CORE DUCT ASSEMBLY FOR A GAS TURBINE ENGINE

摘要: The present invention relates to a core duct assembly (43) for gas turbine engine (10), the comprising: (44) with an outer wall (48) having interior surface (52) and inner (46), vane (54) extending between said walls at least one rotor blade (56) located downstream of vane, platform (56c) tip (56d). An upstream axis (102) is defined as tangential point on first portion (62) from wherein intersects spaced radially inward by distance (c) Thus, damages due shed ice are mitigated.