Gas Turbine Compressor Cascade Shroud with Spatial Structure

Abstract

The invention belongs to the technical field of gas turbines, and particularly relates to a gas turbine compressor shrouding strip of a space structure. The gas turbine compressor shrouding strip comprises a belt ring, equal sections, a moving ring and a driving device. The belt ring is in the form of a mouth table and used for the connection of the overall structural support to the outside. The multiple equal sections are arranged and evenly arranged on the belt ring and are used for changing and adjusting the throat area of the intake air. The moving ring is used for centralized linkage of the equal sections in transmission connection. The driving device is used for adjusting the moving ring through the operating parameter output by a computer to control the equal sections so as to change the amount of the intake air. By the adoption of the gas turbine compressor shrouding strip, the equal sections and the moving ring are mounted and connected together by using the belt ring in the form of the mouth table, the structure is compact and has high three-dimensionality, it is ensured that the ends of a plurality of guide vanes are on the same circumference, the roundness is good, thecombination is convenient, and the gas turbine compressor shrouding strip is suitable for mass production; and in addition, the angle change of the guide vanes can be accurately controlled, so that the guide vanes can always be kept in a reasonable position, the improvement in the performance of the compressor is guaranteed, and the power of the gas turbine is enhanced.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, and relates to a compressor structure, in particular to a space-structured gas turbine compressor cascade shroud. Background technique [0002] Gas turbine engines are also called gas turbines. Gas turbines have a series of advantages such as small size, light weight, and fast start-up. They have made great progress in various fields and are widely used in power generation, ship power, vehicle power, natural gas, oil pipeline transportation, etc. The field is an important manifestation of a country's technological, industrial and national defense strength. A gas turbine is composed of three parts: a compressor, a combustion chamber, and a turbine. The compressor is a component in a gas turbine engine that uses high-speed rotating blades to work on the air to increase the air pressure. In order to reduce the impact loss of air flow, the kinetic energy obtained by the gas in the impeller is c...

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Problems solved by technology

[0003] The traditional cascade shrouds are welded guide vanes between the inner and outer ring shrouds. The precision of the manufacturing process is extremely low, the deformation is large, and the guide vanes are only simple arcs, resulting in uneven airflow of the compressor and resistance. Larger, which seriously affects the performance of the compressor; at present, the gas turbine compressor cascade shroud with a space structure is first processed by full circle turning, and then the groove of the space structure is milled out by a five-axis gantry, and after repeated rough and fine machining Complete, not only the processing price is relatively expensive, but also the structural shape is single and prone to stress deformation. After the guide vanes are inserted into the groove, the guide vanes will not be evenly arranged on the same circumference, which seriously affects the air intake of the throat of the compressor. Stability, and the design strength of the space structure is poor, which makes it difficult to arrange production of the gas turbine cascade shroud, and the production cost is high, which is not conducive to batch production and processing; At this time, the adjustability of the shroud of the cascade is poor, the angular position of the guide vane is fixed, and the angle of the guide vane cannot be changed, resulting in a slightly slower increase in the power of the gas turbine, a slow increase in the speed of the rotor, and a significant surge phenomenon of the rotor at ultra-high revolutions , affect the further improvement of the rotor speed, and at the same time, the effect of increasing the boost ratio is poor, and the poor spatial structure of the cascade shroud will seriously affect the overall performance of the gas turbine

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