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By Gordon C. Oates

A accomplished insurance of the foremost actual strategies that govern fuel turbine propulsion platforms. themes contain combustion know-how, engine/airplane functionality matching, inlets and inlet/engine integration, variable convergent/divergent nozzle aerodynamics, and extra.

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0 curve in Fig. 19. These adjustments, of course, affect the thrust, which can be estimated. Variable nozzles are essential in engines with afterburning. Single-Shaft Turboprop Simplified analysis. This type of engine is represented by the sketch of Fig. 20. The design differs from the turbojet in that the engine speed can be independently set by adjusting the propeller pitch. 1 - ~-"~ :~ 1 . 1 ~-'e) Turbine Fig. 19 Turbine match point. / \ \ / / \ J Fig. 20 Turbine engine with single shaft for turboprop.

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. ) Engine efficiency at reduced power with constant speed is inferior to that obtainable along curve C-C of Fig I. 16, but this situation is seldom necessary and usually has only a small effect on most missions.

Studying a simple jet engine, which is sketched in Fig. 14, provides an understanding of the behavior of more complicated ones. A picture of a production engine, which includes an afterburner, is shown in Fig. 15. 5 a) Turbine flow rate. Fig. 13 Turbine performance maps. Continued. 5 Pressure Ratio Fig. 13 b) Turbine efficiency. (Continued) Turbine performance maps. A definite design point is needed and a representative one is noted on the compressor and turbine maps of Figs. 13. This is where these components are supposed to operate when the design value of the ETR is imposed.

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