The purpose of this study a fast procedure for the structural analysis of gas turbine blades in aircraft engines. In this connection, investigations on the behavior of gas turbine blades concentrate on the analysis and evaluation of starting dynamics and fatigue strength. Besides, the influence of structural mistuning on the vibration characteristics of the single blade is analyzed and discussed.
A basic computation cycle is generated from a flight profile to describe the operating history of the gas turbine blade properly. Within an approximation approach for high-frequency vibrations, maximum vibration amplitudes are computed by superposition of stationary frequency responses by means of weighting functions. In addition, a two-way coupling approach determines the influence of structural mistuning on the vibration of a single blade. Fatigue strength of gas turbine blades is analyzed with a semi-analytical approach. The progressive damage analysis is based on MINER’s damage accumulation assuming a quasi-stable behavior of the structure.
The application to a gas turbine blade shows the computational capabilities of the approach presented. Structural characteristics are obtained by robust and stable computations using a detailed finite element model considering different load conditions. A high quality of results is realized while reducing the numerical costs significantly.
The method used for analyzing the starting dynamics is based on the assumption of a quasi-static state. For structures with a sufficiently high stiffness, such as the gas turbine blades in the present work, this procedure is justified. The fatigue damage approach relies on the existence of a quasi-stable cyclic stress condition, which in general occurs for isotropic materials, as is the case for gas turbine blades.
Owing to the use of efficient analysis methods, a fast evaluation of the gas turbine blade within a stochastic analysis is feasible.
The fast numerical methods and the use of the full finite element model enable performing a structural analysis of any blade structure with a high quality of results.
The support of the German Research Foundation (DFG, Deutsche Forschungsgemeinschaft) through its Collaborative Research Centre (SFB, Sonderforschungsbereich) 871 is gratefully acknowledged.
Rogge, T., Berger, R., Pohle, L., Rolfes, R. and Wallaschek, J. (2018), "Efficient structural analysis of gas turbine blades", Aircraft Engineering and Aerospace Technology, Vol. 90 No. 9, pp. 1305-1316. https://doi.org/10.1108/AEAT-05-2016-0085
Emerald Publishing Limited
Copyright © 2018, Emerald Publishing Limited