Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof

A technology for axial flow compressors and stator blades, applied in mechanical equipment, machines/engines, liquid fuel engines, etc., can solve problems such as increased losses, and achieve the effects of easy engineering implementation and simple adjustment mechanism

Inactive Publication Date: 2015-09-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, as the working state of the compressor changes, the last stage stator may work at a large positive and negative angle of attack, resulting in increased losses

Method used

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  • Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof
  • Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof
  • Axial-flow compressor stator blade system with adjustable first and second half of segments and working method thereof

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Embodiment Construction

[0019] The following combination Figure 1 to Figure 5 The implementation method of the front and rear half adjustable stator blades of the present invention is illustrated. The combination of the front and rear halves of the stator blade constitutes the overall stator blade, which is designed according to the conventional design method, that is, according to the distribution of the inlet and outlet airflow angles of the stator blade along the blade height at the design point, several two-dimensional blade shapes are designed along the blade height direction, and then along the blade height Gao stacked these two-dimensional blade shapes to form three-dimensional blades. According to the three-dimensional blade shape designed above, select the outer diameter of the connecting cylinder 2 and the position of the blade (near the maximum thickness of the blade); and then divide the blade into the first half blade 1 and the second half blade 4 . When the first half of the blade 1 i...

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Abstract

The invention relates to an axial-flow compressor stator blade system with adjustable first and second half segments and a working method thereof and belongs to the field of mechanical technology of impellers. A single-stage stator blade is divided into a first half segment adjustable blade (1) and a second half segment adjustable blade (4). Sleeve ring structures (3) of the first and second half segment adjustable blades are connected via a connection cylinder (2). The connection cylinder (2) is arranged at the biggest thickness part of the last-stage stator blade and installed between an external casing and a stator inner ring. A stepping motor rotates so as to drive a worm, a worm wheel, a rotation ring, a cylindrical pulling block, and the first half or second half segment blade to rotate and move successively, thereby achieving adjustment of angles. Compared with the prior art, the stator blade system is advantageous in that 1) for a middle-stage stator blade, by rotating the first half segment blade, the blade is arranged at a favorable attack angle, and by rotating the second half segment blade, a rotator at the backward position of the stator is arranged at a favorable attack angle; and 2) an adjusting mechanism is simple and easy to realize in engineering.

Description

technical field [0001] The invention relates to an axial-flow compressor stator vane system with adjustable front and rear half sections and a working method thereof, belonging to the technical field of impeller machinery. Background technique [0002] For industrial axial flow compressors or gas turbine engine axial flow compressors, in order to expand their high-efficiency operating range, the stator blade installation angle adjustable technology can be used. For example: Linder, c.G. and Jones.B.A published an article titled "Single-stage experimental evaluation of variable geometry guide vanes and stators. Part II annular cascade investigations of candidate variable geometry designs" (NASA CR-54555, 1967). [0003] For the first-stage inlet guide vane, the installation angle can be adjusted, which will cause a large positive or negative attack angle at the blade inlet, resulting in increased losses. Grahl, k. and Tabakoff, W. published "Off-design behavior for axial flo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/38
Inventor 周正贵曹晖
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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