By Gordon C. Oates
Layout and R&D engineers and scholars will price the excellent, meticulous insurance during this quantity. starting with the elemental ideas and ideas of aeropropulsion combustion, chapters discover particular approaches, barriers, and analytical tools as they endure on part layout.
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Extra info for Aerothermodynamics of Aircraft Engine Components (Pandora Books)
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.
Vapor is removed from this region by diffusion and forced convection; and the heat required to produce the evaporation is transferred to the surface by conduction from within the drop and by conduction and forced convection from the gas stream. The drop radius and the temperature distribution within the drop will be functions of time. Transport of vapor and heat occur by diffusion and forced convection, both of which may be either laminar or turbulent. The simplest situation to analyze for this complex problem is the case in which molecular transport processes for mass and heat are dominant and for which the temperature changes within the drop can be ignored.
This parameter is defined as the time lag for a given fuel-air mixture to achieve significant reaction. Zero time may be defined as the incidence of initial mixing (as in a flow reactor) or of near-instantaneous heating (as in a shock tube). 5 Spontaneous Ignition Temperatures (from Ref. 20) Fuel SIT (K) Fuel SIT (K) Propane Butane Pentane Hexane Heptane Octane Nonane 767 678 558 534 496 491 479 Decane Hexadecane Isooctane Kerosene (JP-8 or Jet A) JP-3 JP-4 JP-5 481 478 691 501 511 515 506 FUNDAMENTALS OF COMBUSTION 35 100 P=IO atm.
Aerothermodynamics of Aircraft Engine Components (Pandora Books) by Gordon C. Oates