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

By Gordon C. Oates

A entire assurance of the foremost actual techniques that govern fuel turbine propulsion platforms. themes contain combustion expertise, engine/airplane functionality matching, inlets and inlet/engine integration, variable convergent/divergent nozzle aerodynamics, and extra.

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Extra resources for Aircraft Propulsion Systems Technology and Design (Aiaa Education Series)

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The other components have not been mentioned in this section, but we should be aware from the other chapters of these volumes that they too have problems. The engine inlet needs the careful attention described in Chapter 4, particularly if supersonic flight is included in the mission. Transient flows at the inlet is given special attention in Chapter 6. Many of the points made in these chapters may be profitably used in the design of compressors and fans. Similarly, the discussion of nozzle aerodynamics in Chapter 5 has many features that are applicable to turbines.

It is the losses causing the component efficiencies to be less than unity that are the subject of the rest of this section, which first examines the requirements for a consistent definition of losses and then discusses their sources. to/T3) Losses in Engine Performance Chapter 3 of Ref. 2 presents an excellent discussion about keeping track of losses. The authors use increases in entropy as the natural quantity for evaluating various losses of available energy in turbines. This idea is equally true for the other components and for engines.

The result is influenced by the characteristics of the compressors and turbines and their arrangement in an engine. Any change in specific power causes the operating point of each component to move. The principal variable causing this change is the ratio of turbine inlet to compressor inlet temperature, which we shall call the engine temperature ratio or ETR. Flight altitude, fuel flow, and flight Mach number are the determinants of this ratio. Note, however, that power and thrust are directly proportional to the inlet pressure unless low pressures reduce the Reynolds number beyond the point where component performance deteriorates.

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