Gas turbine rotor supporting system based on sliding bearings and thrust disc
A technology for sliding bearings and gas turbines, which is applied in the direction of sliding contact bearings, rigid supports of bearing components, bearings for rotating motion, etc. It can solve the problem that rolling bearings cannot adapt to heavy loads, affect the stable operation of the rotor system, have large impacts and require long working life, etc. problem, to achieve the effect of good rotation stability, solid structure, and low friction power consumption
Active Publication Date: 2021-11-26
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology
However, rolling bearings cannot adapt to environments with heavy loads, large shocks, and long working life requirements, which will affect the stability of the rotor system or cause frequent maintenance and replacement
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[0023] In order to make the technical means, creative features, goals and effects of the present invention easy to understand, the following embodiments will specifically illustrate the gas turbine rotor support system based on sliding bearings and thrust discs provided by the present invention in conjunction with the accompanying drawings.
[0024] In the description of the embodiments of the present invention, it should be understood that the terms "center", "spanwise", "chordwise", "upper", "lower", "left", "right", "left end" , "right end", "vertical", "horizontal", "top", "bottom", "inner", "outer" and other indicated orientations or positional relationships are based on the orientations or positional relationships described in the drawings, and are only In order to facilitate the description of the invention and simplify the description, it does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a ...
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The invention discloses a gas turbine rotor supporting system based on sliding bearings and a thrust disc. The supporting system comprises a shaft, the thrust disc arranged at one end of the shaft and three sliding bearings, the three sliding bearings comprise a radial sliding bearing, a radial thrust sliding bearing and a thrust sliding bearing, the radial thrust sliding bearing and the thrust sliding bearing are arranged at one end of the shaft, the radial thrust sliding bearing and the thrust sliding bearing are connected through a bearing supporting leg, and the radial sliding bearing is arranged at the other end of the shaft and connected with the bearing supporting leg through a force bearing frame. The gas turbine rotor supporting system based on the sliding bearings and the thrust disc is based on the sliding bearings and the thrust disc, all fulcrum positions adopt the sliding bearings, the advantages of the sliding bearings are fully played, and the gas turbine rotor supporting system has the advantages of being high in bearing capacity, high in radial positioning precision, high in impact resistance, high in rotation stability and small in friction power consumption.
Description
technical field [0001] The invention relates to the technical field of gas turbines, in particular to a gas turbine rotor support system based on sliding bearings and thrust discs. Background technique [0002] A gas turbine is a device that converts the thermal energy of a high-temperature, high-pressure combustion gas into mechanical energy. The power turbine is an important part of the power output of the gas turbine. Due to the gradual expansion of the gas in the turbine, the power turbine bears a huge axial force. As the power turbine is a large-scale working component, the working environment of its large-scale rotor system has heavy loads, large impacts, and large vibrations, which may easily cause damage to the supporting components and affect the reliable operation of the components. [0003] In the prior art, in the supporting layout of rotating machines, rolling bearings are usually used as the basis for supporting them. However, rolling bearings cannot adapt to ...
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IPC IPC(8): F16C17/02F16C17/08F16C33/04F16C35/02
CPCF16C17/02F16C17/08F16C33/04F16C35/02
Inventor 王晏根王会社赵祥敏
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI