Gas-leading sealing structure of gas turbine

Abstract

The invention relates to a gas-leading sealing structure of a gas turbine. The gas-leading sealing structure comprises a shell, a flame barrel, a rotor and a turbine guider hollow blade, wherein an air compressor rotor and a turbine rotor are arranged on the rotor; compressed air channels are formed between the shell and the outer wall of the flame barrel as well as between the shell and the front wall of the flame barrel; and comb tooth sealing structures which are respectively positioned in front of the air compressor rotor, behind the turbine rotor, on the front wall and on the inner wall are arranged on the rotor. Compressed air in the invention can reach the comb tooth sealing structures through the channels and seals lubricating oil and the flame barrel which are arranged behind the air compressor rotor and the turbine rotor, so that the structural design of an engine is simplified and clear; the mass of the engine can be greatly reduced; and therefore, the push ratio optimization is greatly improved, the energy can be effectively saved, and cost can be reduced.

Description

technical field [0001] The invention relates to an air-bleed sealing structure, in particular to a gas-turbine air-bleed sealing structure. Background technique [0002] The existing gas turbine bleed air sealing structure mostly uses pipe joints installed from the compressor outlet or bypass to connect the pipelines to provide compressed air meeting a certain pressure for the engine air source system, including the starting system of the engine, air conditioning and booster systems, etc. , such as the Boeing 737NG series engine, the bleed air comes from the 9th and 5th high-pressure compressors of the engine, and the 9th one-way valve opens to provide the air source at low speeds. In ground-use gas turbines (or aeroderivative gas turbines), external air pumps, pipelines, and air filters are often used to achieve good sealing effects. For the design of the bleed air sealing structure of the above-mentioned gas turbine, it is necessary to calculate the bleed air pipeline, th...

AI Technical Summary

Problems solved by technology

For the design of the bleed air sealing structure of the above-mentioned gas turbine, it is necessary to calculate the bleed air pipeline, the flow resistance of the nozzle, etc., which requires a large amount of calculation, high difficulty, complex assembly, and cumbersome structure. The quality and volume of the engine have a great impact, which greatly reduces the maneuverability of the aircraft. Another example is the design and calculation of two pipelines for the Boeing 737NG series, resulting in high cost and high cost.

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