Patent ID: 11939877
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  G | IPC F

Claim 0:
1. An integrally bladed rotor for a gas turbine engine, the integrally bladed rotor configured for use in blade off testing, comprising:
a hub having a forward end, an aft end, a circumferentially extending exterior surface disposed between the forward end and the aft end;
a plurality of rotor blades integrally attached to the hub and circumferentially spaced around the hub, the plurality of rotor blades including a test blade, each rotor blade of the plurality of rotor blades extending radially out from the hub exterior surface, and each rotor blade of the plurality of rotor blades having a leading edge disposed proximate the forward end of the hub, and each rotor blade of the plurality of rotor blades having a trailing edge disposed proximate the aft end of the hub;
a central passage disposed in the hub radially below the test rotor blade, the central passage extending along a continuous path between a passage inlet at or forward of the leading edge of the test blade and a passage outlet at or aft of the trailing edge of the test blade;
a first lateral cavity disposed in the hub extending generally parallel to the central passage path, the first lateral cavity disposed on a first circumferential side of the test blade and disposed a first minimal separation distance (MSD1) from the central passage; and
a second lateral cavity disposed in the hub extending generally parallel to the central passage path, the second lateral cavity disposed on a second circumferential side of the test blade that is opposite the first circumferential side, and disposed a second minimal separation distance (MSD2) from the central passage.