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Multistage turbine type micro gas turbine

A micro-turbine, turbine-type technology, applied in the directions of gas turbine devices, lubrication of turbine/propulsion devices, and mechanical equipment, can solve the complexity and uncertainty of large projects, increase the number of compressor fan stages, and single-stage boost ratio. Reduce and other problems, to achieve the effect of reasonable weight distribution, lower pressure drop ratio, and increase working capacity

Pending Publication Date: 2020-04-21
TECH XANADU OF RESONATORY SOLAR SYSTD CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The low-pressure compressor has to reduce the number of revolutions in order to link with the fan, and the single-stage boost ratio is reduced. In order to achieve the total boost ratio, the number of stages of the compressor fan has to be increased.
In this way, the weight of the compressor is difficult to reduce
[0006] To sum up, the traditional mechanical single rotor has many limitations in function, while the traditional multi-rotor system has huge engineering complexity and uncertainty

Method used

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  • Multistage turbine type micro gas turbine
  • Multistage turbine type micro gas turbine
  • Multistage turbine type micro gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0085] Such as Figure 1-5 As shown, the present embodiment provides a multi-stage turbine micro gas turbine, which has a high-pressure machine 1 and a low-pressure machine 2, and the high-pressure machine 1 includes a high-pressure casing, a compressor 11, a high-pressure turbine group 12, a combustion chamber 13, and a high-pressure bearing group 15 , the first rotating shaft 14, the starter motor 16, the low-pressure machine 2 includes the low-pressure casing, the low-pressure turbine group 21, the generator 22, the low-pressure bearing group 24, the second rotating shaft 23; the compressor 11, the high-pressure turbine group 12, the high-pressure bearing group 15 1. The first rotating shaft 14 is set in the high-pressure casing, and the high-pressure casing is sleeved on one end of the combustion chamber 13. The compressor 11 and the high-pressure turbine group 12 are sequentially sleeved on the first rotating shaft 14. The compressor 11 is far away from the end of the high...

Embodiment 2

[0111] The difference between this embodiment and Embodiment 1 is that, as Figure 11 As shown, a regenerator 3 is provided in this embodiment.

[0112] Wherein, in the structure of the regenerator 3 provided in this embodiment, the regenerator 3 has a first inlet 31 , a first outlet 32 ​​, a second inlet 33 and a second outlet 34 . When the regenerator 3 is provided, the intake end of the compressor 11 communicates with the outside world, the exhaust end communicates with the first inlet 31 of the regenerator, and the first outlet 32 ​​of the regenerator communicates with the inlet of the combustion chamber 13, so The exhaust end of the combustion chamber 13 communicates with the intake end of the high-pressure turbine group 12, the exhaust end of the high-pressure turbine group 12 communicates with the intake end of the low-pressure turbine group 21, and the gas discharged from the high-pressure compressor 11 enters the regenerator 3 , enter the combustion chamber 13 after ...

Embodiment 3

[0120] In this embodiment, a low-pressure rotor system structure is provided.

[0121] Such as Figure 12 As shown, the low-pressure rotor system includes a second rotating shaft 23 and a low-pressure bearing set 24;

[0122] Wherein, the second rotating shaft 23 includes a low-pressure turbine shaft and a low-voltage motor shaft, the low-pressure turbine shaft and the low-voltage motor shaft are connected by a coupling, the low-pressure turbine group 21 is arranged on the low-pressure turbine shaft, and the generator 22 is arranged on the low-voltage motor shaft;

[0123] The low-pressure turbine set 21 includes a centrifugal turbine 211 and an axial flow turbine 212, a first bearing 241 is arranged between the centrifugal turbine 211 and the axial flow turbine 212, and a second bearing 242 is arranged between the low-pressure turbine set 21 and the coupling , The third bearing 243, the low-voltage motor shaft and the motor body are rotationally connected through the fourth...

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Abstract

The invention provides a multi-stage turbine type micro gas turbine. The multi-stage turbine type micro gas turbine comprises a high-pressure machine and a low-pressure machine. The high-pressure machine comprises a high-pressure casing, a gas compressor, a high-pressure turbine set, a combustion chamber, a high-pressure rotor system and a starting motor. The low-pressure machine comprises a low-pressure casing, a low-pressure turbine set, a generator, a low-pressure rotor system and a smoke chamber. A gas inlet end of the gas compressor is communicated with the outside, a gas outlet end of the gas compressor is communicated with an inlet end of the combustion chamber, an outlet end of the combustion chamber is communicated with a gas inlet end of the high-pressure turbine set, a gas outlet end of the high-pressure turbine set is communicated with a gas inlet end of the low-pressure turbine set, a gas outlet end of the low-pressure turbine set is communicated with an inlet of the smokechamber, and an outlet of the smoke chamber is communicated with the outside. High-pressure turbines and the low-speed turbines are arranged in multiple stages to form a multi-column turbine-stage micro gas turbine, and the micro gas turbine is reasonable in structural layout, stable in operation and high in efficiency.

Description

technical field [0001] The invention relates to the field of gas turbines, in particular to a multi-stage turbine 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. There are following defects in the micro gas turbine electric unit in the prior art: [0003] The overall structure adopted by the current micro gas turbine includes single-rotor and multi-rotor. The single-rotor structure has only one shaft as a whole, and the compressor and turbine are all on this shaft. The structure is simple and the economy is good. Theoretically, the compressor of a single-rotor structure micro gas turbine can be made into any number of stages to achieve a certain boost ratio. However, due to the structural limitation of the single rotor, all parts are installed on the same main shaft. When t...

Claims

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Application Information

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IPC IPC(8): F02C6/02F02C7/06F02C3/04F02C3/14F02C7/00F01D25/24
CPCF02C6/02F02C7/06F02C3/04F02C3/14F02C7/00F01D25/24
Inventor 靳普于宁
Owner TECH XANADU OF RESONATORY SOLAR SYSTD CO LTD
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