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Engine performance
Published in Mohammad H. Sadraey, Aircraft Performance, 2017
A gas turbine engine that delivers power through a shaft to operate something other than a propeller is referred to as a turboshaft engine. Turboshaft engines are very similar to turboprop engines. The turbine that extracts energy from gas flow is primarily designed to produce shaft power. The turboshaft engine has the same basic components found in a turbojet engine, with the addition of a turbine shaft to absorb the power of the hot gases of combustion.
Shaft Engines
Published in Ahmed F. El-Sayed, Aircraft Propulsion and Gas Turbine Engines, 2017
A turboshaft engine is defined as a gas turbine engine designed to produce only shaft power. Turboshaft engines are similar to turboprop engines, except that the hot gases are expanded to a lower pressure in the turbine, thus providing greater shaft power and little exhaust velocity.
Effect of bleed air on performance of small turbojet engine used in unmanned aerial vehicle
Published in Energy Sources, Part A: Recovery, Utilization, and Environmental Effects, 2023
By virtue of the working principle, gas turbine engines have been employed for different purposes such as electrical generation by generator, power production for miscellaneous pumps used on it, and thrust for propelling the aircraft. If gas turbine systems are used on the ground, these are named cogeneration systems due to producing both heat and electric energy. For air vehicle applications, these produce thrust for fixed wings or power for rotating helicopter blades. Gas turbine engines are categorized into four subsystems such as turbojet utilized unmanned aero vehicles, turbofan employed on mainly passenger aircraft, turboshaft for helicopter and turboprop used on mainly cargo aircraft. Figure 1 indicates turbojet engine with one spool, which links air compressor to turbine unit. This engine consists of air inlet, air compressor, combustion chamber, turbine and exhaust unit. It could be kept in mind that the present engine bears similar specifications with TRI 60–5 version (Forecast, 2010). Moreover, Table 1 presents engine-specific parameters for sea level and baseline. As can be seen, net thrust of STE is 4370 N whereas its air mass flow entering from air inlet is 6.63 kg/s. However, at 10 km of altitude, net thrust of STE is computed as 1420 N while air mass flow is measured 2.42 kg/s. As mentioned above, bleed air ratio taken from compressor changes between 1% and 8%. The values of other specifications could be provided from Table 1.