Our Publications

makale1

ENGINE DESIGN FOR A HALF SCALE MODEL OF JSF UAV WITH HIGH POWER EXTRACTION REQUIREMENTS

Unmanned aerial vehicles (UAV) are the future of air combat. These platforms have generic needs in contrast to manned air platforms. These needs should also be addressed from the engine design perspective. In this study conceptual design for a half-scale UAV (based on the dimensions of the Joint Strike Fighter) is presented. For this purpose a twin spool low by-pass ratio turbofan engine is designed. The main requirement is the high power extraction capability from the engine. This issue is addressed utilizing a novel alternator concept that relies on integrating the stator and the rotor on counter rotating spools. Furthermore on and off design point analyses and component design summaries are also presented. Outcome of the conceptual design task pushes the boundaries of the current state-of-the-art.

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makale4

QUASI THREE DIMENSIONAL FAN DESIGN FOR A TWIN-SPOOL LOW BYPASS RATIO TURBOFAN ENGINE

This paper presents the preliminary design of a three stage fan for a twin-spool low bypass ratio turbofan aeroengine. Design produre has been initialized with the specification of technical requirements obtained from the parametric cycle analysis. With this information, a suitable baseline engine is selected that has the closest technical specifications. The design process continues with the determination of the number of fan stages and other stage parameters. The next step is the designation of the blade airfoil profiles such that they have adequate stall margin in subsonic conditions. Airfoils are designed to avoid both positive and negative stall situations. Hub profiles have noticeably larger cambers due to lower linear speeds in comparison to tip profiles. By stacking up airfoil profiles in the radial direction form hub to tip a quasi three dimensional design is reached. Finally, solid models of the rotor and the stator parts were produced.

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makale1

ENGINE DESIGN FOR A HALF SCALE MODEL OF JSF UAV WITH HIGH POWER EXTRACTION REQUIREMENTS

Unmanned aerial vehicles (UAV) are the future of air combat. These platforms have generic needs in contrast to manned air platforms. These needs should also be addressed from the engine design perspective. In this study conceptual design for a half-scale UAV (based on the dimensions of the Joint Strike Fighter) is presented. For this purpose a twin spool low by-pass ratio turbofan engine is designed. The main requirement is the high power extraction capability from the engine. This issue is addressed utilizing a novel alternator concept that relies on integrating the stator and the rotor on counter rotating spools. Furthermore on and off design point analyses and component design summaries are also presented. Outcome of the conceptual design task pushes the boundaries of the current state-of-the-art.

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turbojet_model

A Model-Based Design Software for Propulsion System Design

We have developed a rapid prototype for the core layer, one that
handles computations, under MATLAB environment. This core
at the time being is able to solve the steady-state behavior of simple
pipe networks and some turbo-machinery components. We
also developed a user friendly graphical user interface (GUI) and
started porting our MATLAB code into C#. Now, we can show a
stand-alone proof-of-concept desktop application demo that can
solve pipe networks that are defined by the user via drag and
drop interactions. We also began implementing databases for
some standard components. As a next step we will start implementing
Git integration which lets teams of all sizes to collaborate
easily in a shared project.

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makale5

REVERSE ENGINEERING OF A MICRO TURBOJET ENGINE

Reverse engineering is the process of discovering the technological working principles of a device, object or system. This paper in particular, focuses on the reverse engineering of a micro turbojet engine. First, components of gas turbine geometry are scanned and transformed into digitized point cloud format utilizing a three axis scanner. Next, solid geometry of the engine parts were re-constructed in computer aided drafting environment from these data. Furthermore, performance maps of individual components are either calculated or certain assumptions were made as to their behavior. On and off design point engine performance has been determined through a parametric cycle analysis. Obtained results are in line with the reported performance parameters of the reverse engineered engine. This study demonstrates the use of reverse engineering procedures, when designing from scratch would not be as practical. This approach can cut down the overall turnover time for a new design.

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makale6

CONCEPTUAL DESIGN AND MECHANICAL CONSTRUCTION OF A 150 mm SHOCK EXPANSION TUBE TEST FACILITY

A 150 mm shock expansion tube test facility has been designed in order to investigate superspnic and hypersonic flows. The facility has the capacity to reach a stagnation enhtalpy of 7.3 MJ/kgair. It is an impulse type facility with typical test times ranging from 150 to 1000 microseconds. In order to maximize test duration sections with interchangeable lengths can be used.

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makale2

ONE DIMENSIONAL NETWORK MODEL FOR A REVERSE FLOW COMBUSTOR

In this study, a one-dimensional empirical network code was developed for the preliminary
design of a reverse flow combustor, which was intended to be used in a 1000 hp turbo-shaft helicopter engine. Network code is able to predict critical design features such as discharge coefficients at each hole set, mass flow rate distributions across the swirler, cooling devices and dilution holes, overall pressure drop across the combustor, liner wall and gas temperatures along the combustor and pollutant emissions at the exit of the combustor. By these means, many design alternatives can be scanned rapidly in early stages of design. Results are presented for a particular combustor geometry operating at idle, cruise and take-o↵ conditions based on the cycle analysis of a turbo-shaft engine design which is intended for light duty helicopter missions. Calculated flow distributions and discharge coefficients were compared with isothermal numerical simulations and reasonably good agreement was achieved for the non-reacting case. On the other hand, liner temperatures for three operating conditions obtained from the network code were examined to see whether the liner temperatures were suitable for liner material and the obtained results showed that this particular design raises doubts when viewed from the predicted high liner temperatures.

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