Abstract:
A tip turbine engine includes an axial compressor having a plurality of airfoils compressing core airflow. The airfoils include bleed air openings on their suction side surfaces. The bleed air openings prevent separation of the compressed airflow, which permits each airfoil stage to perform increased compression without separation of the airflow. As a result, the number of stages can be reduced, thereby shortening the overall length of the turbine engine.
Abstract:
A fan-turbine rotor assembly (24) includes a diffuser (114) mountable to the outer periphery of a multitude of hollow fan blade sections (72) to provide structural support to the outer tips of the fan blade sections and to turn and diffuse the airflow from the radial core airflow passage toward an axial airflow direction. The diffuser includes a fan blade tip shroud inner portion (136) which forms a planar ring about the multiple of fan blade sections. Diffuser support rings (115a, 115b) are mounted to the fan blade tip shroud to further share the radial load applied to the fan blade sections by the blade mounted diffuser and annular turbine (32).
Abstract:
A component includes a component body that is configured for use in a gas turbine engine. The component body includes first and second structural segments that are bonded to each other in at least one diffusion joint. The first and second structural segments are formed of, respectively, first and second materials. The first and second materials are different base-metal alloys, a metallic alloy and a ceramic-based material, or ceramic-based materials that differ by at least one of composition and microstructure.