| 摘要 |
<p>#CMT# #/CMT# The blade has a vane (36) that extends outwards from a slanted base (38) to define an inner radial limit for an air stream passage. The vane has a concave shaped lower surface (42) and a convex shaped upper surface situated opposite to each other in the direction of the periphery. The surfaces radially extend in height from an inner base side end to a distal end (46) situated radially at outside, in the immediate neighborhood of a fan casing (16). The vane presents a front aerodynamic deflection at the end (46), from a leading edge (48) to a trailing edge (50). #CMT# : #/CMT# An independent claim is also included for a set of fan blades. #CMT#USE : #/CMT# Used in a gas turbine engine (claimed) e.g. turbo-blower or turbofan aircraft engine, that is utilized for propelling an aircraft. #CMT#ADVANTAGE : #/CMT# The presenting of front aerodynamic deflection at the distal end, from the leading edge to the trailing edge, permits to increase the flow capacity at increased or maximum speed of the fan while improving the efficiency at partial speed and margin of stability. The blade presents an improved mechanical resistance while limiting the oscillation, noise, weight and cost. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows an axial cross sectional view of the part of fans of an engine. 16 : Fan casing 36 : Vane 38 : Slanted base 42 : Lower surface 46 : Distal end 48 : Leading edge 50 : Trailing edge.</p> |
