Patent ID: 7632071

Claim:
A turbine engine component comprising: an airfoil portion; a plurality of cooling passages within the airfoil portion; said cooling passages including a first cooling passage for cooling a leading edge portion of said airfoil portion, a second cooling passage for cooling a main body portion of said airfoil portion, and a third cooling passage for cooling a trailing edge portion of said airfoil portion; said first cooling passage receiving cooling fluid from only a first inlet having a flared bellmouth inlet portion; said second cooling passage being independent of said first cooling passage and receiving said cooling fluid from only a second inlet having a flared bellmouth inlet portion; said third cooling passage being independent of said second cooling passage and receiving said cooling fluid from only a third inlet having a flared bellmouth inlet portion and said third cooling passage having a plurality of outlets for cooling a trailing edge of said airfoil portion; said second cooling passage having a serpentine tip turn and a dirt funnel located in the serpentine tip turn; a platform and said platform having a plurality of beveled edges to avoid a flowpath step-up; each said beveled edge being located where flow crosses a platform gap with an adjacent platform of an adjacent turbine component; a first one of said beveled edges being located along a first side of said platform and a second one of said beveled edges being located along a second side of said platform; said airfoil portion having a trailing edge and an undercut extending beneath a portion of said trailing edge; and said undercut being positioned beneath said platform.