Double wall outer ring structure of a gas turbine turbine

Abstract

The invention discloses a double-layer wall outer circle structure of a gas turbine, and belongs to a gas turbine structure. The double-layer wall outer circle structure of the gas turbine comprises an annular impact wall and blades. The impact wall comprises an outer wall body and an inner wall body. A plurality of impact holes are uniformly formed in the outer wall body. Lateral wall bodies are arranged at the two ends of the outer wall body. Supporting edges are arranged under the lateral wall bodies, and the inner wall body is located on the supporting edges. A plurality of air film holes are uniformly formed in the inner wall body. The inner wall body is connected with the outer wall body through a connecting mechanism. Under the condition that the gaps between blade tips and the outer circle inner wall body keep unchanged, the relative movement speed of the blade tips and the inner wall body is lowered through rotation of the inner wall body, and the pneumatic loss caused by relative movement is lowered by 5-10%. Due to rotation of the inner wall body, the speed of leaking fuel gas in the blade tip gaps and near the inner wall body is lowered, and the density-flow ratio between cold air sprayed by the air film holes and the leaking fuel gas in the gaps is improved, which means that the needed cold air amount is reduced in order to reach a certain cooling effect.

Description

technical field [0001] The invention relates to a gas turbine turbine structure, in particular to a double-wall outer ring structure of the gas turbine turbine. Background technique [0002] The gas turbine rotates the rotor blades through the impact of the gas on the rotor blades to output work. The rotor blade speed is usually above 10,000 rpm. The outer ring structure of the turbine separates the rotating rotor blades from the stationary parts, and is affected by the temperature changes of the rotating parts during operation. Influenced by factors such as deformation caused by centrifugal force, aerodynamic load, processing and assembly, a certain gap must be reserved between the rotor blade and the outer ring, and the high-temperature gas passes through the blade gap from the pressure side of the blade to the suction side. Leakage flow is formed, which will form a complex vortex system, especially the mixing of leakage flow and main channel gas will cause serious aerodyn...

AI Technical Summary

Problems solved by technology

[0002] The gas turbine rotates the rotor blades through the impact of the gas on the rotor blades to output work. The rotor blade speed is usually above 10,000 rpm. The outer ring structure of the turbine separates the rotating rotor blades from the stationary parts, and is affected by the temperature changes of the rotating parts during operation. Influenced by factors such as deformation caused by centrifugal force, aerodynamic load, processing and assembly, a certain gap must be reserved between the rotor blade and the outer ring, and the high-temperature gas passes through the blade gap from the pressure side of the blade to the suction side. Leakage flow is formed, which will form a complex vortex system, especially the mixing of leakage flow and main channel gas will cause serious aerodynamic loss

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