Aerothermodynamics of aircraft engine components by Gordon C. Oates

By Gordon C. Oates

Layout and R&D engineers and scholars will price the finished, meticulous assurance during this quantity, which, lower than the professional editorial supervision of Gordon C. Oates, good points the invited paintings of popular experts in airplane gasoline turbine engines.

Beginning with the fundamental rules and ideas of aeropropulsion combustion, chapters discover particular techniques, barriers, and analytical equipment as they endure on part layout.

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And Lefebvre, A. , "Minimum Ignition Energies in Flowing Kerosene-Air Mixtures," Combustion and Flame, Vol. 27, No. 1, Aug. 1976, pp. 1-20. 2SLewis, B. , Combustion Flames and Explosions of Gases, Academic Press, New York, 1961. , 1973. CHAPTER 2. AFTERBURNERS Edward E. Zukoski California Institute of Technology, Pasadena, California 2. 1 AFTERBURNERS Introduction The simple gas turbine cycle can be designed to have good performance characteristics at a particular operating or design point. However, a particular engine does not have the capability of producing a good performance for large ranges of thrust, an inflexibility that can lead to problems when the flight program for a particular vehicle is considered.

These results correspond to a case where n = 2, E~ = 40 k c a l / g , mole, and stoichiometric combustion of a fuel yielding T F values of 2550, 2500, and 2400 K for T, values of 1000, 800, and 600 K, respectively. 32) yields three solutions for any value of m / V P " - - o n l y the two highest T R solutions are indicated in Fig. 15, as the lowest T R solution, while stable, is not of practical interest here. The m i d - T R solution is also of academic importance as it is unstable. Considering only the highest T R solution, the analysis indicates that the adiabatic flame temperature for a complete reaction is achieved only at flow rates approaching zero.

For this example, the increase in the diffusion coefficient resulting from a reduction in the pressure is offset by a reduction in the vapor pressure (due to reduced Tp) so that the vapor diffusion and evaporation rates are held almost constant. For this case then, the evaporation time t e of Eq. 4) will not be affected directly by the pressure. In the second regime, assume that Too is almost equal to Tp. Then, when Poo is forced to drop, the small change in Tp needed to balance Eq. 6) will make an appreciable difference in the temperature difference (Too- Tp).

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