A method for forming a compressor corner area expansion stabilizing blade and its trailing edge groove
A compressor and trailing edge technology, used in mechanical equipment, machines/engines, liquid fuel engines, etc., can solve the problems of high processing technology, reduced blade strength reserves, difficult to adapt, etc., and achieves simple process requirements, simple structure, The effect of small structural changes
Active Publication Date: 2020-06-16
HARBIN ENG UNIV
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Problems solved by technology
The control effect of this method depends on the blade surface pressure at both ends of the gap. Generally, the two sides of the blade with a large pressure difference are selected, so it is difficult to achieve a good adaptation to the variable working conditions of the compressor.
In addition, slotted blades need to be slotted at the position of the airfoil of the compressor to achieve the jet effect, which has high requirements for jet angle, slot shape, and roughness, and requires high processing technology, and may reduce the strength reserve of the blade
Method used
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[0028] The following examples describe the present invention in more detail.
[0029] combine Figure 1a-Figure 1b , Figure 2a-Figure 2b According to the schematic diagram of the compressor corner stall structure, the position of the radial flow of the corner stall is roughly determined. According to the design parameters of the compressor cascade, including: incoming flow Mach number, diffusion factor, airflow turning angle, blade hub ratio and other parameters preliminary judgment For the form of stall in the corner area and the position of the end wall recirculation area, use numerical simulation methods to determine the range of lateral secondary flow and the intensity of end wall recirculation, and use this as a basis to determine the width and height of the groove structure of the trailing edge in the corner area of the moving blade or stationary blade. and other basic geometric dimensions. exist Figure 1a-Figure 1b and Figure 2a-Figure 2b Among them, A represents...
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The invention provides a stability improvement blade of an angle area of an air compressor and a trailing edge groove forming method of the blade. A trailing edge groove is formed in the angle area ofthe root of the blade of the air compressor, starts from the trailing edge of the blade, has the width being 10%-30% of the chord length and has the height being 0.5%-1.5% of the chord length. According to the blade and the method, the local jet effect is formed in the angle area of the root of the blade by the aid of differential pressure of the pressure surface side and the suction surface sideof the trailing edge of the blade of the air compressor, and the radial migration process of a low-energy fluid in the angle area is inhibited, so that the blade of the air compressor has the wider adaptability and the wider stable working range.
Description
technical field [0001] The invention relates to a compressor blade structure, in particular to a compressor blade structure with a groove-shaped structure in a corner area. The invention also relates to a method for forming a trailing edge groove of a compressor blade. Background technique [0002] Modern high-performance compressor blades can efficiently distribute the flow at 60% to 80% of the blade span. Therefore, the low-energy fluid near the end wall and corner area becomes the main source of flow blockage and loss, and also affects the stability of the compressor. important factor of sex. Corner zone separation is a complex three-dimensional flow separation phenomenon that widely exists in the angular zone of the compressor moving blade and stator blade. Regional flows are more complex. [0003] According to whether additional energy is added, the control methods of corner separation are mainly divided into active control and passive control. The source method sup...
Claims
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IPC IPC(8): F04D29/38
CPCF04D29/384F04D29/386F04D29/388
Inventor 姜斌赵文峰彭涛张海郑群
Owner HARBIN ENG UNIV