Patent ID: 6454535
Filing Date: 2002-09-24
Classification: F01D,F02K

Abstract:
A blisk for use in a turbine engine comprising:an annular disk having a hub surrounding a central opening, a web extending generally radially outward from the hub and a rim surrounding the web; an inner row of blades including a plurality of circumferentially spaced airfoils integrally formed with the disk, each of said airfoils of said inner row of blades extending generally radially outward from a root positioned adjacent the print of the disk to a tip opposite the root; an annular splitter integrally formed with the inner row of blades and surrounding the tips of said plurality of airfoils thereof, said splitter having an inner surface facing the tips of the plurality of airfoils of the inner row of blades and an outer surface opposite said inner surface; and an outer row of blades including a plurality of circumferentially spaced airfoils integrally formed with the splitter, each of said airfoils of said outer row of blades extending generally radially outward from a root positioned adjacent the outer surface of the splitter to a tip opposite the root, wherein there are more airfoils in said outer row of blades than in said inner row of blades and each airfoil in said outer row of blades has a midspan chord length less than about 75 percent of a midspan chord length of the airfoils in said inner row of blades.