Patent ID: 8468795
Filing Date: 2013-06-25
Classification: F01D,F02C

Abstract:
1. A fan blade for a tip turbine engine comprising: a fan blade section which defines a core airflow passage therethrough, said fan blade section defined about a fan blade axis of rotation; a diffuser section mounted radially outward from said fan blade section relative said fan blade axis of rotation, said diffuser section defining a diffuser passage and a diffuser flow passage, said diffuser passage in communication with said core airflow passage to turn an airflow from said core airflow passage toward an annular combustor, said diffuser flow passage in communication with said diffuser passage to redirect a portion of said airflow from said diffuser passage; and a turbine blade which extends radially outward from said diffuser section relative said fan blade axis of rotation, said turbine blade located within a first row of a multi-row turbine to define a turbine blade passage therethrough, said turbine blade passage in communication with said diffuser flow passage to receive said portion of said airflow from said diffuser passage.