Pratt-Whitney Canada Corp

Anthony Mathias

Geoffrey Henriksen

Jason Wedemire

Louis Lavoie

Michael Hunze

Dennis Wilkinson

Marven Paynter

Carlo Porco

Carlo S Porco

David Nicol

Filip Ristovski

An aircraft engine repair tool for installing and/or removing a mid turbine frame from a gas turbine engine is provided. The tool includes a stabilizer configured to support a shaft via a load path different from a load path provided by the mid turbine frame rotatably supporting the shaft about a rotation axis. The tool includes a holder attachable to the mid turbine frame, and a guide movably engageable with the shaft and attachable to the holder. The guide guides movement of the holder and of the mid turbine frame relative to the shaft along the rotation axis, and prevents movement of the holder and the mid turbine frame relative to the shaft transverse to the rotation axis when the mid turbine frame is released from the support structure and attached to the holder, and when the holder is attached to the guide.

Aircraft engine repair tool and method for removal and installation of a mid turbine frame in an aircraft engine

Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

Aircraft engine repair tool and method for removal and installation of a rotor in an aircraft engine

A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

Gas turbine engine disassembly / assembly methods

A gas turbine engine yoke includes an arcuate body mountable to a stand and rotatable between an upright orientation and a horizontal orientation. The body has an inner wall spaced apart from an outer wall and first and second side walls extending between the inner and outer walls. A mounting plane of the yoke extends through the inner and outer walls and is positioned between the first and second side walls. Engine attachments are spaced apart along the inner wall and lie in the mounting plane. A method of assembling the gas turbine engine is also disclosed.

Gas turbine engine yoke and build support

Growing community of inventors

King Township, Canada

Anthony Mathias