and flow resistance are less than open, the efficiency is higher, and certain rigidity and strength are provided, so that the device can work at higher peripheral speed.

(3) Closed impeller: the friction loss and the flow resistance are both minimum, the efficiency is highest, but the structure is complex and heavy, and the wheel cover can generate huge stress on the blades during rotation, so the strength is poor, and the wheel cover is not suitable for being used under the working condition of high rotating speed.

Most of the impellers adopted by the existing gas compressor are semi-open impellers. The problems that the compressor needs to overcome are how to obtain smaller friction loss and flow resistance, higher efficiency, lightness and high strength.

The bearing group that present compressor generally adopted a plurality of radial bearing and thrust bearing to constitute often needs the pivot of sufficient length to install, and the problem of bringing is that compressor axial dimensions increases, if with the compressor of this type be used in equipment such as micro gas turbine generating set, can increase the shared space of equipment, increases whole weight simultaneously, is unfavorable for the design of integrating, and arranges that processing and assembly error that a plurality of bearings brought can increase, and processing and assembly degree of difficulty are high.

Disclosure of Invention

Aiming at the prior art, the invention provides a double-shaft power generation gas turbine, which does not need a longer rotating shaft, is easy to ensure the coaxiality of parts on a shaft, is easier to process, has high integration level and high overall reliability.

The invention is realized by the following technical scheme:

a dual shaft power generating gas turbine comprising a first rotor system and a second rotor system; the first rotor system comprises a first rotating shaft, a first motor, a gas compressor, a first turbine and a combustion chamber, wherein the first motor, the gas compressor and the first turbine are sequentially sleeved on the first rotating shaft from front to back;

the second rotor system comprises 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 in front of the second rotating shaft; the exhaust end of the first turbine is in communication with the intake end of the second turbine.

Further, the first motor is a starting and starting integrated motor. The gas compressor is driven by the starting integrated motor when being started, the starting integrated motor firstly serves as a motor to drive the gas compressor to rotate, the gas compressor is separated after the gas compressor is accelerated to be capable of independently operating, then the gas compressor serves as a generator, and the first turbine rotates to drive the first rotating shaft to rotate so as to drive the first motor to generate electricity.

Furthermore, the combustion chamber is a rotary backflow combustion chamber or an axial flow combustion chamber, the axis of the combustion chamber is coaxial with the first rotating shaft, and the combustion chamber is arranged around the first rotating shaft and is positioned on the periphery of the gas compressor or/and the first turbine.

Further, the first rotor system further comprises a regenerator; the heat 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 second outlet of the regenerator is communicated with the air inlet end of the second turbine. When the heat regenerator works, a working medium (such as air) enters from an inlet of the air compressor, is compressed by the air compressor, enters a first inlet of the heat regenerator from an outlet of the air compressor, flows out of a first outlet, enters a combustion chamber for combustion, enters an air inlet end of a first turbine and pushes the first turbine to rotate to do work; after working medium works through the first turbine, the working medium enters the second inlet of the heat regenerator from the exhaust end of the first turbine, exchanges heat in the heat regenerator and then flows out of the second outlet of the heat regenerator to enter the second turbine, and the flowing gas pushes the second turbine to rotate to do work so as to drive the second motor to generate power.

Further, 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 comprises a rear cover, blades, a sleeve body and a front cover, wherein the rear cover is arranged at the tail end of the sleeve body, and the rear cover and the center of the sleeve body are provided with an integrated through hole for being sleeved and fixed on the rotating shaft; the blades are arranged around the sleeve body and rotate towards the same direction, one end of each blade is connected with the outer wall of the sleeve body, and the other end of each blade is connected with the end face of the rear cover; the front cover is covered on the blade and is in a circular truncated cone shape; the air inlet surface of the front cover is a curved surface which is in smooth transition along the profile of the ridge line of the blade, the air outlet surface is provided with grooves which are matched with the end parts of the blade, and the end parts of the blade corresponding to the grooves are embedded into the grooves and are in tight fit connection; a flow passage is formed among the blade, the rear cover and the front cover; the air outlet is separated by the blades between the tail part of the front cover and the rear cover, and the air flows out of the air outlet from the front part of the blades through the flow channel.

Furthermore, the rear cover, the blades and the sleeve body are integrally formed.

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

Further, the blade includes longer main leaf and shorter splitter blade, and main leaf and splitter blade set up at interval in proper order. The front cover groove is divided into a main blade groove and a splitter blade groove which are respectively arranged corresponding to the end parts of the main blade and the splitter blade.

Furthermore, the front edge of the front cover protrudes out of the front edge of the blade, or is flat with the front edge of the blade, or is shorter than the front edge of the blade.

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

Furthermore, the stator is arranged outside the closed impeller cover, one circle or more circles of air holes are uniformly formed in the part, opposite to the front cover, of the stator, the part can be decomposed into axial and radial air flows after air is fed, the impeller is suspended in the stator to stably rotate through the radial air flows, the impeller is pushed backwards through the axial air flows, and the stator serves as an air bearing and plays a role of a radial bearing and a thrust bearing at the same time.

Furthermore, a thrust bearing and a thrust disc 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 may be disposed at the front end of the rotating shaft, and the problems that the cantilever at the front end of the first rotating shaft is too long and the rotating shaft is deviated due to the magnetic force of the motor may be solved. In addition, a radial bearing may be provided on one or both sides of the first electric machine, or between the compressor and the first turbine.

Further, the first turbine is provided with two or more than two turbines which are connected in series on the first rotating shaft; radial bearings may be provided between adjacent turbines. When the gas turbine works, the exhaust gas at the second outlet of the combustion chamber or the heat regenerator sequentially pushes each turbine to rotate to do work.

Further, the second turbine is provided with two or more than two turbines which are connected in series on the second rotating shaft; radial bearings may be provided between adjacent turbines. When the gas turbine works, the exhaust of the first turbine sequentially pushes the second turbines to rotate to do work.

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

The double-shaft power generation gas turbine comprises two power generation shafts, the two power generation shafts are decoupled, the rotating speeds are not necessarily the same, and the pneumatic design of the turbine can be flexibly matched conveniently. Compared with the adoption of a longer rotating shaft, the double-shaft power generation gas turbine provided by the invention has the advantages that the high power is ensured, the required length of each rotating shaft is shorter, the length of the rotating shaft is shortened (the smaller the number of bearings on the rotating shaft is, the shorter the length of the rotating shaft is, the shorter the overall length of equipment is, the higher the integration is), the coaxiality of parts on the shaft is easily ensured, the processing is easier, the integration degree is high, and the reliability of the whole machine is high. When the pressure drop ratio of the compressor is high, two or more first turbines or/and second turbines can be arranged to fully utilize the pressure difference generated by the compressor and obtain high power generation efficiency. The gas compressor of the invention adopts the closed impeller, can obtain smaller friction loss and flow resistance, higher efficiency, lightness and high strength.

The closed impeller compressor is provided with the detachable front cover which is in a circular truncated cone shape, the air inlet surface is a curved surface which is in smooth transition along the ridge line profile of the blade, and the air outlet surface is provided with the groove which is matched with the end part of the blade, so that the closed impeller compressor has the advantages of small friction loss, small flow resistance and high efficiency in work; during operation, the front cover is tightly occluded with the blades, gas flows out from the air outlet through the flow channel from the front parts of the blades, and gas leakage is little. The protecgulum is made by carbon-fibre composite, and the whole quality of impeller is light and have high strength, and blade (metal material) can expand during the rotation, and the protecgulum does not expand, consequently along with the increase of pivoted speed up, time increase, interlock between the recess of blade and protecgulum can be more and more tight (be provided with the stator when as air bearing, its admission also can be applyed on the protecgulum, further prevents the recess separation of blade and protecgulum), is fit for high-speed rotatory operating mode. The splitter blade is arranged, so that the blockage of inlet airflow can be reduced, the sliding coefficient of the outlet of the impeller can be improved, the efficiency of the impeller is improved, and the overall efficiency of the gas compressor can be improved due to the improvement of the flow field of the outlet of the impeller. The closed impeller gas compressor is provided with the oblique thrust structure, the stator is used as an air bearing and simultaneously plays the roles of a radial bearing and a thrust bearing (gas is introduced into a gap between the stator and the impeller from an air hole, so that a uniform and stable gas film is formed in the gap, the impeller stably rotates in the stator, and the air bearing is played), and the original radial bearing and the original thrust bearing can be reduced or even replaced. When the stator is simultaneously used as a thrust bearing, if other radial bearings are arranged on the rotating shaft, a plurality of radial bearings are equivalently supported, the whole vibration is small, and the operation is stable. If no other radial bearing or only a small number of radial bearings are arranged on the rotating shaft, the length of the rotating shaft is shortened, the coaxiality of parts on the shaft is easily ensured, the processing is easier, the integration level is high, and the reliability of the whole machine is high.

The various terms and phrases used herein have the ordinary meaning as is well known to those skilled in the art. To the extent that the terms and phrases are not inconsistent with known meanings, the meaning of the present invention will prevail.

Drawings

FIG. 1: the schematic structural diagram of the two-shaft power generation gas turbine of example 1.

FIG. 2: the schematic structural diagram of the two-shaft power generation gas turbine of example 2.

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

FIG. 3: the structure schematic diagram of the closed impeller compressor.

FIG. 4: the structure of the closed impeller is shown schematically.

FIG. 5: the structure of the rear cover, the blades and the sleeve body is schematically shown.

FIG. 6: fig. 5 is a front view.

FIG. 7: fig. 5 is a side view.

FIG. 8: fig. 7 is a sectional view taken at the position a-a.

Wherein, 1, a rotating shaft; 2. an impeller; 201. a rear cover; 202. a blade; 203. a sleeve body; 204. a front cover; 205. a flow channel; 206. an air outlet; 3. a stator; 301. air holes; 4. an electric motor.

Detailed Description

The present invention will be further described with reference to the following 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 may be made to the invention without departing from the spirit and scope of the invention.

Example 1 two-shaft Power Generation gas turbine

A dual shaft power generating gas turbine comprising a first rotor system and a second rotor system, as shown in fig. 1; the first rotor system comprises a first rotating shaft 100, a first motor 200, a gas compressor 300, a first turbine 400 and a combustion chamber 500, wherein the first motor 200, the gas 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 gas compressor 300 is communicated with the inlet end of the combustion chamber 500, and the exhaust end of the combustion chamber 500 is communicated with the 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, 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 arranged, and the first rotating shaft 100 is arranged in front of 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 starter-integrated motor. When the compressor 300 is started, the compressor 300 is driven by the starting integrated motor, the starting integrated motor is firstly used as a motor to drive the compressor 300 to rotate, and is disengaged after the compressor is accelerated to be capable of independently operating, and then the compressor is used as a generator, and the first turbine 400 rotates to drive the first rotating shaft 100 to rotate so as to drive the first motor 200 to generate electricity.

The combustor 500 may be a rotary reflow combustor or an axial-flow combustor, and the axis of the combustor 500 is coaxial with the first shaft 100, is arranged around the first shaft 100, and is located at the periphery of the compressor 300 or/and the first turbine 400.

The first turbine 400 may be provided in two or more and connected in series to the first shaft 100; radial bearings may be provided between adjacent turbines. In operation, the exhaust gas at the second outlet of the combustion chamber 500 or the heat regenerator 900 sequentially pushes each turbine to rotate and do work.

The second turbine 600 may be provided in two or more and connected in series to the second rotating shaft 600; radial bearings may be provided between adjacent turbines. In operation, the exhaust of the first turbine 400 in turn propels each of the second turbines 600 to rotate to produce work.

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

During operation, a working medium (such as air) enters from the inlet of the compressor 300, is compressed by the compressor 300, enters the combustion chamber 500 from the outlet of the compressor, and enters the air inlet end of the first turbine 400 after being combusted, so as to push the first turbine 400 to rotate and do work; after the working medium works through the first turbine 400, the working medium enters the second turbine 700 from the exhaust end of the first turbine 400, and the outflowing gas pushes the second turbine 700 to rotate and work, so as to drive the second motor 800 to generate power.

EXAMPLE 2 two-shaft Power Generation gas turbine

A dual shaft power generating gas turbine comprising a first rotor system and a second rotor system, as shown in fig. 2; the first rotor system comprises a first rotating shaft 100, a first motor 200, a gas compressor 300, a first turbine 400, a combustion chamber 500 and a heat regenerator 900, wherein the first motor 200, the gas 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 arranged, and the first rotating shaft 100 is arranged in front of the second rotating shaft 600;

the heat 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 heat regenerator 900, the first outlet of the heat regenerator 900 is communicated with the inlet end of the combustion chamber 500, and the exhaust end of the combustion chamber 500 is communicated with the air inlet end of the first turbine 400; the exhaust end of the first turbine 400 communicates with a second inlet of the regenerator 900 and a second outlet of the regenerator 900 communicates with the intake end of the second turbine 700.

During operation, a working medium (such as air) enters from an inlet of the compressor 300, is compressed by the compressor 300, enters a first inlet of the heat regenerator 900 from an outlet thereof, flows out from a first outlet, enters the combustion chamber 500 for combustion, enters an air inlet end of the first turbine 400, and pushes the first turbine 400 to rotate and do work; after working medium works through the first turbine 400, the working medium enters the second inlet of the heat regenerator 900 from the exhaust end of the first turbine 400, exchanges heat in the heat regenerator 900 and then flows out from the second outlet of the heat regenerator, the working medium enters the second turbine 700, and the flowing gas pushes the second turbine 700 to rotate to work, so that the second motor 800 is driven to generate power.

EXAMPLE 3 two-shaft Power Generation gas turbine

The differences from the embodiment 1 and the embodiment 2 are that: the compressor 300 in the

embodiments

1 and 2 is a closed impeller compressor; the closed impeller compressor comprises a rotating shaft 1, a closed impeller 2 and a motor 4 are sleeved on the rotating shaft 1, and a stator 3 is arranged outside the closed impeller 2, as shown in figure 3.

The closed impeller comprises a rear cover 201, blades 202, a sleeve body 203 and a front cover 204, as shown in fig. 4-8, wherein the rear cover 201 is arranged at the tail end of the sleeve body 203, and a through hole which is formed by integrating the rear cover 201 and the sleeve body 203 is used for being sleeved and fixed on the rotating shaft 1; the blades 202 are arranged around the sleeve body 203 and rotate towards the same direction, one end of each blade 202 is connected with the outer wall of the sleeve body 203, and the other end of each blade 202 is connected with 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 a circular truncated cone shape; the air inlet surface of the front cover 204 is a curved surface which is in smooth transition along the ridge line profile of the blade 202, the air outlet surface is provided with grooves which are matched with the end parts of the blade 202, and the end parts of the blade 202 corresponding to the grooves are embedded into the grooves and are in tight fit connection; a flow passage 205 is formed among the blade 202, the rear cover 201 and the front cover 204; an air outlet 206 is formed between the rear part of the front cover 204 and the rear cover 201 and is partitioned by the blades 202, and air flows out of the air outlet 206 from the front part of the blades 202 through a flow passage 205.

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

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

The blades 202 include a longer main blade and a shorter splitter blade, and the main blade and the splitter blade are sequentially arranged at intervals. The groove of the front cover 204 is divided into a main blade groove and a splitter blade groove, which are respectively arranged corresponding to the ends of the main blade and the splitter blade.

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

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

One or more circles of air holes 301 are uniformly formed in the part, opposite to the front cover 204, of the stator 3, air can be decomposed into axial air flow and radial air flow after entering the air, the impeller is suspended in the stator 3 to stably rotate through the radial air flow, the impeller is pushed backwards through the axial air flow, and the stator 3 serves as an air bearing and plays a role of a radial bearing and a thrust bearing at the same time.

The closed impeller compressor is provided with the detachable front cover which is in a circular truncated cone shape, the air inlet surface is a curved surface which is in smooth transition along the ridge line profile of the blade, and the air outlet surface is provided with the groove which is matched with the end part of the blade, so that the closed impeller compressor has small friction loss, small flow resistance and high efficiency in work; during operation, the front cover is tightly occluded with the blades, gas flows out from the air outlet through the flow channel from the front parts of the blades, and gas leakage is little. The protecgulum is made by carbon-fibre composite, and the whole quality of impeller is light and have high strength, and blade (metal material) can expand during the rotation, and the protecgulum does not expand, consequently along with the increase of pivoted speed up, time, interlock between the recess of blade and protecgulum can be more and more tight, is fit for high-speed rotatory operating mode. The splitter blade is arranged, so that the blockage of inlet airflow can be reduced, the sliding coefficient of the outlet of the impeller can be improved, the efficiency of the impeller is improved, and the overall efficiency of the gas compressor can be improved due to the improvement of the flow field of the outlet of the impeller. Be equipped with slant thrust structure, the stator has played radial bearing and thrust bearing's effect simultaneously as air bearing (from the gas pocket in to the clearance between stator and the impeller in let in gas, make the clearance form even stable air film, make the impeller steady rotation in the stator to play air bearing's effect), can reduce or even replace original radial bearing and thrust bearing. When the stator is simultaneously used as a thrust bearing, if other radial bearings are arranged on the rotating shaft, a plurality of radial bearings are equivalently supported, the whole vibration is small, and the operation is stable. If no other radial bearing or only a small number of radial bearings are arranged on the rotating shaft, the length of the rotating shaft is shortened, the coaxiality of parts on the shaft is easily ensured, the processing is easier, the integration level is high, and the reliability of the whole machine is high. In addition, the air inlet of the air hole is applied to the front cover, so that the separation of the blade and the groove of the front cover can be better prevented, and the air hole is more suitable for the working condition of high-speed rotation.

EXAMPLE 4 Dual shaft Power generating gas turbine

The differences from the

embodiments

1, 2 and 3 are that:

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

At least one radial bearing is disposed on the first rotating shaft 100 or/and the second rotating shaft 600. Specifically, for the first rotor system, the radial bearing may be disposed at the front end of the rotating shaft, and the problems that the cantilever at the front end of the first rotating shaft 100 is too long and the rotating shaft is deviated due to the magnetic force of the motor may be solved. Further, a radial bearing may be provided at one or both sides of the first motor 200 or between the compressor 300 and the first turbine 400.

The above examples are provided to those of ordinary skill 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 apparent to those skilled in the art are intended to be within the scope of the appended claims.

Claims

1. A dual shaft power generating gas turbine, characterized by: comprises a first rotor system and a second rotor system; the first rotor system comprises a first rotating shaft, a first motor, a gas compressor, a first turbine and a combustion chamber, wherein the first motor, the gas compressor and the first turbine are sequentially sleeved on the first rotating shaft from front to back;

2. The two-shaft power generating gas turbine according to claim 1, characterized in that: the first motor is a starting integrated motor; or/and: the combustion chamber is a rotary backflow 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 positioned on the periphery of the gas compressor or/and the first turbine.

3. The two-shaft power generating gas turbine according to claim 1, characterized in that: the first rotor system further comprises a regenerator; the heat 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 second outlet of the regenerator is communicated with the air inlet end of the second turbine.

4. The two-shaft power generating 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 comprises a rear cover, blades, a sleeve body and a front cover, wherein the rear cover is arranged at the tail end of the sleeve body, and the rear cover and the center of the sleeve body are provided with an integrated through hole for being sleeved and fixed on the rotating shaft; the blades are arranged around the sleeve body and rotate towards the same direction, one end of each blade is connected with the outer wall of the sleeve body, and the other end of each blade is connected with the end face of the rear cover; the front cover is covered on the blade and is in a circular truncated cone shape; the air inlet surface of the front cover is a curved surface which is in smooth transition along the profile of the ridge line of the blade, the air outlet surface is provided with grooves which are matched with the end parts of the blade, and the end parts of the blade corresponding to the grooves are embedded into the grooves and are in tight fit connection; a flow passage is formed among the blade, the rear cover and the front cover; the air outlet is separated by the blades between the tail part of the front cover and the rear cover, and the air flows out of the air outlet from the front part of the blades through the flow channel.

5. The two-shaft power generating gas turbine according to claim 4, wherein: the rear cover, the blades and the sleeve body are integrally formed;

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

or/and: the blade includes longer main leaf and shorter splitter blade, and main leaf and splitter blade set up at interval in proper order. The front cover groove is divided into a main blade groove and a splitter blade groove which are respectively arranged corresponding to the end parts of the main blade and the splitter blade;

or/and: the front edge of the front cover protrudes out of the front edge of the blade, or is parallel to the front edge of the blade, or is shorter than the front edge of the blade;

or/and: the front cover is made of carbon fiber composite material.

6. The two-shaft power generating gas turbine according to claim 4, wherein: the closed impeller is covered by a stator, one or more circles of air holes are uniformly formed in the part, opposite to the front cover, of the stator, the part can be decomposed into axial and radial air flows after air is introduced, the impeller is suspended in the stator to stably rotate by the radial air flows, the impeller is pushed backwards by the axial air flows, and the stator is used as an air bearing and plays a role of a radial bearing and a thrust bearing at the same time.

7. The two-shaft power generating gas turbine according to claim 1, 2 or 3, characterized in that: and a thrust bearing and a thrust disc are arranged on the first rotating shaft or/and the second rotating shaft.

8. The two-shaft power generating gas turbine according to claim 1, 2 or 3, characterized in that: 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 arranged at the front end of the rotating shaft;

or/and: the radial bearing is arranged on one side or two sides of the first motor or between the compressor and the first turbine.

9. The two-shaft power generating gas turbine according to claim 1, 2 or 3, characterized in that: the first turbines are arranged in two or more than two and are connected in series on the first rotating shaft; radial bearings are arranged or not arranged between adjacent turbines;

or/and: the second turbines are arranged in two or more and are connected in series on the second rotating shaft; radial bearings may or may not be provided between adjacent turbines.

10. The two-shaft power generating gas turbine according to claim 1, 2 or 3, characterized in that: the power of the first motor is 20-30 KW, the power of the second motor is 120-130 KW, and the total power of the gas turbine is 140-160 KW.