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Training simulators are used in a variety of industries that require the skill of handling complex or sophisticated technologies and having knowledge of advanced controls. Training simulators have a long history; a number of studies have already been done to make the training simulators more flexible. Jet engine testing operators have to follow a proper methodology to carry out the procedures of safe engine testing. While performing the tests, the operators have to deal with various emergency conditions and should have proper information on how to deal with those situations. This thesis presents the design and development of a training simulator for aviation engine testing operators. Engine simulation software, GasTurb, is used to develop the jet engine model files and to get the output variables from the simulator. These model files are made accessible in Simulink (MATLAB) with the help of second order S-function. The S-function accesses the Dynamic Link Library (DLL) of GasTurb, to read the model files and to provide real time output on the basis of inputs from external hardware. The user interface to display these output values is developed in Unity game engine. Five different emergency scenarios have been designed and evaluated using the developed simulator. Related variables for these emergency scenarios are plotted to compare the reaction of the operators. The feedback is also taken from the operators regarding the effectiveness of training simulator. The result shows that training simulator would promote and develop their understanding of process. It would help to enhance the ability of operator to identify parameters causing the emergency scenarios and enable them to overcome such situations. / October 2016

The major downfalls of vegetable oils, namely soybean oil in this research, are very detrimental to engine lubricant performance. A unique - out of the box- additive package is needed to compensate for the lubricant deficiencies. This research searched for unique additive solutions to the problems of oxidation and heat stability, low temperature pumpability, and fluid corrosiveness. The additive solutions were then tested in preliminary engine tests. In this research, several formulations were developed that passed the main engine oil low temperature test, the mini rotary viscometer. The lubricants met the passing viscosity requirements of 60,000 centipoise and exhibited no yield stress. The formulation was tested using ASTM D 6594[1], hot tube corrosion bench test, and Sequence VIII corrosion engine test. Acceptable results were seen in both tests. Oxidation bench tests were used to examine soybean engine oil stability. Several antioxidants showed improved performance in the TFOUT oxidation induction time bench test. A mixture of those antioxidants was tested in the Sequence IIIG engine test. All of the formulas failed the Sequence IIIG tests. However, improved test results were seen when the soybean oil was decreased from 15 wt % to 5 wt % in the formulations.

After undergoing an extensive study about engine air mass flow measurement approaches as well as engine modelling for air mass flow prediction, a major problem found to exist is that engineers have still not found a suitable technique to accurately measure the air mass flow entering the cylinder of an internal combustion engine. The engine air mass flow is the most important parameter needed during engine development so the fuel control can be accurately calibrated and as a result increase performance and reduce emission output of an engine. The current methods used to determine the air mass flow lead to inaccuracies due to the large amount of mathematical assumptions and also sensor errors and as a result the mapping and calibration process of a new engine family takes approximately 2 years due to extensive modelling and testing required overcoming the above drawbacks. To improve this, the distributed lumped modelling technique (D-L) of the inlet manifold was chosen, where the intake system is separated into very small sections which are distributed continuously throughout the volume of the intake until entering the cylinder. This technique is validated against a CFD model of the engine’s intake system and real engine data as well as a 1D engine model.

Future commercial transport aircraft will feature more aerodynamic architectures to accommodate stringent design goals for higher fuel efficiency, reduced cruise and taxi NOx emissions, and reduced noise. Airframe designs most likely to satisfy the first goal feature architectures that lead to the formation of non-uniform flow introduced to the engine through boundary layer ingesting (BLI) inlets, creating a different operational environment from which the engines were originally designed. The goal of this study was to explore the effects such non-uniform flow would have on the behavior and performance of a transonic fan in a full scale engine test environment. This dissertation presents an experimental study of the interaction between a full scale transonic fan and a total pressure distortion representative of a boundary layer ingesting serpentine inlet. A five-hole pneumatic probe was traversed directly in front of and behind a fan rotor to fully characterize the inlet and outlet fan profile. The distortion profile was also measured at the aerodynamic interface plane (AIP) with an SAE standard total pressure rake, which has historically been accepted as the inlet profile to the fan. This provided a comparison between the present work and current practice. Accurate calculation of local fan performance metrics such as blade loading, pressure rise, and efficiency were obtained. The fan inlet measurement profile greatly enhanced the understanding of the fan interaction to the flow distortion and provided a more complete explanation of the fan behavior. Secondary flowfield formation due to the accelerated flow redistribution directly upstream of the fan created localized bulk co- and counter- rotating swirl regions that were found to be correlated with localized fan performance phenomena. It was observed that the effects of the distortion on fan performance were exaggerated if the assumed fan inlet profiles were data taken only at the AIP. The reduction in fan performance with respect to undistorted inlet conditions is also explored, providing insight into how such distortions can be compared to baseline conditions. The dissertation closes with several recommendations for improving distortion tolerant fan design in the context of experimental research and development. / Ph. D.

International Telemetering Conference Proceedings / October 26-29, 1987 / Town and Country Hotel, San Diego, California / In an Independent Research and Development (IR&D) effort, the Telemetry Systems Operation (TSO) of Computer Sciences Corporation (CSC) sought to determine the feasibility of using Artificial Intelligence (AI) techniques in a real-time processing environment. Specifically, the use of an expert system to assist in telemetry data acquisition processing was studied. A prototype expert system was implemented with the purpose of monitoring F15 Vertical Short Take Off and Landing (VSTOL) aircraft engine tests in order to predict engine stalls. This prototype expert system was implemented on a Symbolics 3670 symbolic processor using Inference Corporation's Artificial Reasoning Tool (ART) expert system compiler/generator. The Symbolics computer was connected to a Gould/SEL 32/6750 real-time processor using a Flavors, Inc. Bus Link for real-time data transfer.

Current methods of creating inlet total pressure distortion for testing in gas turbine engines are only able to simulate steady-state distortion patterns. With modern military aircraft it is becoming necessary to examine the effects of transient inlet distortion on engines. One alternative being evaluated is a splitting airfoil that is essentially a wedge that can be set at different opening angles. An array of such devices would be placed in front of the engine for testing that would be capable of creating steady-state distortion patterns as well as transient distortion patterns by changing the opening angle of the airfoils. The work here analyzes the steady-state wake characteristics of some of the splitting airfoil concepts. Single-wedge tests were conducted with various opening angles in an attempt to classify the various aspects found in the wake pattern. It was found that the wake has completely different characteristics with larger opening angles. In addition, several different combinations of wedges were also examined to see if single wedge analysis could be applied to arrays of wedges. Analysis was done on combinations of wedges aligned vertically as well as combinations that were done horizontally. It was found that single wedge characteristics change considerably when different wake patterns interact with each other / Master of Science

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Thesis (MScEng (Process Engineering))--Stellenbosch University, 2008. / This report covers the development of a biofuels engine testing facility at Stellenbosch University. The motivation for the project was three fold: a) a desire to establish biofuels and engine testing know-how; b) to test the performance characteristics of biodiesel; and c) make a facility available for future research. The two main conclusions drawn from the initial test results are: 1) the test cell is fully operational and 2) biodiesel can be substituted for mineral diesel. To the author’s knowledge this is the first biofuel specific engine testing facility in South Africa. After a literature study the test cell was realised in three phases. • Firstly, the hardware layout was designed and the necessary equipment was sourced from respectable suppliers including the judicious use of good qaulity second hand components to minimize capital cost. • The test cell was then instrumented with new sensors. Key components among these are the K-type thermocouples, barometric pressure, humidity, oil pressure and an Allen-Bradley programmable controller to serve as a data acquisition card. Two software programs were chosen, ETA for the control of the test cell and RSLogix to program the programmable logic controller (PLC). • The complete system was then integrated, debugged and validated. The design methods and procedures have been documented throughout the project along with user manuals to facilitate further research. To determine the difference in combustion parameters between biodiesel and mineral diesel an autonomous power curve test was conducted. This revealed little difference in terms of performance between the two fuels, although biodiesel had on average a marginal 0.4% decrease in power over mineral diesel. The fuel consumption for pure biodiesel was found to be higher, which is as expected as it is has a lower calorific value than mineral diesel. As a final validation, an energy balance was conducted. Here the calculated calorific value of biodiesel was compared to the results from a calorie bomb test, and the two results were found to be within 2% of each of other. / Centre for Renewable and Sustainable Energy Studies