A turbine blade with transverse meandering and alternately shortening and shortening channels inside

A technology of turbine blades and short passages, which is applied to the supporting components of blades, machines/engines, mechanical equipment, etc., can solve the problems of ineffective air film and low cooling efficiency, so as to improve cooling conditions, increase heat exchange capacity, Enhanced internal cooling effect

Active Publication Date: 2022-05-10
SHENYANG AEROSPACE UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The characteristics of the flow field in this area make the film cooling almost impossible, and the cooling efficiency is extremely low

Method used

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  • A turbine blade with transverse meandering and alternately shortening and shortening channels inside
  • A turbine blade with transverse meandering and alternately shortening and shortening channels inside
  • A turbine blade with transverse meandering and alternately shortening and shortening channels inside

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] When the chord length of the turbine rotor blade in this embodiment is 37mm and the blade height (blade body 1 height) is 44mm, the thickness of the inner rib 15 is 1mm. The aspect ratio of the short channel is 2.92, the expansion ratio is 1:7, and the maximum section aspect ratio of the channel is 1.23. The number of channels is 7, and the number of corners is 6. The air film holes 9 are arranged in the second half of the root of the suction surface 7, the hole diameter is 0.5mm, the hole spacing is 1.5mm, the jet angle is 30°, and the azimuth angle is 60°. The overflow hole 14 is arranged in the center of the outer wall of the U-shaped bend near the trailing edge 6 of the meandering channel 11 distributed along the chord direction, and the cross-section is a rectangle of 1*2 mm; The cooling efficiency is increased by 13-18%.

Embodiment 2

[0034] When the chord length of the turbine rotor blade in this embodiment is 44mm and the blade height (blade body 1 height) is 53mm, the thickness of the inner rib 15 is 1.5mm. The aspect ratio of the short channel is 3, the shrinkage ratio is 1:6, and the maximum section aspect ratio of the channel is 1.3. The number of channels is 7, and the number of corners is 6. The air film holes 9 are arranged in the second half of the root of the suction surface 7, the hole diameter is 0.6mm, the hole spacing is 2mm, the jet angle is 30°, and the azimuth angle is 75°. The overflow hole 14 is arranged in the center of the outer wall of the U-shaped bend near the trailing edge 6 of the meandering channel 11 distributed along the chord direction, and has a rectangular cross-section of 1.2*2.5mm; the second half of the root of the suction surface 7 of the turbine rotor blade The overall cooling efficiency is increased by 15-20%.

Embodiment 3

[0036] When the chord length of the turbine rotor blade in this embodiment is 45mm and the blade height (blade body 1 height) is 69mm, the inner rib 15 is 2mm thick. The aspect ratio of the short channel is 3.2, the expansion ratio is 1:5.5, and the maximum section aspect ratio of the channel is 1.35. The number of channels is 9, and the number of corners is 8. The air film holes 9 are arranged in the second half of the root of the suction surface 7, the hole diameter is 0.8mm, the hole spacing is 2.5mm, the jet angle is 45°, and the azimuth angle is 90°. The overflow hole 14 is arranged in the center of the outer wall of the U-shaped bend near the trailing edge 6 of the meandering channel 11 distributed along the blade chord direction, and the cross section is a rectangle of 1.5*3 mm; The cooling efficiency is increased by 17-22%.

[0037] The present invention is different from the longitudinal meandering channel 11 with the length-to-diameter ratio exceeding 10. The lengt...

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Abstract

The invention relates to a turbine blade with transverse meandering and alternately shortening and shortening passages inside, including a blade body, a tenon, a base connecting the blade body and the tenon, and a middle blade root. The blade body includes a leading edge, a trailing edge, and a protruding The suction surface and the concave pressure surface, the blade body is equipped with spoiler columns and the meandering channels along the height direction of the blade body and along the direction of the blade chord surrounded by internal ribs, and the meandering channels distributed along the direction of the blade chord are close to the trailing edge There is an overflow hole in the center of the outer wall of the U-shaped bend at the center, an impact hole is opened on the inner rib between the cold air cavity at the leading edge and the winding channel along the height direction of the blade body, and there are splits on the trailing edge outside the blade body and along the height of the blade body. direction and air film holes along the chord direction. The invention can make up for the defect of insufficient external cooling by strengthening the internal heat exchange of the blades, and at the same time make the air film cooling play a good role, so as to meet the higher requirements for cooling brought about by the continuous increase of the working temperature of the turbine.

Description

technical field [0001] The invention belongs to the technical field of cooling the turbine rotor blades of gas turbines, and in particular relates to a turbine blade with transverse meandering and alternately shortening and expanding channels inside. Background technique [0002] The gas turbine turbine is a turbomachinery that exchanges energy with the airflow. The extremely high enthalpy of the airflow is converted into kinetic energy through the turbine, and then converted into mechanical energy through the turbine rotor blades. Under the impact of high-temperature and high-pressure gas, the mechanical properties of the metal materials used to manufacture turbine rotor blades drop sharply due to the increase in temperature. Therefore, it is particularly important to effectively cool the blades during high-intensity operation. The current turbine rotor blades generally have the problem of a cliff-like decline in the film cooling efficiency in the second half of the root of...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18
CPCF01D5/186
Inventor 张魏曾睿李广超朱建勇寇志海毛晓东
Owner SHENYANG AEROSPACE UNIVERSITY
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