Gas turbine engine with morphing variable compressor vanes

Patent metadata

Field	Value
Publication number	US-11111811-B2
Application number	US-201916460060-A
Country	US
Kind code	B2
Filing date	Jul 2, 2019
Priority date	Jul 2, 2019
Publication date	Sep 7, 2021
Grant date	Sep 7, 2021

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.

First claim

The invention claimed is:

1. 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.

2. The stator vane as set forth in claim 1 , wherein at least one piezoelectric actuator is mounted on each of said suction and pressure sides, with one of said piezoelectric actuators being controlled to contract and the other being controlled to expand to change the position of said leading edge relative to said trailing edge.

3. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are mounted within pockets in said suction and pressure sides.

4. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are operable to change a position of said leading edge about a virtual hinge axis while changing the position of the trailing edge to a lesser extent.

5. The stator vane as set forth in claim 2 , wherein said piezoelectric actuators are operable to change a position of said trailing edge about a virtual hinge axis while changing the position of the leading edge to a lesser extent.

6. The stator vane as set forth in claim 2 , wherein said elastomer connection does not extend along an entire axial distance between said leading edge and said trailing edge.

7. The stator vane as set forth in claim 2 , wherein said at least one radially spaced piezoelectric actuator is orientated at a right angle relative to the radially central piezoelectric actuator.

8. The stator vane as set forth in claim 2 , wherein said at least one radially spaced piezoelectric actuator includes a pair of radially spaced piezoelectric actuators between said one of radially and inner and outer ends of said airfoil and orientated at a right angle relative to each other, and at a 45 degree angle relative to the radially central piezoelectric actuator.

9. The stator vane as set forth in claim 1 , wherein said at least one piezoelectric actuator includes at least two, and mounted within pockets in said suction and pressure sides.

10. The stator vane as set forth in claim 9 , wherein said piezoelectric actuators are operable to change a position of said leading edge about a virtual hinge axis while changing the position of the trailing edge to a lesser extent.

11. The stator vane as set forth in claim 9 , wherein said piezoelectric actuators are operable to change a position of said trailing edge about a virtual hinge axis while changing the position of the leading edge to a lesser extent.

12. 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.

13. The stator vane as set forth in claim 12 , wherein said at least one radially spaced piezoelectric actuator is orientated at a right angle relative to the radially central piezoelectric actuator.

14. The stator vane as set forth in claim 12 , wherein said at least one radially spaced piezoelectric actuator includes a pair of radially spaced piezoelectric actuators between said one of radially and inner and outer ends of said airfoil and orientated at a right angle relative to each other, and at a 45 degree angle relative to the radially central piezoelectric actuator.

15. The stator vane as set forth in claim 12 , wherein said airfoils are formed of a metal.

16. 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.

17. The gas turbine engine as set forth in claim 16 , 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.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Joly Michael M
• Chaudhry Zaffir A
• Evans Simon W
• Medic Gorazd
• Prasad Dilip

Classifications

• F05D2260/407

  through piezoelectric conversion · CPC title

• F01D17/24

  electrical · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title