By Gordon C. Oates
A complete assurance of the main actual strategies that govern fuel turbine propulsion platforms. subject matters comprise combustion expertise, engine/airplane functionality matching, inlets and inlet/engine integration, variable convergent/divergent nozzle aerodynamics, and extra.
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Additional info for Aircraft Propulsion Systems Technology and Design (Aiaa Education Series)
They show that the optimum energy added by the fan depends only on the flight velocity, on the efficiency of the fan itself, and on the parts of the fan installation that degregates energy. It is independent of the rest of the engine. ]FN, which reflects the aerodynamic losses due to the fan installation, as well as those in the exhaust nozzle of the fan duct. The entire fan assembly should thus be designed in close cooperation with airplane designers. The fan energy should increase as higher losses are encountered or as flight velocity becomes higher.
A match point on the turbine map is thus located and the estimate of the powers developed by the turbine, compressor, and engine are routine. Performance trends. Adjustable propeller pitch provides for good propulsion efficiency at a variety of flight speeds and engine powers. Constant engine speed is the preferred mode of operation, however, even at reduced power levels. The engine then quickly responds to demands for higher power. (If rapid increases in engine speed were necessary at lower speeds, the large polar moment of inertia of the propeller and gears would delay the response.
26. A photograph of a production version for subsonic flight is shown in Fig. 27. Recall that the fan is nothing more than a compressor producing a relatively low pressure ratio. The off-design behavior of the components of this engine is similar to the two-shaft turbojet, since the turbines and jet divide the pressure ratio in about the same way. Observe that when the ETR is lowered, the power to the jet diminishes faster than that to the fan. The discussion of turbofan engines in Sec. 3 demonstrated that there is an optimum division of these powers, which depends on flight speed and internal efficiencies.
Aircraft Propulsion Systems Technology and Design (Aiaa Education Series) by Gordon C. Oates