United Technologies Corporation

Pratt & Whitney

Bernard J Reilly

John E Wilber

Jeffrey M Palitsch

Jesse T Carmichael

Ryan H Quinn

Rimal Patel

A bladed rotor and a hub rotor for a gas turbine are provided. A bladed rotor may comprise a rotor interface comprising a radially inward surface, wherein the rotor interface comprises a constant diameter zone; and a reduced stress zone located adjacent to and aft of the constant diameter zone. A hub rotor may comprise a hub interface comprising a radially outward surface, wherein the hub interface comprises, a constant diameter zone, and a reduced stress zone located adjacent to and aft of the constant diameter zone.

Reduced stress rotor interface

A seal ring for use between an integrally bladed rotor and a hub rotor of a compressor section of a gas turbine engine includes an arm configured to be positioned between the integrally bladed rotor and the hub rotor, such that the seal ring is removably coupled to the integrally bladed rotor and the hub rotor in response to a compressive force applied to the arm by the integrally bladed rotor and the hub rotor. The seal ring also includes a first blade coupled to the arm and configured to form a seal between a first volume and a second volume.

Clamped HPC seal ring

Growing community of inventors

Coventry, CT, United States of America

Bernard J Reilly