Pratt-Whitney Canada Corp

Maxime Desgagne

Francois G Massicotte

Pierre-Luc Lachance

Gabriel Cyr-Carrier

Frederic Labrie

Frederic Deschenes

Alexandre Lupien

Robert Lavallee

Xavier Lemieux Sutton

Tooling and methods for assembling a vane ring of a turbine engine are provided. A tool includes a base configured to receive an outer ring and vanes radially inwardly of the outer ring. A heater is operable to apply heat to the outer ring when the outer ring is received on the base. Expandable jaws having a plurality of radially actuatable pads are operable to urge the vanes radially outwardly toward the outer ring. A press is operable to apply an axial force against an inner support of the vane ring to install the inner support radially inwardly of the vanes.

Tooling and method for assembling a vane ring

A seal device includes a first sidewall, a second sidewall and a carbon seal element. The first sidewall is arranged with a first tool die which centers the first sidewall about an axis. The first sidewall axially contacts the first tool die along the axis. The carbon seal element is arranged with a centering element which centers the carbon seal element about the axis. The carbon seal element circumscribes and radially contacts the centering element. The second sidewall is arranged with a second tool die which centers the second sidewall about the axis. The second sidewall axially contacts the second tool die along the axis. The first tool die and the second tool die are moved axially together along the axis to press fit the second sidewall into a bore of the first sidewall and axially capture the carbon seal element between the first sidewall and the second sidewall.

Tools and methods for assembling a seal device of a gas turbine engine

A method is provided for testing an annular seal within a gas turbine engine. During this method, a vacuum is applied to a first volume through a conduit. The annular seal is between the first volume and a second volume. A vacuum pressure is measured within the conduit while the vacuum is applied. The measured vacuum pressure is compared to a threshold vacuum pressure. A difference between the measured vacuum pressure and the threshold vacuum pressure is indicative of leakage across the annular seal from the second volume to the first volume.

Vacuum testing a seal within a gas turbine engine structure

A rotor loading system for an aircraft turbine engine has a first tool having first proximal and first distal ends. The first proximal end defines a traction interface about a first axis and a first surface radially outward of the traction interface. The first distal end defines first projections spaced circumferentially and extending to outward of the first surface. The system has a second tool with second proximal and second distal ends. The second proximal end defines a torque interface about a second axis and a second surface radially outward of the torque interface. The second distal end defines second projections spaced circumferentially and extending to outward of the second surface. One of the first and the second tool is received by the other one of the tools such that: the first and the second axis are colinear and each of the first projections is received between two second projections.

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Longueuil, Canada

Maxime Desgagne