Calculation of natural frequencies and effective elastic properties of the axial compressor rotor blade

2016 ◽  
Vol 11 (1) ◽  
pp. 81-87
Author(s):  
A.A. Filippov
Keyword(s):  
Composite Structures ◽  
Rotor Blade ◽  
Natural Frequencies ◽  
Axial Compressor ◽  
Homogenization Method ◽  
Asymptotic Homogenization ◽  
Turbine Engine ◽  
Composite Blade ◽  
Compressor Rotor ◽  
Asymptotic Homogenization Method

The results of the numerical calculations of the natural frequencies of the composite rotor blade axial compressor of aircraft gas turbine engine. Shows the way of solving of а unit cell problem arising in the application of asymptotic homogenization method to elastic deformation of regular composite structures. Components of the effective stiffness matrix of the composite blade obtained by asymptotic homogenization.

Asymptotic study of imperfect interfaces in conduction through a granular composite material

2010 ◽  
Vol 466 (2121) ◽  
pp. 2707-2725 ◽  
Author(s):  
Igor V. Andrianov ◽  
Vladimir I. Bolshakov ◽  
Vladyslav V. Danishevs’kyy ◽  
Dieter Weichert
Keyword(s):  
Composite Structures ◽  
Effective Conductivity ◽  
Perturbation Technique ◽  
Homogenization Method ◽  
Asymptotic Homogenization ◽  
Imperfect Interfaces ◽  
Spherical Inclusions ◽  
Shape Perturbation ◽  
Asymptotic Homogenization Method ◽  
Constitutive Components

Imperfect bonding between the constitutive components can greatly affect the properties of composite structures. We propose an asymptotic analysis of different types of imperfect interfaces arising in the problem of conduction through a simple cubic array of spherical inclusions. The performed study is based on the two-scale asymptotic homogenization method. The microscopic problem on the unit cell is solved using the underlying principles of the boundary-shape perturbation technique. The influence of the interface properties on the effective conductivity and on the local potential and flux fields is studied.

scholarly journals Design and Strength Analysis of Curved-Root Concept for Compressor Rotor Blade in Gas Turbine

2017 ◽  
Vol 2017 (9) ◽  
pp. 137-155
Author(s):  
Wojciech Wdowiński ◽  
Elżbieta Szymczyk ◽  
Jerzy Jachimowicz ◽  
Grzegorz Moneta
Keyword(s):  
Rotor Blade ◽  
Axial Compressor ◽  
Computational Effort ◽  
Rotor Blades ◽  
Strength Analysis ◽  
Cyclic Symmetry ◽  
Turbine Engine ◽  
Compressor Rotor ◽  
Blade Assembly ◽  
Contact Pressures

AbstractThe motivation of the article is fatigue and fretting issue of the compressor rotor blades and disks. These phenomena can be caused by high contact pressures leading to fretting occurring on contact faces in the lock (blade-disk connection, attachment of the blade to the disk). Additionally, geometrical notches and high cyclic loading can initiate cracks and lead to engine failures. The paper presents finite element static and modal analyses of the axial compressor 3rd rotor stage (disk and blades) of the K-15 turbine engine. The analyses were performed for the original trapezoidal/dovetail lock geometry and its two modifications (new lock concepts) to optimize the stress state of the disk-blade assembly. The cyclic symmetry formulation was used to reduce modelling and computational effort.

Two applications of the asymptotic homogenization method

PAMM ◽  
2021 ◽  
Vol 20 (1) ◽  
Author(s):  
Sergey Sheshenin ◽  
Nina Artamonova ◽  
Petr Klementyev
Keyword(s):  
Homogenization Method ◽  
Asymptotic Homogenization ◽  
Asymptotic Homogenization Method

Cold Blade Profile Generation Methodology for Compressor Rotor Blades Using FSI Approach

2017 ◽  
Author(s):  
Kirubakaran Purushothaman ◽  
Sankar Kumar Jeyaraman ◽  
Ajay Pratap ◽  
Kishore Prasad Deshkulkarni
Keyword(s):  
Aspect Ratio ◽  
Rotor Blade ◽  
Axial Compressor ◽  
Operating Conditions ◽  
Rotor Blades ◽  
Blade Profile ◽  
Interaction Technique ◽  
Compressor Rotor ◽  
Blade Shape ◽  
Blade Geometry

This paper describes a methodology for obtaining correct blade geometry of high aspect ratio axial compressor blades during running condition taking into account of blade untwist and bending. It discusses the detailed approach for generating cold blade geometry for axial compressor rotor blades from the design blade geometry using fluid structure interaction technique. Cold blade geometry represents the rotor blade shape at rest, which under running condition deflects and takes a new operating blade shape under centrifugal and aerodynamic loads. Aerodynamic performance of compressor primarily depends on this operating rotor blade shape. At design point it is expected to have the operating blade shape same as the intended design blade geometry and a slight mismatch will result in severe performance deterioration. Starting from design blade profile, an appropriate cold blade profile is generated by applying proper lean and pre-twist calculated using this methodology. Further improvements were carried out to arrive at the cold blade profile to match the stagger of design profile at design operating conditions with lower deflection and stress for first stage rotor blade. In rear stages, thermal effects will contribute more towards blade deflection values. But due to short blade span, deflection and untwist values will be of lower values. Hence difference between cold blade and design blade profile would be small. This methodology can especially be used for front stage compressor rotor blades for which aspect ratio is higher and deflections are large.

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