# US 11,111,811 B2 · Gas turbine engine with morphing variable compressor vanes > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,111,811 B2 - Document ID: US11111811B2 - Status: Granted - Kind: B2 - Application number: 16/460,060 - Filed: 2019-07-02 - Published: 2021-01-07 - Granted: 2021-09-07 - Earliest claimed: 2019-07-02 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Michael M. Joly; Zaffir A. Chaudhry; Simon W. Evans; Gorazd Medic; Dilip Prasad - Web page: https://patentgrep.com/patent/US11111811B2 ## CPC - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - F01D 17/162: {for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 17/24: electrical - F01D 25/02: De-icing means for engines having icing phenomena - F02C 9/22: by adjusting turbine vanes - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2260/407: through piezoelectric conversion - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 2) The stator vane as set forth in claim 2, wherein said piezoelectric actuators are mounted within pockets in said suction and pressure sides. ### Claim 4 (depends on 2) 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. ### Claim 5 (depends on 2) 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. ### Claim 6 (depends on 2) 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. ### Claim 7 (depends on 2) 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. ### Claim 8 (depends on 2) 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. ### Claim 9 (depends on 1) 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. ### Claim 10 (depends on 9) 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. ### Claim 11 (depends on 9) 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. ### Claim 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. ### Claim 13 (depends on 12) 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. ### Claim 14 (depends on 12) 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. ### Claim 15 (depends on 12) The stator vane as set forth in claim 12, wherein said airfoils are formed of a metal. ### Claim 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. ### Claim 17 (depends on 16) 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.