COMPUTATIONAL AND EXPERIMENTAL INVESTIGATION OF FLOW IN COUNTER ROTATING PROPFANS INCLUDING REVERSE THRUST REGIMES

摘要

The paper presents the results of computational and experimental investigation of a ducted counter-rotating propfan (DCRP) for advanced ultra-high bypass ratio engines at take-off and cruise regimes. A valuable property of the DCRP is the possibility to adjust it by turning its blades round the radial axis in order to take optimum positions at direct thrust regime, and to reverse thrust when its blades are turned through a large angle. Reverse thrust regimes with transition “through feather” and “through null” as well as direct thrust regimes at different blade angles were investigated experimentally for the S101VV model stage the rotor of which is close to the DCRP first rotor by main parameters. 3D calculations of viscous flow in the S101VV model stage showed good convergence in comparison of numerical results with experimental ones both at direct thrust regimes and at reverse thrust with separation zones and return flows.