By Gordon C. Oates
Layout and R&D engineers and scholars will worth the finished, meticulous assurance during this quantity, which, less than the specialist editorial supervision of Gordon C. Oates, positive factors the invited paintings of favorite experts in plane gasoline turbine engines.
Beginning with the elemental rules and ideas of aeropropulsion combustion, chapters discover particular techniques, barriers, and analytical equipment as they undergo on part layout.
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Extra info for Aerothermodynamics of aircraft engine components
55-90. 3Howard, J. , Williams, G. , and Fine, D. , 1973, pp. 975-986. 4 Mosier, S. A. , "Low Power Turbopropulsion Combustor Exhaust Emissions," AFAPL-TR-73-36, Vols. 1-3, 1974. SFremont, H. , Powell, H. , and Siecia, S. , Properties of Combustion Gases, Vols. , Cincinnati, 1955. 6Gordon, S. and McBride, B. , "Computer Program for Calculation of Complex Chemical Equilibrium Compositions, Rocket Performance, Incident and Reflected Shocks, and Chapman Jouguet Detonations," NASA SP 273, 1971. 7Zabetakis, M.
Thus, if the engine is sized for takeoff and has its design point at this condition, the engine will be too large at cruise. The vehicle performance will be penalized at cruise for the poor off-design point operation of the engine components and for the larger weight of the engine. Similar problems arise when supersonic cruise vehicles are considered. The afterburning gas turbine cycle was an early attempt to avoid some of these problems. Afterburners or augmentation devices were first added to aircraft gas turbine engines to increase their thrust during takeoff or brief periods of acceleration and supersonic flight.
The force applied to the surface of the stream tube in the direction of the flow (see Fig. 4) will be proportional to the dynamic pressure of the gas poov2/2 and some cross-sectional area, say ~ x h (where is an average width and h the penetration distance). This force must be balanced by the momentum flux of the injectant stream with mass flux rhj. // ~ ~ [ / . ,.. y // ///0) Fig. '. I // // /// dj [ v j, - // /////// pj Estimate of penetration distance. 1) The actual penetration distance is obtained by assuming w ~ dj and rhj oc (~rdf/4)pjvg; it is given by 1 --0C aj Note that the denominator of Eq.
Aerothermodynamics of aircraft engine components by Gordon C. Oates