Numerical Investigation of the Effects of Swept Blade on the Aerodynamic Performance of A Highly Loaded Transonic Two-Stage Fan
Both conventional and swept schemes are adopted to design a highly-loaded transonic two-stage fan. The effects of swept blade on the aerodynamic performance of the fan are investigated using the three-dimensional numerical simulation method. The results indicate that: the adiabatic efficiency and the stall margin of the swept scheme are increased by 0. 63％ and 7.1％ respectively than the conventional scheme; the comer separation of the flow in the second stator passage is suppressed effectively by the swept stator; the stage matching problem that the second stage has already reached its stall condition while the first stage still has certain levels of stall margin at near design point in the conventional scheme has been improved by the swept design in the swept scheme; in this highly-loaded two-stage fan, the first stage does not start its stalling process until the second stage reaches its near stall condition and the fan starts to stall when both the first and second stages reach their stall conditi ons; the distance of the shock location from the leading edge of the forward-swept rotor is farther, and the shock moving upstream velocity due to the increasing backpressure is slower than that in the conventional rotor.
swept blade highly loaded transonic two-stage fan aerodynamic design numerical investigation
Jin Hailiang Jin Donghai Gui Xingmin
Aeroengine Numerical Simulation Research Center, Beihang University, Beijing 100191,China Aeroengine Numerical Simulation Research Center, Beihang University,Beijing 100191, China Aeroengine Numerical Simulation Research Center,Beihang University, Beijing 100191, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
987-992
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）