Modified heavy-duty gas turbine

A gas turbine and heavy-duty technology, which is applied in the direction of gas turbine devices, liquid fuel engines, mechanical equipment, etc., can solve the problem of high technical risk and long time. It usually takes 20 to 30 years from the first prototype to design and finalization, and it is not accepted by the market. problem, to achieve the effect of increasing power and performance

Pending Publication Date: 2018-10-16
XIAMEN ZHONGGUANNENG GAS TURBINE TECH CO LTD
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Problems solved by technology

Heavy-duty gas turbine products require long life, high reliability, and high performance. Newly designed heavy-duty gas turbines are difficult to design and have high technical risks. They need to invest a lot of money in component testing and verification. At the ...

Method used

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  • Modified heavy-duty gas turbine

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Embodiment

[0010] Example: such as figure 1 As shown, the present invention is a modified heavy-duty gas turbine, including an intake casing assembly 1, a rotor assembly 2, a compressor front stator assembly 3, a compressor middle stator assembly 4, a compressor rear stator assembly 5, a combustion chamber 6, The turbine subassembly 8, the exhaust diffuser assembly 9 and the bearing assemblies 101, 7, 10 etc. are composed. All stator components are all horizontal split structures. The gas turbine stator assembly includes intake casing assembly 1, compressor front stator assembly 3, compressor middle stator assembly 4, compressor rear stator assembly 5, combustion chamber 6, turbine stator assembly 8, front, middle and rear fulcrum bearings Assembly and exhaust diffuser 9, all stator assemblies are completely split horizontally. The gas turbine rotor assembly 2 is composed of working blades, discs, journals and tie rod bolts. The compressor and turbine rotors are respectively connected ...

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Abstract

The invention relates to a modified heavy-duty gas turbine. The modified heavy-duty gas turbine comprises an air inlet casing assembly, wherein a gas compressor stator assembly, a rotor assembly, a combustion chamber, a turbine stator assembly, an exhausting pressure expander and a bearing assembly are sequentially arranged at the right end of the air inlet casing assembly; all stator assemblies are of horizontal opposite opening structures; the lower half part of a front supporting point bearing assembly is integrally casted with the lower half part of an air inlet casing; the lower half parts of an intermediate supporting point bearing and a rear supporting point bearing are correspondingly mounted at the lower half part of a combustion chamber casing and the lower half part of the exhausting pressure expander. The modified heavy-duty gas turbine has the advantages that the technical risk can be effectively reduced; few new tools and devices are needed, so that the manufacturing period and the construction cost can be decreased; and meanwhile, the utilization rate of spare parts of an original machine is high, so that the reliability can be ensured.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, in particular to a modified heavy-duty gas turbine. Background technique [0002] With the vigorous development of the civil gas turbine industry, the competition in the gas turbine product market is increasingly intensified. How to speed up the development process of heavy-duty gas turbine products while ensuring a high degree of technical maturity has become the key to the development of gas turbine products. Heavy-duty gas turbine products require long life, high reliability, and high performance. Newly designed heavy-duty gas turbines are difficult to design and have high technical risks. They need to invest a lot of money in component testing and verification. At the same time, the development cycle is long. From the first prototype to design finalization, it usually takes 20 From 20 to 30 years, even if the development is successful, it is often not accepted by the market because the d...

Claims

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Application Information

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IPC IPC(8): F02C3/00F04D29/26F04D29/40F01D9/02F01D5/14
CPCF01D5/141F01D9/02F02C3/00F04D29/26F04D29/403
Inventor 崔荣繁
Owner XIAMEN ZHONGGUANNENG GAS TURBINE TECH CO LTD
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