Patent ID: 7883314
Filing Date: 2011-02-08
Classification: F01D,F02C,F02K,F04D

Abstract:
1. A tip turbine engine comprising: a rotationally fixed support structure mounted along an engine centerline; a fan hub which rotates about said engine centerline; an inducer section mounted to said fan hub, said inducer section having an axial inducer face and a radial inducer face which define an airflow passage which turns an airflow from an axial airflow direction to a radial airflow direction; a fan blade section mounted to said inducer section, said fan blade section defining a fan blade core airflow passage generally perpendicular to the axis to receive the airflow from the inducer section; a diffuser section attached to said fan blade, said diffuser section in communication with said core airflow passage to diffuse said airflow from said core airflow passage; and an annular seal assembly radially outboard of said fan blade section, said seal assembly includes a first and second radial ring which run adjacent to one another, said first radial ring rotatable with said diffuser and said second radial ring fixed to said rotationally fixed support structure.