The paper presents the examination of two different types of engine starting configurations, applicated on TV2-117A turboshaft, running into the test bench. The first type of starting configuration is a normal starting, with the engine connected to the dynamometer which controls the free turbine speed by the dynamometer load. The second type of starting is a different one, the engine is not connected with the dynamometer, therefore it results that there is no control of the free turbine speed from the dynamometer, only from the engine but in particular conditions. To achieve the starting phase an instrumentation scheme is created, to control and monitor the engine, and a starting sequence with all the parameters, confirmations and commands that are involved into the starting phase. The engine starting is performed by the test bench operating system, composed of an acquisition system and a programmable controller, wherewith is running the starting sequence.

The paper presents a detailed study of certain working regimes of a TV2-117A turboshaft engine, based on practical research using experimental data following the engine run tests. The engine run tests were made into the test bench, using a hydraulic dynamometer to vary the load on the free power turbine and to measure the main working turbine parameters, and by operating the dynamometer, different engine working regimes are obtained. To accomplish the experimental tests, the execution of an additional instrumentation of the engine was conducted and, through a digital acquisition and controller system, a series of engine parameters were measured. The detailed study of the working regimes concerned the examination of a variation of the engine main parameters and performances at various regimes, from the idle (a) to the takeoff (b), including cruise (b) and maximum continuous (c) regimes, and presented the actual values and curve variation diagrams of the measured data and the experimental results in order to create a base comparison with the regimes values from the engine manual.

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In this paperwork we are studying a turbofan engine with mixed separate flows where the primary flow it is initiated separately from the secondary flow which by it’s configuration helps improving the thrust and a reduction of the specific consumption. The thrust growth it is made by an air feed infusion, the infusion it’s made by the mix of air feed flown by the fan’s runners and compressor’s runners using air intakes with a different geometric configuration.

In this paperwork we are studying the performance of a combustion process into a jet engine combustion chamber, more specifically the relations between excess of air, overall pressure ratio and inlet turbine temperature for a combustion reaction based on a jet A fuel. The study present a method of calculating the excess of air for a generalized combustion reaction based on Jet A fuel indicated by the general formula , for different temperatures of air, different temperatures of fuel and different inlet turbine temperatures. The result of this study is to achieve diagrams in which are presented the variation of air excess with engine parameters who participate in combustion process and to performed a computing program in which it is calculated the exactly value of excess of air for any outlet compressor temperatures, any inlet turbine temperatures and different fuel temperatures.