Tip cooled blade
Passive clearance system for turbine blades
Film cooled blade tip
Turbine blade having angled squealer tip
Compound tip notched blade Patent #: 6790005
ApplicationNo. 11162433 filed on 09/09/2005
US Classes:416/92, Discharge solely at periphery normal to rotation axis416/228, Tined or irregular periphery415/173.1, Between blade edge and static part416/97RFlow exhausted to working fluid
ExaminersPrimary: Edgar, Richard A.
Attorney, Agent or Firm
International ClassF01D 5/20
AbstractAn airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.