Aerodynamic damping calculation method for an impeller machine

A technology of aerodynamic damping and impeller machinery, which is applied in computing, instrumentation, electrical and digital data processing, etc., and can solve problems such as difficult fluid-structure coupling and inconvenient aerodynamic damping

Active Publication Date: 2019-08-23
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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  • Abstract
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Problems solved by technology

[0006] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a method for calculating the aerodynamic damping of turboma

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  • Aerodynamic damping calculation method for an impeller machine
  • Aerodynamic damping calculation method for an impeller machine
  • Aerodynamic damping calculation method for an impeller machine

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Embodiment Construction

[0045]Specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.

[0046] It should be noted here that, in order to avoid obscuring the present invention due to unnecessary details, only the device structure and / or processing steps closely related to the solution according to the present invention are shown in the drawings, and the steps related to the present invention are omitted. Invent other details that don't really matter.

[0047] In order to introduce the fluid-solid coupling method into the turbomachinery design, the embodiment of the present invention provides a turbomach...

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Abstract

The embodiment of the invention discloses an aerodynamic damping calculation method for an impeller machine, and relates to an aerodynamic stability analysis technology for the impeller machine, and the method comprises the steps: carrying out the dynamic modal analysis of an isolated blade, and obtaining the vibration mode and frequency characteristics of the blade; constructing a modal excitingforce through modal data, writing the modal exciting force into a transient structure dynamic calculation command, and performing motion coupling iterative calculation on unsteady flow field calculation and transient structure dynamic calculation through a blade to obtain a response of the blade in a flow field; solving the transient kinetic equation in the vacuum to obtain the response of the blade in the vacuum; fitting a displacement response envelope line of a monitoring point in vacuum and a flow field through the logarithmic basis function to obtain non-pneumatic damping and total damping, and further calculating and obtaining the pneumatic damping.

Description

technical field [0001] The invention relates to the technical field of aeroelastic stability analysis of a turbomachinery, in particular to a calculation method for aerodynamic damping of a turbomachinery. Background technique [0002] With the continuous improvement of turbomachinery performance, the pressure ratio of the compressor stage is getting higher and higher, but the blades tend to be lighter and thinner, which makes blade flutter a key factor in the design of turbomachinery and its reliability. Due to the difficulty and long period of flutter experiments, systematically carrying out this work requires a lot of manpower and material resources. Therefore, the development of accurate theories and methods for flutter boundary prediction is a necessary means to obtain high performance and sufficient flutter margin turbomachinery . [0003] In most turbomachinery aeroelastic stability analysis methods, the fluid domain and the solid domain are treated separately, and t...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23G06F30/17Y02T90/00
Inventor 杨晓东金亮高勇仝宗凯林晔唐奇
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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