General Electric Company

Subramanya Shankar

Nagamohan Govinahalli Prabhakar

Nitesh Jain

Daniel Edward Loringer

Lukas William Johnson

Charles Stanley Orkiszewski

Andrew Theogift Jeyanth Selwyn Victor

Suresha Kumar Panambur

Michael Riehle

Steven Andrew Strang

Marc Edward Christopfel

Omar A Ramirez

Brian G Quinn

Sean M O′Melia

A system and method for inspecting fan blade clearances in a fan stator module are presented. The method includes rotating a fan rotor assembly that includes an attached bracket situated between adjacent fan blades connected to the fan rotor assembly. The bracket includes a laser module and an inclinometer configured to measure a circumferential position of the laser module. The method further includes projecting a laser beam from the laser module to the fan case to determine a distance measurement between the laser module and the fan case at multiple circumferential points around the fan case. The distance measurement and circumferential position data is processed by a computing device to determine a clearance distance between a fan blade and the fan case.

System and method for inspecting fan blade tip clearance relative to an abradable fan case

The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.

System and method for HPT disk over speed prevention

Various methods and systems are provided for an axial turbine including a containment shroud. In one example, an axial turbine for use in an engine system comprises a turbine disc/blisk and a shroud housing the turbine disc/blisk, the shroud including a first region, a second region, and a third region. A thickness of the second region is dependent on a length between the first region and the third region, and the third region has a burst strength that under a burst condition retains one or more fragments of the turbine disc/blisk.

Axial turbine with containment shroud

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Karnataka, India

Subramanya Shankar