Turbine blades and methods of forming modified turbine blades and turbine rotors
AssigneeHoneywell International Inc.
InventorsBob Mitlin, Mark C. Morris, Steve Halfmann, Ardeshir Riahi
Life of this patent
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Abstract
Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.
Claims14
A method of forming a modified turbine blade for use in an engine, the method comprising the steps of:
- providing an unmodified blade configuration including a platform and an airfoil extending from the platform, the platform including a surface defining a portion of a flowpath of the engine;
- subjecting the unmodified blade configuration to one or more maximum engine operating conditions, wherein the one or more maximum engine operating conditions include rotating a turbine rotor including the unmodified blade configuration thereon at a predetermined maximum speed and exposing the turbine rotor to a predetermined maximum temperature;
- performing a plastic analysis of the unmodified blade configuration, while the unmodified blade configuration is subjected to the one or more maximum engine operating conditions;
- calculating a residual plastic deformation of the platform surface, based on the plastic analysis;
- determining whether the residual plastic deformation of the platform surface is within a predetermined acceptable range;
- determining an inverse of the residual plastic deformation of the platform surface, if a determination is made that the residual plastic deformation of the platform surface is within the predetermined acceptable range;
- and
- incorporating the inverse of the residual plastic deformation of the platform surface into the unmodified blade configuration to form the modified blade configuration.
A method of forming a turbine rotor for use in an engine, the method comprising the steps of:
- providing an unmodified blade configuration including a platform and an airfoil extending from the platform, the platform including a surface defining a portion of a flowpath of the engine;
- subjecting the unmodified blade configuration to one or more maximum engine operating conditions, wherein the one or more maximum engine operating conditions include rotating a turbine rotor including the unmodified blade configuration thereon at a predetermined maximum speed and exposing the turbine rotor to a predetermined maximum temperature;
- performing a plastic analysis of the unmodified blade configuration, while the unmodified blade configuration is subjected to the one or more maximum engine operating conditions;
- calculating a residual plastic deformation of the platform surface, based on the plastic analysis;
- determining whether the residual plastic deformation of the platform surface is within a predetermined acceptable range;
- determining an inverse of the residual plastic deformation of the platform surface, if a determination is made that the residual plastic deformation of the platform surface is within the predetermined acceptable range;
- incorporating the inverse of the residual plastic deformation of the platform surface into the unmodified blade configuration to form the modified blade configuration;
- casting a turbine blade from a mold including the modified blade configuration;
- attaching the turbine blade to a hub to form the turbine rotor;
- and
- rotating the turbine rotor at the maximum engine operating conditions to impart a final contour to the turbine blade.
Dependencies are inferred from the claim text.