Nozzle guide vane assembly for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorsWilfred H. Wilkinson, Harry Henshaw
Life of this patent
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AssigneeROLLS-ROYCE plc
InventorsWilfred H. Wilkinson, Harry Henshaw
Estimating the term…
A nozzle guide vane assembly for a gas turbine engine comprises a circumferentially extending array of angularly spaced apart aerofoils each having projections adapted to engage with structure to retain the aerofoil in its longitudinal direction. Inner and outer platform members are separate from the aerofoils and each comprises a thicker support skin and a thinner inner skin. Both skins have aerofoil shaped apertures through which the aerofoils project, the support skin retaining the aerofoil against twisting, circumferential or axial loads and the inner skin serving to define a respective boundary of the gas flow through the assembly. The aerofoil is free to slide through the apertures sufficiently to permit relative expansion in a direction longitudinal of the aerofoil, and sealing means are associated with the inner skins and provide a seal between the skins and the aerofoils.
A nozzle guide vane assembly for a gas turbine engine comprising a circumferentially extending array of angularly spaced apart aerofoils, retaining structure for the aerofoils and projections from each aerofoil adapted to engage with the retaining structure to retain the aerofoils in their longitudinal direction, inner and outer platform members separate from the aerofoils and each comprising two skins, a thicker support skin having at least one aerofoil section aperture therein through which one said aerofoil projects and which retains the aerofoil against twisting, circumferential or axial loads and a thinner inner gas contacting skin which also has at least one aerofoil section aperture therein through which the aerofoil projects, said thinner inner gas contacting skin serving to define the respective boundary of the gas flow through the assembly, the aerofoil being free to slide through the apertures sufficiently to permit relative expansions in a direction longitudinal of the aerofoil, and sealing means associated with each said inner skin adapted to form a seal between said inner skin and said aerofoils.
Dependencies are inferred from the claim text.