Aerothermodynamics of aircraft engine components by Gordon C. Oates
By Gordon C. Oates
Layout and R&D engineers and scholars will worth the finished, meticulous assurance during this quantity, which, below the specialist editorial supervision of Gordon C. Oates, good points the invited paintings of fashionable experts in airplane gasoline turbine engines.
Beginning with the fundamental rules and ideas of aeropropulsion combustion, chapters discover particular strategies, boundaries, and analytical equipment as they undergo on part layout.
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Extra resources for Aerothermodynamics of aircraft engine components
Temperature 7"1, tig. 41) Because the ignition mechanism is not dependent on the final flame temperature, tig n is not strongly dependent on the mixture ratio within the flammability limits. However, a strong dependence on pressure is usually observed. Ignition delay times for typical fuels are illustrated in Fig. 19. Below the spontaneous ignition temperature, an additional heat source must be utilized to allow temperatures to locally exceed the SIT. The most c o m m o n method of achieving this is the spark discharge.
This oxygen can be burned with additional fuel in a secondary combustion chamber located downstream of the turbine where temperature constraints are relaxed. The increased total temperature produced at the nozzle by this additional heat addition results in an increased exit velocity and thrust. The advantage of using the afterburning gas turbine engine cycle is that the weight of the augmented engine is much less than the weight of a turbojet engine producing the same maximum thrust. This advantage is partially offset by the low thermal efficiency of the augmented turbojet cycle, which is characterized by values of specific fuel consumption much higher than those for the gas turbine cycle.
Thus, the heat-transfer rate and consequently the evaporation rate will increase as the pressure falls. If the simplified results presented above are combined, it is found that as the pressure in the afterburner falls, say as a result of the increase in altitude of an engine operating at a fixed Mach number, the simple injector discussed here is capable of supplying the required fuel flow to the appropriate volume of space. However, as the pressure decreases, the droplet diameter will increase.