Double-layer wall outer circle structure of gas turbine

A gas turbine, double-wall technology, applied in mechanical equipment, engine components, machines/engines, etc., can solve problems such as aerodynamic losses, and achieve the effects of reducing aerodynamic losses, reducing air-conditioning volume, and increasing the density of flow ratio.

Inactive Publication Date: 2017-02-01
SHENYANG AEROSPACE UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • Double-layer wall outer circle structure of gas turbine
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  • Double-layer wall outer circle structure of gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] Embodiment 1: The axial chord length of the blade is 40mm. The axial inner length of the outer wall of the outer ring (the length between the two side walls) is 50mm, the height of the side wall is 8mm, the axial length of the support is 4mm, the diameter of the impact hole is 0.8mm, and there are two rows of impact holes, 30 in each row, evenly arranged , 6 bearings and their connecting rods, arranged evenly. The axial length of the inner wall is 46mm, the radius of rotation of the inner wall is 0.3m, one row of air film holes in the bearing cavity, two rows of air film holes outside the bearing cavity, one row on each side of the bearing cavity, 30 film holes for each exhaust, and the diameter of the air film holes 0.5mm, the height of the bearing cavity is 4mm, and the axial length is 20mm. Impact hole 85 degrees. The radius of the inner wall is greater than the radius of the support edge, the inner wall is located on the support edge, and the rotation speed of the...

Embodiment 2

[0024] Embodiment 2: The axial chord length of the blade is 60mm. The axial inner length of the outer wall of the outer ring (the length between the two side walls) is 70mm, the height of the side wall is 10mm, the axial length of the support is 5mm, the diameter of the impact hole is 1mm, and there are two rows of impact holes, 50 in each row, evenly arranged. There are 16 bearings and connecting rods arranged evenly. The axial length of the inner wall is 68mm, the rotation radius of the inner wall is 0.5m, there are 2 rows of air film holes in the bearing cavity, 4 rows of air film holes outside the bearing cavity, 2 rows on each side of the bearing cavity, 40 film holes for each exhaust, and the diameter of the air film holes 0.5mm, the height of the bearing cavity is 5mm, and the axial length is 30mm. Impact hole 60 degrees. The radius of the inner wall is larger than the radius of the support edge, the inner wall is located on the support edge, and the speed of the inne...

Embodiment 3

[0026] Embodiment 3: The axial chord length of the blade is 120mm. The axial inner length of the outer wall of the outer ring (the length between the two side walls) is 140mm, the height of the side wall is 20mm, the axial length of the support is 10mm, the diameter of the impact hole is 1.2mm, and there are two rows of impact holes, 40 in each row, evenly arranged , 30 bearings and connecting rods, evenly arranged. The axial length of the inner wall is 136mm, the radius of rotation of the inner wall is 1m, there are 2 rows of air film holes in the bearing cavity, 4 rows of air film holes outside the bearing cavity, 2 rows in each of two bearing chambers, 40 film holes for each exhaust, and the diameter of the air film holes is 0.8 mm, the height of the bearing cavity is 8mm, and the axial length is 50mm. Impact hole 80 degrees. The radius of the inner wall is greater than the radius of the support edge, the inner wall is located on the support edge, and the speed of the inn...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/02F01D5/14F01D5/18
CPCF01D5/02F01D5/147F01D5/18
Inventor 李广超王昊峰张魏寇志海毛晓东张国臣
Owner SHENYANG AEROSPACE UNIVERSITY
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