Micro gas turbine

Abstract

The invention provides a micro gas turbine. The turbine comprises a high-pressure machine, a low-pressure machine and a regenerator, wherein the high-pressure machine comprises a gas compressor, a high-pressure turbine, a combustion chamber and a high-pressure rotor system, the low-pressure machine comprises a low-pressure turbine, a motor, a low-pressure rotor system, and a flue gas chamber, thegas inlet end of the gas compressor communicates with the outside, the exhaust end of the gas compressor communicates with a first inlet of the regenerator, a first outlet of the regenerator communicates with an inlet of the combustion chamber, the exhaust end of the combustion chamber communicates with the gas inlet end of the high-pressure turbine, the exhaust end of the high-pressure turbine communicates with the gas inlet end of the low-pressure turbine, the exhaust end of the low-pressure turbine communicates with an inlet of the flue gas chamber, an outlet of the flue gas chamber communicates with a second inlet of the regenerator, and a second outlet of the regenerator communicates with the outside. According to the turbine, through reasonable matching arrangement of the regenerator, the micro gas turbine with a compact structure is formed, so that the thermal efficiency can be sufficiently improved.

Description

technical field [0001] The invention relates to the field of gas turbines, in particular to a micro gas turbine. Background technique [0002] The micro gas turbine is a newly developed small heat engine, its stand-alone power ranges from 25 to 300kW, and its basic technical features are radial flow impeller machinery and regenerative cycle. The gas turbine electric unit in the prior art has the following defects: [0003] The micro gas turbine regenerator is one of the most critical components to improve the thermal efficiency of the micro gas turbine. The regenerator is a heat exchanger for heat exchange between compressed air and high-temperature gas. Its use makes the improvement of the thermal efficiency of the micro gas turbine the most direct. Most efficient and reliable. The reason why micro gas turbines have a thermal efficiency of more than 30% is that the key technology is the use of regenerators. Without regenerators, the thermal efficiency of micro gas turbine...

AI Technical Summary

Problems solved by technology

In the prior art, the combination configuration of the regenerator and the micro gas turbine is different, which will greatly affect the thermal efficiency of the micro gas turbine, and the unreasonable combination will cause unnecessary heat loss along the way

[0004] At the same time, in the prior art, the high-speed rotor of the micro gas turbine is connected with the rotor of the motor to generate electricity. The centrifugal force of the machine and turbine impeller is as high as 100MPa, which requires extremely high bearing strength

At high speed, the rotor system of the micro gas turbine motor unit has poor stability due to the deviation of coaxiality. As the rotor speed increases, the axial force on the rotor will further increase. Under the high speed working state of the micro gas turbine, the coupling The axial force of the rotor on the bearing is relatively large, which may easily cause damage to the coupling

[0005] In addition, for the rotor system, the traditional installation method in which the thrust bearing is arranged between the compressor and the turbine is a cantilever shaft structure for the entire rotor system, and the center of gravity is biased towards the turbine side, resulting in poor stability of the entire rotor system ; At the same time, because the high temperature experienced by the hot end parts of the turbine will be transmitted to the thrust bearing during operation, resulting in an increase in the operating temperature of the bearing, which will easily cause the expansion and wear of the shaft system and cause the rotor system to be stuck; in addition, the traditional installation method, If the thrust bearing is installed between the coupling and the compressor, the large-diameter thrust disc may block the air inlet of the micro gas turbine; if the thrust bearing is installed on the coupling facing the motor, the shaft of the micro gas turbine rotor All the axial force acts on the coupling, resulting in damage to the coupling, and there will be a problem that the thrust bearing has no installation position

It can be seen that the layout structure of the traditional micro gas turbine system limits the further increase of the speed of the micro gas turbine.

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