Stator vane assembly for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorGeorge Pask
Life of this patent
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Abstract
A stator vane assembly for a gas turbine engine comprises a plurality of aerofoil sectioned vanes supported from a circumferentially extending support member or casing via a circumferentially extending platform or platforms. Each vane is attached at one end to one said platform which is carried from the supporting member, each platform being relatively flexible so that deflections of its respective aerofoil sectioned vane cause it to deform. The mounting between the platform and the supporting member is such as to damp motion of the platform and thus of the aerofoil sectioned vane; in some instances resilient material may be interposed between the platform and supporting member to provide the damping.
Claims7
A stator vane assembly for a gas turbine engine comprising:
- a rigid supporting member having a circumferentially extending surface thereon;
- at least one circumferentially extending flexible platform member capable of deformation and operatively carried from said supporting member, said flexible platform member having a circumferentially extending surface thereon corresponding to and spaced from the circumferentially extending surface of said supporting member;
- means resiliently mounting said platform member from said supporting member;
- and
- at least one aerofoil sectioned vane rigidly attached at one end thereof to said flexible platform member, deflections of said aerofoil sectioned vane being transferred directly to said platform member to deform the same radially and such radial deformations being damped by said means resiliently mounting the platform member from said supporting member whereby deflections of said aerofoil sectioned blade are effectively damped.
Dependencies are inferred from the claim text.