Design method for maximum blade thickness distribution of aero-engine blades
An aero-engine and design method technology, applied in the direction of instrumentation, geometric CAD, electrical digital data processing, etc., can solve problems such as difficult to ensure the stability of blade structure, large loss of blade aerodynamic performance, and poor degree of freedom, so as to improve low-order inherent frequency, increased design freedom, and reduced aerodynamic performance loss
Pending Publication Date: 2022-04-12
AECC SHENYANG ENGINE RES INST
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Problems solved by technology
[0005] 1) Oblique line type. Under the constraints of this method, the maximum thickness distribution of the design blade is to thicken or thin the blade as a whole, and the degree of freedom is poor. In order to ensure the structural reliability of the blade, the overall design of the blade has a large Thickness, resulting in greater loss of blade aerodynamic performance;
[0006] 2) Arbitrary curve type, large degree of freedom, and large arbitrariness, it is difficult to guarantee the structural stability of the designed blade
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[0035] In order to make the technical solution of the present application and its advantages clearer, the technical solution of the present application will be further clearly and completely described in detail below in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only part of the application Examples are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the drawings, and other relevant parts can refer to the general design. In the case of no conflict, the embodiments in the application and the technologies in the embodiments Features can be combined with each other to obtain new embodiments.
[0036] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the application shall have the usual meanings und...
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The invention belongs to the technical field of aero-engine blade maximum blade thickness distribution design, and particularly relates to an aero-engine blade maximum blade thickness distribution design method which comprises the steps that the position, with the blade height being 0.618, of the blade serves as a first golden section part; the position, with the blade height being 0.854, of the blade serves as a second golden section part; the maximum thickness distribution of the blade is controlled by a spline curve between the root part of the blade and the first golden section part; the maximum thickness distribution of the blade is controlled by a spline curve between the first golden section part and the second golden section part; and the maximum thickness distribution of the blade is controlled by a spline curve between the second golden section part and the tip part of the blade.
Description
technical field [0001] The application belongs to the technical field of design of maximum blade thickness distribution of aeroengine blades, and in particular relates to a design method of maximum blade thickness distribution of aeroengine blades. Background technique [0002] Blades in aero-engines, including fan blades and compressor blades, have a three-dimensional surface composed of multiple blades with different cross-sections from the root to the tip, such as figure 1 As shown, the maximum thickness of each airfoil section is equal to the diameter of its maximum inscribed circle, which is determined by the working environment of the blade such as the Mach number, and the maximum thickness distribution from the root to the tip of the blade gradually decreases as the blade height increases. [0003] Designing the maximum thickness distribution of the blade is an important process of constructing the three-dimensional shape of the blade, which has an important impact on...
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Login to View More IPC IPC(8): G06F30/17G06F119/02
Inventor 刘杰刘太秋潘若痴杨琳孟德君张耀光
Owner AECC SHENYANG ENGINE RES INST