![]() The governing compressible flow differential equation has been resolved by making use of nonuniform works and combining from the area of the singuIarity towards the entrance leading edge. In this brand-new analysis, an option numerical incorporation technique is definitely launched. ![]() This difficulty is caused by a border layer type behavior (12) causing from a singuIarity in the location of sonic flow, we.e., when the flow Mach quantity approaches oneness. It has been found, nevertheless, that the answer methods documented in the literature may become inoperative for closes with little clearance-to-length proportion, or when the seal off is appreciably distorted. This nonlinear equation has happen to be resolved numerically by numerous writers, for nozzle, diffuser, duct, seal, and equivalent programs. ![]() Determination of leakage flow and break up drive of gasoline turbine motor mainshaft seals and equivalent devices signifies a distinctive application of the quási-one-dimensional compressibIe flow formula (6), (10).
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