Honeywell International Inc.

Frank A Mignano

Ardeshir Riahi

Steve Halfmann

David Chou

Kin Poon

Rajiv Rana

Bob Mitlin

A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.

Turbine blade assemblies and methods of manufacturing the same

A vortex spoiler () for delivery of a cooling airflow () in a turbine () engine () including a plurality of inlet ports () formed circumferentially about a radial exterior sidewall (), and a plurality of outlet ports () formed circumferentially about a radial interior sidewall (). The plurality of inlet ports () are coupled to the plurality of outlet ports () via a plurality of ducts (). Each of the ducts is formed having an interior diameter at the inlet port and the outlet port formed at a preselected angle normal to the surface of the each of the radial sidewalls to form a radially curved profile such that a cooling airflow () may pass radially inwardly through each of the plurality of ducts () with minimal tangential stress and minimal static pressure loss.

Vortex spoiler for delivery of cooling airflow in a turbine engine

Growing community of inventors

Glendale, AZ, United States of America

Frank A Mignano