Aeroelastic stability fluid-structure interaction prediction method of turbo-machine changed interblade phase angles

A technology of aeroelastic stability and turbomachinery, applied in computing, special data processing applications, instruments, etc., can solve problems such as predicting the aeroelastic stability of turbomachinery blades, and achieve the effect of reducing calculation costs

Inactive Publication Date: 2010-11-10
BEIHANG UNIV
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Problems solved by technology

The biggest difficulty is how to accurately and efficiently realize the data transmission on the fluid-structure coupling interface and take into account the inter-blade phase angle in the osci

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  • Aeroelastic stability fluid-structure interaction prediction method of turbo-machine changed interblade phase angles
  • Aeroelastic stability fluid-structure interaction prediction method of turbo-machine changed interblade phase angles
  • Aeroelastic stability fluid-structure interaction prediction method of turbo-machine changed interblade phase angles

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Embodiment Construction

[0081] The present invention will be further described in detail with reference to the accompanying drawings and embodiments. The present invention is a method for predicting fluid-solid coupling of aeroelastic stability by considering the inter-blade phase angle of a turbomachinery. The flow of the method is as follows: figure 1 shown.

[0082] Step 1: Establish a single-sector finite element model;

[0083] A single-sector finite element model of the turbomachinery is established in the finite element software MARC for a given solid model;

[0084] Step 2: Perform modal analysis with prestress on the established finite element model;

[0085] First, the finite element model established in MARC is imported into the finite element software ANSYS, the corresponding material parameters are defined, and the rotational speed and displacement constraints are given, and the prestress caused by centrifugal force is obtained through static analysis;

[0086] Then, the modal analysi...

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Abstract

The invention relates to an aeroelastic stability fluid-structure interaction prediction method of turbo-machine changed interblade phase angles, which predicts the aeroelastic stability of a turbo-machine through the modal pneumatic damping ratio of different interblade phase angles by adopting an energy method. The method adopts the modal analysis containing prestress on established single-sector finite element models, realizes the vibration displacement transfer on the fluid-structure interaction interface through a data transfer method, adopts the dynamic mesh technology for obtaining mesh files taking the interblade phase angles into consideration, is used for unsteady computation fluid mechanic analysis of Junction Box modules in CFX, further obtains the modal pneumatic damping ratio of each interblade phase angle, and is used for predicting the aeroelastic stability. The method based on the fluid-structure interaction fully utilizes the cutting edge technology of the computational structural mechanics and the computation fluid mechanics, ensures the computation precision in each sub system, and improves the computation efficiency through the division of a fixed region and a movable region. The invention has good practical value and wide application prospects in the technical field of turbo-machine simulation.

Description

(1) Technical field [0001] The invention belongs to the technical field of impeller machinery simulation, and in particular relates to an energy method-based method for predicting fluid-solid coupling of aeroelastic stability of impeller machinery taking into account the phase angle between blades. (2) Background technology [0002] The advancement of science and technology has continuously increased the blade tip tangential speed and pressure ratio of turbomachinery, which has led to the prominent aeroelastic stability of fan / compressor blades. With the development of turbomachinery towards high power and high performance, the working conditions of fan / compressor blades are getting worse and worse, the blade tip tangential speed is getting higher and higher, the rigidity of the blades is getting smaller and smaller, and the aeroelastic instability of the blades occurs more and more likely. Aeroelastic stability failures of fan / compressor blades have occurred in many engine...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 张小伟王延荣
Owner BEIHANG UNIV
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