Numerical simulations of complex large-scale flow systems must capture a variety of physical phenomena in order to predict the flow accurately. Currently, many flow solvers are specialized to simulate one part of a flow system effectively, but are either inadequate or too expensive to be applied to a generic problem. As an example, the flow through a gas turbine can be considered. In the compre...

Aircraft engines constitute a comp‌lex system, requiring adequate mon-itoring to ensure flight safety and timely maintenance. The best way to achieve this, is modeling the engine. Therefore, in this paper, a suitable mathematical model from engine controller design point of view, for a specific aero turbine engine is proposed by the aid of MATLAB/Simulink software. The model is capable of reduc...

1. Abstract Gas turbine engines for aerospace applications have evolved dramatically over the last 50 years through the constant pursuit for better specific fuel consumption, higher thrust-to-weight ratio, lower noise and emissions all while maintaining reliability and affordability. This paper addresses one facet of this inter-disciplinary optimization problem – optimal design of a turbine bla...

The ingestion of volcanic ash by jet engines is widely recognized as a potentially fatal hazard for aircraft operation. The high temperatures (1,200-2,000 °C) typical of jet engines exacerbate the impact of ash by provoking its melting and sticking to turbine parts. Estimation of this potential hazard is complicated by the fact that chemical composition, which affects the temperature at which v...

Abstract Blade vibrations in aircraft engines are a significant challenge that must be overcome during the design and development of modern turbine engines. Vibrations lead to cyclic displacements result alternating stress strain undesired environments (high temperatures, erosion, corrosion surface, etc.). Under resonance conditions, amplitudes can increase exceed their safety limits, extreme c...

Executive Summary 3 Thermal barrier coating (TBC) ceramic topcoats made from Y 2 O 3-stabilized ZrO 2 (YSZ) have been used successfully in gas-turbine engine applications for more than 30 years. YSZ derives its favorable performance from a combination of properties that include low thermal conductivity, high thermal expansion coefficient, and phase stability to relatively high temperatures. Wit...

Isogeometric analysis is a novel approach to numerical simulation that has the potential to bridge the gap between geometric design and numerical analysis. It uses the same exact geometry representation in all stages of the product development. In this paper we present recent results which demonstrate the competitiveness of the new concept in an industrial environment, more precisely, in the ch...

A control software verification framework for gas turbine engines is developed. A stability proof is presented for gain scheduled closed-loop engine system based on global linearization and linear matrix inequality (LMI) techniques. Using convex optimization tools, a single quadratic Lyapunov function is computed for multiple linearizations near equilibrium points of the closed-loop system. Wit...

This paper presents controllers based on linear and nonlinear models of an aircraft gas turbine engine. These models along with the performance indexes, ITAE, IAE and IES are used to estimate the parameters of a PID controller. The parameters and hence the quality of the controllers are very much dependent on the accuracy of the models. It is shown that the Nonlinear AutoRegressive Moving Avera...