Rolls-Royce Corporation

Philip Joseph

Chaitanya Paruchuri

Jae-Wook Kim

Mathieu Gruber

Mahdi Azarpeyvand

Suresh Palani

Narayanan Subramanian

Sergi Palleja Cabre

Chaitanya Puruchuri

An outlet guide vane includes an aerofoil body including a root, a tip, a leading edge extending between the root and the tip, a trailing edge opposite to the leading edge, a pressure surface extending between the leading edge and trailing edge, and a suction surface extending between the leading edge and trailing edge opposite to the pressure surface. The outlet guide vane further includes a flexible membrane disposed along the pressure surface and/or the suction surface of the aerofoil body, such that the flexible membrane at least partially forms an outer surface of the outlet guide vane. The aerofoil body has a first modulus of elasticity and the flexible membrane has a second modulus of elasticity, wherein the first modulus of elasticity of the aerofoil body is greater than the second modulus of elasticity of the flexible membrane by a factor of at least 2.

Outlet guide vane for a gas turbine engine and method

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

Aerofoil

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.

Aerofoil with leading edge slits

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.

An aerofoil component () defining an in use leading edge () and a trailing edge (). At least one of the leading edge and the trailing edge () comprises a plurality of first and second recesses () 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.

A blade for a rotating machine, particularly for a gas turbine engine, has a leading edge and a trailing edge joined by pressure and suction surfaces. The trailing edge has a serrated form including a first periodic variation and a second periodic variation of higher frequency and lower amplitude than the first periodic variation.

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Southampton, United Kingdom

Philip Joseph