By Gordon C. Oates
Layout and R&D engineers and scholars will worth the accomplished, meticulous assurance during this quantity, which, lower than the specialist editorial supervision of Gordon C. Oates, positive aspects the invited paintings of widespread experts in airplane gasoline turbine engines.
Beginning with the fundamental rules and ideas of aeropropulsion combustion, chapters discover particular techniques, barriers, and analytical tools as they undergo on part layout.
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Additional info for Aerothermodynamics of aircraft engine components
Nozzles with variable-area throats are necessary to accommodate the large total temperature changes produced by afterburning. These elements of the afterburner are illustrated in Fig. 1 for the turbojet cycle and in Fig. 2 for the turbofan cycle. The turbojet engine is a sketch of the General Electric J79 engine and the turbofan engine is a sketch of the Pratt & Whitney F100 engine. In the latter case, afterburning is accomplished without mixing core and fan streams and the inner contour of the nozzle is shown in closed (11) and open (12) positions.
2Rao, K. V. L. and Lefebvre, A. , "Evaporation Characteristics of Kerosene Sprays Injected into a Flowing Air Stream," Combustion and Flame, Vol. 26, No. 3, June 1976, pp. 303-310. X3Lefebvre, A. H. , "The Influence of Turbulence on the Structure and Propagation of Enclosed Flames," Combustion and Flame, Vol. 10, pp. 355-366. , Zeitschrift fuer Elektrochemie, Vol. 46, 1949, p. 601. 15Shchelkin, K. , Soviet Physics--Technical Physics, Vol. 13, Nos. 9-10, 1943. , Denniston, D. , and Wells, F. , Journal of Chemical Physics, Vol.
A final aspect of turbulence to be discussed here involves its effect on chemical reactions. During fuel-air mixing as well as in the reaction zone, the individual turbulent eddies can have widely differing values of fuel-air ratio and temperature. Because reaction rates are very sensitive to these variables [see Eq. 4)], the turbulence characteristics can strongly influence the rates and end products of the combustion process. 31) where the bars indicate average_values. 3 shows the (Ea/RT) -2 for different values of E a and T.
Aerothermodynamics of aircraft engine components by Gordon C. Oates