Abstract: An outlet guide vane for a turbofan engine, which results in reduced noise. The outlet guide vane may comprise an aerofoil, the aerofoil comprising at least porous section, wherein the at least one channel or porous section is positioned near the leading edge of the aerofoil.

Abstract: An aerofoil component (10) defining an in use leading edge (16) and a trailing edge (18), the leading edge (16) comprising at least one serration (22) defining a sawtooth profile projecting in a generally upstream direction, each serration (22) comprising a plurality of rectangular-wave projections (26) extending in an upstream chordwise direction from the sawtooth profile.

Abstract: An aerofoil has a leading edge, a trailing edge, a suction surface and a pressure surface. The leading edge includes apertures extending through the aerofoil from the suction surface to the pressure surface. The apertures define a first row spaced a distance (L1) of between 2 and 6 cm from the leading edge in a chordal direction (C).

Abstract: An outlet guide vane for a turbofan engine, which results in reduced noise. The outlet guide vane may comprise an aerofoil, the aerofoil comprising at least porous section, wherein the at least one channel or porous section is positioned near the leading edge of the aerofoil.

Abstract: An aerofoil having a leading edge and a trailing edge, the leading edge including a plurality of slits extending toward the trailing edge, such that the leading edge is defined by alternating peaks and troughs. Each peak extends in a generally spanwise direction and defines a peak width, each peak being separated from an adjacent peak in the spanwise direction by a trough. Each trough extends in the generally spanwise direction and is spaced in a chordwise direction from the peak, each trough defining a trough width. A ratio of the peak width to the trough width is between 4:1 and 10:1.

Abstract: An aerofoil component (10) defining an in use leading edge (16) and a trailing edge (18), the leading edge (16) comprising at least one serration (22) defining a sawtooth profile projecting in a generally upstream direction, each serration (22) comprising a plurality of rectangular-wave projections (26) extending in an upstream chordwise direction from the sawtooth profile.

Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.

Abstract: An aerofoil component (32) defining an in use leading edge (38) and a trailing edge (40). At least one of the leading edge and the trailing edge (38, 40) comprises a plurality of first and second recesses (52, 56) projecting in a direction corresponding with an in use flow direction, the first and second recesses being spaced apart normal to the in use flow direction and having a different chordal extent.

Abstract: An aerofoil having a leading edge and a trailing edge, the leading edge including a plurality of slits extending toward the trailing edge, such that the leading edge is defined by alternating peaks and troughs. Each peak extends in a generally spanwise direction and defines a peak width, each peak being separated from an adjacent peak in the spanwise direction by a trough. Each trough extends in the generally spanwise direction and is spaced in a chordwise direction from the peak, each trough defining a trough width. A ratio of the peak width to the trough width is between 4:1 and 10:1.

Abstract: An aerofoil component defines an in use leading edge and a trailing edge. The leading edge has at least one serration defining an apex and a nadir. The leading edge has a generally chordwise extending slot located at the nadir of each serration.

Abstract: An aerofoil component (32) defining an in use leading edge (38) and a trailing edge (40). At least one of the leading edge and the trailing edge (38, 40) comprises a plurality of first and second recesses (52, 56) projecting in a direction corresponding with an in use flow direction, the first and second recesses being spaced apart normal to the in use flow direction and having a different chordal extent.