Aerodynamics of aero-engine installation

This paper describes current progress in the development of methods to assess aero-engine airframe installation effects. The aerodynamic characteristics of isolated intakes, a typical transonic transport aircraft as well as a combination of a through-flow nacelle and aircraft configuration have been evaluated. The validation task for an isolated engine nacelle is carried out with concern for the accuracy in the assessment of intake performance descriptors such as mass flow capture ratio and drag rise Mach number. The necessary mesh and modelling requirements to simulate the nacelle aerodynamics are determined. Furthermore, the validation of the numerical model for the aircraft is performed as an extension of work that has been carried out under previous drag prediction research programmes. The validation of the aircraft model has been extended to include the geometry with through flow nacelles. Finally, the assessment of the mutual impact of the through flow nacelle and aircraft aerodynamics was performed. The drag and lift coefficient breakdown has been presented in order to identify the component sources of the drag associated with the engine installation. The paper concludes with an assessment of installation drag for through-flow nacelles and the determination of aerodynamic interference between the nacelle and the aircraft

Flow structure and optical beam propagation in high-Reynolds-number gas-phase shear layers and jets

We report on the structure of the scalar index-of-refraction field generated by turbulent, gas-phase, incompressible and compressible shear layers and incompressible jets, and on associated beam-propagation aero-optical phenomena. Using simultaneous imaging of the optical-beam distortion and the turbulent-flow index-of-refraction field, wavefront-phase functions were computed for optical beams emerging from the turbulent region in these free-shear flows, in an aero-optical regime producing weak wavefront distortions. Spatial wavefront-phase behaviour is found to be dominated by the large-scale structure of these flows. A simple level-set representation of the index-of-refraction field in high-Reynolds-number, incompressible shear layers is found to provide a good representation of observed wavefront-phase behaviour, indicating that the structure of the unsteady outer boundaries of the turbulent region provides the dominant contributions

Survey of Competition Aircraft of Aero L-159 Alca

Bakalářská práce se zabývá cvičnými a lehkými víceúčelovými letouny pro pokračovací výcvik srovnatelnými s letounem Aero L-159 ALCA. Je zde vytvořen přehled několika letounů, jejich užití, technických dat, historického vývoje a vzájemné porovnání dle letových výkonů a dalších vlastností. Aero L-159 ALCA je nejnovější konstrukce cvičného letounu a víceúčelového společnosti Aero Vodochody a následník cvičného letounu L-39 Albatros.This bachelor‘s thesis deals with military training and lightweight multi-role continuation trainers which are comparable with the Aero L-159 ALCA. Here, a survey of the most important airplanes is created, of their using, technical data, historical development and mutual comparison based on their flight performances and other properties. Aero L-159 ALCA is the latest construction of training and multi-role aircraft of the company Aero Vodochody and the successor of the traning airplane L-39 Albatros.

Alternative logistic concepts and their effect within the company and the supply chain

This document presents findings from the simulation of a focused factory at Volvo Aero, Trollhättan. A series of experiments were carried out, aimed at testing a range of alternative logistic concepts. Each concept describes an approach to the control of workflow within the business, for the purpose of determining its effect within the company, and in the wider context of the supply chain

Optimization of aeroengine utilization through improved estimation of remaining useful life (RUL) of on condition (OC) parts

Gas Turbine Operators and Maintainers face the challenge of increasing the operationallife, availability, and reliability of Aero Engine during the operations amid the advancements in the technology for the speed, Power, SFC, and Comfort which led to closing in the safety margins and increasing in the failure rate of Aero Engines, and low serviceability of aero engines due to the rapid increase in demand and expansion of the aircraft fleet by the various airlines for various reasons which led to increase in downtime and lead time of serviceability of Aero Engines. This study focuses on the inherent Aero Engine deterioration caused due to various Gas Turbine Faults or Physical Problems and how Performance, Trend, and Systems Monitoring contain this deterioration and contribute to the optimization of aero engine utilization. The purpose of thispaper is to present the importance of accurate estimation of Remaining Useful Life (RUL) of On Condition (OC) Parts and how it optimizes aero engine life. The benefits associated with the introduction of a novel estimation of RUL of OC Parts are also presented. A Standardized Replacement Model (SRM), which improves the estimation of RUL of OC Parts, is proposed for optimization of Aero Engine Utilization