Pratt-whitney Canada Corp

Morgan Demenois

Raghavendra Pendyala

Negin Abaeian

Tomasz Olech

Domenico Di Florio

A gas turbine engine under this disclosure could be said to include a compressor section, a combustor and a turbine section. At least one casing surrounds at least one of the compressor and turbine section. The at least one casing is formed of sheet metal, and has at least one potential peak displacement point due to vibration across a speed range of the at least one of the compressor and turbine section. A stiffening element is fixed to a wall of the casing at the at least one potential peak displacement point. A method is also disclosed.

Local stiffening for gas turbine engine casing

A gas turbine engine includes a compressor section, a combustor and a turbine section. At least one casing surrounds at least one of the compressor and turbine section. The at least one casing is formed of sheet metal. The at least one casing has at least one potential peak displacement point due to vibration across a speed range of the one of the compressor and turbine section. A damper is placed on the casing at the at least one potential peak displacement point. The damper has one end fixed to the casing, and a second end not fixed to the casing and the second end provides an interference fit such that the second end cannot move to a relaxed position of the second end due to the wall of the casing. A method is also disclosed.

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Montreal, Canada

Morgan Demenois