A Non-Uniform Horizontal and Longitudinal Slot Turbine Outer Ring Structure

A non-uniform, horizontal and vertical technology, applied in the machine/engine, engine function, stator and other directions, can solve the problems of fast gas flow, gas leakage, use efficiency and film cooling efficiency, etc., to improve gas use efficiency, clearance gap The effect of reducing leakage flow and improving sealing performance

Active Publication Date: 2022-04-15
SHENYANG AEROSPACE UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

After air film cooling is adopted, the leakage fluid in the tip clearance is mixed with the mainstream fluid in the channel, and the flow is very complicated. On the one hand, seepage will form in the leading edge area, resulting in energy loss of the mainstream fluid. On the other hand, the blade pressure surface and suction surface The pressure difference will form a gap leakage flow, thereby disturbing the normal and stable flow of the main flow inside the cascade
Due to the smooth surface of the outer ring, the pressure between cascade stages is high, and the gas flow speed is fast, when the gas flows from the cascade inlet to the cascade outlet, a large amount of gas leakage will be caused, resulting in a decrease in the use efficiency of gas and the film cooling efficiency of the outer ring

Method used

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  • A Non-Uniform Horizontal and Longitudinal Slot Turbine Outer Ring Structure
  • A Non-Uniform Horizontal and Longitudinal Slot Turbine Outer Ring Structure
  • A Non-Uniform Horizontal and Longitudinal Slot Turbine Outer Ring Structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] The axial chord length of the blade 8 is 40mm; the axial length of the outer casing 1 is 50mm, the thickness of the inner casing 2 and the outer casing 1 is 10mm, and the height of the connecting body 3 is 8mm; the inner diameter of the impact hole 6 is 0.8mm, two rows of impact holes 6, each row 30, evenly arranged, the impact angle of the impact hole 6 is 85°; the number of 3 connectors is 12, evenly arranged; two exhaust film holes 7, each exhaust film hole 7 is 30, and the air film hole is 7 The diameter is 0.5mm; the height of the circumferential rib groove 4 is 0.5mm, the gap between the rib grooves is 0.2mm, the width of the rib groove sealing tooth is 1.3mm, the chamfer of the top of the sealing tooth is 62.5°, and the overall length of the circumferential rib groove 4 is 25mm, evenly distributed on the inlet side of the cascade; the height of the axial rib groove 5 is 0.5mm, the width of the bottom of the rib groove is 0.2mm, the width of the rib groove sealing ...

Embodiment 2

[0026] The axial chord length of the blade 8 is 40mm; the axial length of the outer casing 1 is 50mm, the thickness of the inner casing 2 and the outer casing 1 is 10mm, and the height of the connecting body 3 is 8mm; the diameter of the impact hole 6 is 0.8mm, and two rows of impact holes 6, each 25 rows, evenly arranged, the impact angle of the impact hole 6 is 90°; the number of 3 connectors is 20, evenly arranged; two exhaust film holes 7, each exhaust film hole 7 is 25, the air film The inner diameter of hole 7 is 0.5mm; the height of circumferential rib groove 4 is 0.5mm, the gap between rib grooves is 0.2mm, the width of rib groove sealing teeth is 0.6mm, the chamfer of the tooth top of sealing teeth is 62.5°, and the circumferential rib groove 4 The overall length is 20mm, evenly distributed on the inlet side of the cascade; the height of the axial rib groove 5 is 0.5mm, the width of the bottom of the rib groove is 0.2mm, the width of the rib groove sealing teeth is 0.2...

Embodiment 3

[0029]The axial chord length of the blade 8 is 40mm; the axial length of the outer casing 1 is 50mm, the thickness of the inner casing 2 and the outer casing 1 is 10mm, and the height of the connecting body 3 is 8mm; the inner diameter of the impact hole 6 is 0.8mm, and two rows of impact holes 6, each 25 rows, evenly arranged, the impact angle of the impact hole 6 is 80°; the number of 3 connectors is 20, evenly arranged; two exhaust film holes 7, each exhaust film hole 7 is 30, the air film The inner diameter of the hole 7 is 0.5mm; the height of the circumferential rib groove 4 is 0.5mm, and the rib groove gap is 0.2mm. mm, increasing successively toward the outlet of the cascade. The top chamfer of the sealing tooth is 62.5°, the overall length of the circumferential rib groove 4 is 30mm, and is unevenly distributed on the inlet side of the cascade; the height of the axial rib groove 5 is 0.5mm, and the width of the bottom of the rib groove is 0.2mm. The groove sealing to...

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Abstract

A non-uniform horizontal and vertical groove turbine outer ring structure, including an impact body, the impact body is composed of an inner shell, an outer shell and a connecting body, a number of impact holes are arranged on the outer shell, and a number of impact holes are arranged on the inner wall of the inner shell Rib grooves, the rib grooves include circumferential rib grooves and axial rib grooves, the inner wall of the inner shell at the inlet of the cascade is provided with circumferential rib grooves along the circumferential direction, and several circumferential rib grooves are unevenly or evenly distributed On the inner wall of the inner casing, the inner wall of the inner casing at the outlet of the cascade is provided with axial rib grooves in the axial direction, and several axial rib grooves are evenly distributed on the inner wall of the inner casing, and the inner casing on the inner casing A number of air film holes are opened, and the outer shell and the inner shell are fixedly installed through the connecting body. When the gas passes through the rib groove, the gas velocity in the groove is obviously reduced because the rib groove hinders the gas. Compared with the turbine outer ring without rib groove structure, after adding the horizontal and vertical groove structure, the gap leakage flow is reduced by 1-3%.

Description

technical field [0001] The invention relates to a gas turbine turbine outer ring structure, in particular to a gas turbine outer ring structure with non-uniform horizontal and vertical grooves. Background technique [0002] The gas turbine rotates the rotor blades through the impact of gas on the rotor blades to output work, and the outer ring structure of the turbine separates the rotating rotor blades from the stationary parts. In the cascade passage, the gas temperature is already higher than the temperature resistance limit of the turbine components, which must be effectively cooled. The outer ring is usually cooled by film cooling, which separates the high-temperature gas in the cascade channel from the outer wall. After air film cooling is adopted, the leakage fluid in the tip clearance is mixed with the mainstream fluid in the channel, and the flow is very complicated. On the one hand, seepage will form in the leading edge area, resulting in energy loss of the mainst...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D9/00F01D25/12
CPCF01D9/00F01D25/12F05D2260/202
Inventor 张魏张子阳李广超杨鹏寇志海毛晓东
Owner SHENYANG AEROSPACE UNIVERSITY
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