科研之友
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摘要
Turbofan engine is very important for civil aviation. The fan as a crucial component, its internal flow mechanisms is more complex and the loss mechanisms analysis is more difficult with the demand for greener, more efficient aircraft engines. In this paper, taking Rotor67, a high-load fan rotor, as the research object. Using the physical characteristics of the fluid in the computational fluid dynamics(CFD) results, the losses are divided into five loss regions: shock loss, boundary layer loss, tip clearance leakage loss, corner separation loss and wake loss. Each region is defined by the flow physics in the CFD results combined with geometrical locations. Three operating conditions of design point, near stall point and choke point are taken into account, and the loss of each loss zone is quantified by using the entropy rate analysis theory, which provides a basis for the loss analysis of transonic fan and blade optimization.
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