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Impeller machine blade, modeling method thereof and impeller machine

An impeller machinery and blade technology, applied in the field of impeller machinery blades and their modeling, can solve the problems of restricting the further increase of the high-lift blade shape load, and achieve the effects of inhibiting development and controlling strength

Pending Publication Date: 2022-07-01
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The channel vortex is an important source of end zone loss, and the end zone loss limits the further increase of high lift airfoil load

Method used

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  • Impeller machine blade, modeling method thereof and impeller machine
  • Impeller machine blade, modeling method thereof and impeller machine
  • Impeller machine blade, modeling method thereof and impeller machine

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Embodiment Construction

[0039] The technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present invention.

[0040] In the description of the present invention, it should be understood that the terms "center", "horizontal", "portrait", "front", "rear", "left", "right", "top", "bottom", " The orientation or positional relationship indicated by vertical, horizontal, top, bottom, inner, outer, etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and The description is simplified rather than indicating or im...

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Abstract

The invention relates to a turbomachine blade and a modeling method thereof and a turbomachine, the turbomachine blade comprises a blade body, the blade body comprises a first blade body part (1) and a second blade body part (2), and the mounting angle of the blade-shaped section of the first blade body part (1) is suddenly increased relative to the mounting angle of the blade-shaped section of the second blade body part (2). According to the embodiment of the invention, the mounting angle of the first blade body part is increased suddenly, so that the first blade body part can form a part which is obviously protruded relative to the second blade body part, and the protruded part is beneficial to inhibiting the development of an incoming flow boundary layer so as to control the strength of a horseshoe vortex.

Description

technical field [0001] The invention relates to the technical field of impeller machinery, in particular to an impeller machinery blade and a molding method thereof, and an impeller machinery. Background technique [0002] In the current development trend of large bypass ratio aero-engines, the performance of the low-pressure turbine is a crucial part, which is of great significance to the improvement of the performance and efficiency of the whole machine. In recent years, in order to reduce the weight of low-pressure turbines, high-lift airfoils are often used to reduce the number of blades, but the increase in the aerodynamic load of the blades will lead to an increase in the secondary flow at the end zone, thereby increasing the end zone loss. [0003] The secondary flow in the end zone is an important source of turbine aerodynamic losses. The so-called secondary flow in the end zone is a low-energy fluid in the boundary layer of the end zone. Under the action of the late...

Claims

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Application Information

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IPC IPC(8): F01D5/14
CPCF01D5/145
Inventor 孟凡妍侯伟涛曾静茹
Owner AECC COMML AIRCRAFT ENGINE CO LTD