Damped fairing assembly
AssigneePratt & Whitney Canada Corp.
InventorJason FISH
Life of this patent
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Abstract
A bypass duct of a turbofan gas turbine engine includes a first shroud extending at least partially around an axis and a second shroud extending at least partially around the axis, the second shroud being radially spaced apart from the first shroud to define a bypass passage between the first and second shrouds. The bypass duct further includes a fairing disposed in the bypass passage. The fairing includes a first outer shell and a second outer shell defining therebetween an internal passage. The first and second outer shells extend radially from the first shroud to the second shroud. A plate extends across the internal passage between the first and second outer shells. A damper is engaged with the plate between the first and second outer shells.
Claims20
A bypass duct of a turbofan gas turbine engine, the bypass duct comprising:
- a first shroud extending at least partially around an axis;
- a second shroud extending at least partially around the axis, the second shroud being radially spaced apart from the first shroud to define a bypass passage between the first and second shrouds;
- and
- a fairing disposed in the bypass passage, the fairing including:
- a first outer shell and a second outer shell defining therebetween an internal passage, the first and second outer shells extending radially from the first shroud to the second shroud;
- a plate extending across the internal passage between the first and second outer shells;
- and
- a damper engaged with the plate between the first and second outer shells.
A turbofan gas turbine engine comprising:
- a fan through which ambient air is propelled;
- a core including a compressor for pressurizing a first portion of the air propelled by the fan, a combustor in which the pressurized air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section for extracting energy from the combustion gases;
- a bypass duct defining a bypass passage at least partially surrounding the core for conveying a second portion of the air propelled by the fan, the bypass duct including:
- a first shroud extending at least partially around an axis;
- a second shroud extending at least partially around the axis, the second shroud being radially spaced apart from the first shroud to define a bypass passage between the first and second shrouds;
- and
- a fairing disposed in the bypass passage and extending between the first and second shrouds, the fairing including a first outer shell and a second outer shell with a gap defined between the first and second outer shells, the first and second outer shells extending radially between the first and second shrouds, the first and second outer shells supported by a frame, a plate disposed in the gap between the first and second outer shells, the plate engaged with a damper to dampen movement of the first and second outer shells.
A method for mitigating vibrations of a fairing disposed in a bypass duct of a gas turbine engine, the fairing including outer shells extending between radially inner and outer shrouds in the bypass duct, the method comprising:
- receiving a flow of air in the bypass duct, the flow of air interacting with the fairing;
- and
- using a damper engaged with a plate extending between the outer shells to damp a vibration of the fairing induced by the flow of air in the bypass duct interacting with the fairing.
Dependencies are inferred from the claim text.