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US 11,111,811 B2Granted
Gas turbine engine with morphing variable compressor vanes
AssigneeRaytheon Technologies Corporation
InventorsMichael M. Joly, Zaffir A. Chaudhry, Simon W. Evans, Gorazd Medic, Dilip Prasad
Life of this patent
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Abstract
A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.
Claims17
A stator vane for a gas turbine engine section comprising:
- a stator vane having an airfoil extending between a leading edge and a trailing edge, said airfoil having a suction side and a pressure side, and there being at least one piezoelectric actuator for changing a shape of at least one of said leading edge and said trailing edge;
- wherein said airfoil is connected to radially inner and outer platforms, and there is an elastomeric material between said airfoil and said radially inner and outer platforms to accommodate movement of at least one of said leading and trailing edges;
- and
- wherein said airfoils are formed of a metal.
1 more element
A stator vane for a gas turbine engine section comprising:
- a stator vane having an airfoil extending between a leading edge and a trailing edge, said airfoil having a suction side and a pressure side, and there being at least one piezoelectric actuator for changing a shape of at least one said leading edge and said trailing edge;
- wherein said airfoil is connected to radially inner and outer platforms, and there is an elastomeric material between said airfoil and said radially inner and outer platforms to accommodate movement of at least one said leading and trailing edges;
- and
- wherein said airfoil is connected to radially inner and outer platforms, and a radially central piezoelectric actuator causes a change in a position of said at least one of said leading and trailing edges, and at least one radially spaced piezoelectric actuator is positioned between one of radially inner and outer ends of said airfoil and oriented at an angle to the radially central piezoelectric actuator to cause bowing of at least one of said leading and trailing edges.
1 more element
A gas turbine engine comprising:
- at least one row of rotating blades;
- a plurality of stator vanes upstream of said at least one row of blades;
- said plurality of stator vanes each being provided with airfoils extending between a leading edge and a trailing edge, said airfoils having a suction side and a pressure side and there being at least one piezoelectric actuator for changing a shape of at least one of said leading edge and said trailing edge;
- wherein said airfoil is connected to radially inner and outer platforms, and there is an elastomeric material between said airfoil and said radially inner and outer platforms to accommodate movement of at least one of said leading and trailing edges;
- and
- wherein said airfoils are formed of a metal.
3 more elements
Dependencies are inferred from the claim text.