Turbine blade including balanced mateface condition
AssigneeUnited Technologies Corporation
InventorsEvan P. Molony, Carey Clum, Wolfgang Balzer
Life of this patent
Estimating the term…
Abstract
A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.
Claims16
A blade for a gas powered turbine comprising:
- a platform having a leading edge and a trailing edge, the leading edge being connected to the trailing edge by a suction side mateface and by a pressure side mateface;
- a blade extending outward from said platform, the blade having an airfoil shaped cross section, wherein a suction side of the blade faces the suction side mateface, and a pressure side of the blade faces the pressure side mateface;
- and
- a radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position, and wherein a difference between the radial height of the suction side mateface and the radial height of the pressure side mateface at the first axial position is an ideal disparity for a balanced manufacturing range at the first axial position.
A gaspath component for a gas powered turbine comprising:
- a platform having a leading edge and a trailing edge, the leading edge being connected to the trailing edge by a first side mateface and by a second side mateface circumferentially opposite the first side mateface;
- and
- a radial height of the first side mateface is different from a radial height of the second side mateface at a first axial position, wherein a difference between the radial height of the first side mateface and the radial height of the second side mateface at the first axial position is an ideal disparity for a balanced manufacturing range at the first axial position, and the ideal balanced manufacturing range is a radial height difference configured to balance negative waterfall effects and negative damming effects that arise due to manufacturing variability.
A gas powered turbine comprising:
- a compressor section;
- a combustor section fluidly connected to the compressor section;
- a turbine section fluidly connected to the combustor section;
- at least one of said compressor section and said turbine section including a rotor stage comprised of a plurality of rotor blades, wherein each of said rotor blades includes a blade extending outward from a platform, the blade having an airfoil shaped cross section, wherein a suction side of the blade faces a suction side mateface of the platform, and a pressure side of the blade faces a pressure side mateface of the platform and a radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position, such that a radial height disparity exists across a mateface gap at any given axial position wherein the radial height disparity is an ideal disparity for a balanced manufacturing range at a first axial position.
Dependencies are inferred from the claim text.