Download Aircraft Propulsion Systems Technology and Design (Aiaa by Gordon C. Oates PDF

By Gordon C. Oates

A entire assurance of the most important actual strategies that govern fuel turbine propulsion structures. issues comprise combustion expertise, engine/airplane functionality matching, inlets and inlet/engine integration, variable convergent/divergent nozzle aerodynamics, and extra.

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Sample text

2 0 <: 0 2 Nozzle (or 2nd Turbine) I 0. 1 2 3 4 I 5 I I 6 7 Overall Pressure Ratio Fig. 18 Pressure distribution in turbine and nozzle in series. However, a prior mission analysis should already have accounted for this. A word about variable jet nozzles is in order at this point. Opening the nozzle increases the turbine pressure ratio when the ETR is fixed. 0 pressure ratio curve in Fig. 19 indicates the trend of the new match point. The higher speed causes the compressor to develop a higher pressure ratio with a higher weight flow.

Such a procedure is now described. It ignores Reynolds number effects, but one should recognize that anything that changes the Reynolds number has the potential of producing other noticeable changes in performance. Method of approximate analysis. We shall assume an ideal gas having the properties expressed in Sec. 3. This allows the major trends to be easily revealed. To establish these trends, it is also convenient to make the reasonable assumption that the gas flow rate in the turbine just behind the combustor is about the same as that in the compressor immediately in front of it.

Experimental evidence on two-dimensional bends shows that the swept flow tends to roll up into vortices denoted by E at the corners. The retarded flow at the outlet of Fig. 36 is exaggerated to C H D Fig. 36 Two-dimensional curved duct illustration of secondary flows.

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