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US 12,637,949 B2Granted
Airfoil-mounted acoustic resonator array for gas turbine engine component
AssigneeRtx Corporation
InventorsRamons A. Reba, Benjamin G. Gardell, Michael Raymond LaFavor
Life of this patent
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Abstract
A gas turbine engine component includes an airfoil extending between a leading edge and a trailing edge. The airfoil has hollow cells with walls separating the plurality of hollow cells. A perforated surface has a plurality of perforations and closes off the hollow cells. The hollow cells have a diverter plate which extends away from the face surface at a first angle for a first portion. A gas turbine engine and a method are also disclosed.
Claims20
A gas turbine engine component comprising:
- an airfoil extending between a leading edge and a trailing edge, the airfoil having a plurality of hollow cells with walls separating the plurality of hollow cells, a perforated surface having a plurality of perforations and closing off the hollow cells;
- and wherein
- the hollow cells have a diverter plate which is attached and directly extends away from the perforated surface at an angle;
- wherein a ramp ends before a separating wall to provide an opening further into a corresponding hollow cell;
- and
- wherein said hollow cells are defined between four of said walls, with said diverter plate extending to connect to all four of said walls, and said ramp connecting to two of said walls.
3 more elements
A gas turbine engine comprising:
- a fan section for delivering air into a bypass duct and for delivering air into a compressor section, a combustor and a turbine section;
- said fan section including a fan rotor, and fan exit guide vanes positioned downstream of the fan rotor;
- the fan exit guide vanes having an airfoil extending between a leading edge and a trailing edge, the airfoil having a plurality of hollow cells with walls separating the plurality of hollow cells, a perforated surface having a plurality of perforations and closing off the hollow cells, the hollow cells having a diverter plate which is attached and directly extends away from the perforated surface at an angle;
- and
- wherein said hollow cells are defined between four of said walls, with said diverter plate extending to connect to all four of said walls.
2 more elements
A gas turbine engine component comprising:
- an airfoil extending between a leading edge and a trailing edge, the airfoil having a plurality of hollow cells with walls separating the plurality of hollow cells, a perforated surface having a plurality of perforations and closing off the hollow cells;
- and wherein
- the hollow cells have a diverter plate which is attached and directly extends away from the perforated surface at an angle;
- and
- wherein said hollow cells are defined between four of said walls, with said diverter plate extending to connect to all four of said walls, and a ramp connecting to two of said walls.
2 more elements
Dependencies are inferred from the claim text.