Pratt-whitney Canada Corp

Chao Zhang

Othmane Leghzaouni

Robert Huszar

Michael Papple

Marc Tardif

Rambod Larijani

A method of producing a centrifugal compressor impeller is provided. The impeller includes a hub with a rotational axis, and forward and aft surfaces. The aft surface extends between an outer radial surface of the impeller and a bore centered on the rotational axis. The method includes: analyzing the impeller to determine a stress field having tangential stress data values and radial stress data values as a function of radial position within the impeller hub and as a function of axial position within the impeller hub; determining biaxiality ratio (BR) data using the determined tangential stress data values and the determined radial stress data values; determining a peak von Mises creep strain location on the impeller; contouring the aft surface at the peak von Mises creep strain location using the radial stress data values and the BR data; and producing the impeller with the contoured aft surface.

Centrifugal compressor impeller and method of producing the same

A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.

Method of making a single-crystal turbine blade

The turbine blade includes an airfoil, a root connected to the airfoil and having lobed edges spaced apart on laterally opposed sides of an axis extending axially through the root, and an air passage extending through the airfoil and the root. A first tab extends at least partially along and laterally outward from a first edge of the laterally opposed lobed edges, and a second tab extending at least partially along and laterally outward from a second edge of the laterally opposed lobed edges.

Turbine blade and method

A method of reducing creep in an internally cooled turbine blade, comprising: providing a radially extending intermediate wall to continuously join a localized high stress zone of a concave side wall and a convex side wall in an intermediate cooling air channel through the blade. The intermediate wall distributes stress from the localized zone to a zone of lower stress to balance the creep inducing stress and temperature more evenly.

Growing community of inventors

Vaughan, Canada

Chao Zhang