# US 9,752,442 B2 · Airfoil with variable profile responsive to thermal conditions > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,752,442 B2 - Document ID: US9752442B2 - Status: Granted - Kind: B2 - Application number: 15/267,186 - Filed: 2016-09-16 - Published: 2017-01-05 - Granted: 2017-09-05 - Earliest claimed: 2012-12-27 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Richard K. Hayford; Paul M. Lutjen - Web page: https://patentgrep.com/patent/US9752442B2 ## CPC - F01D 5/28: Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion - F01D 5/148: {Blades with variable camber, e.g. by ejection of fluid} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F05D 2220/32: in gas turbines - F05D 2300/10: Metals, alloys or intermetallic compounds - F05D 2300/50212: dissimilar - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An airfoil includes an airfoil body having a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions. ## Claims ### Claim 1 An airfoil comprising: an airfoil body including a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body, the second section being arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions, wherein the first section forms a pressure side of the airfoil body and a suction side of the airfoil body, and the second section is disposed on the first section and has a wedge shape that tapers toward a radially inner end of the airfoil body. ### Claim 2 (depends on 1) The airfoil as recited in claim 1, wherein the first section and the second section are different composition metallic materials. ### Claim 3 (depends on 2) The airfoil as recited in claim 2, including a compositional gradient boundary between the first section and the second section. ### Claim 4 (depends on 1) The airfoil as recited in claim 1, wherein the first section and the second section are different compositions selected from aluminum, aluminum alloys, titanium, titanium alloys, iron, iron alloys, nickel, nickel alloys, cobalt, cobalt alloys and combinations thereof. ### Claim 5 (depends on 1) The airfoil as recited in claim 1, including a distinct boundary between the first section and the second section. ### Claim 6 (depends on 1) The airfoil as recited in claim 1, wherein the first section is a core and the second section is a shell circumscribing the core. ### Claim 7 (depends on 6) The airfoil as recited in claim 6, wherein the core terminates at an intermediate span between ends of the airfoil body. ### Claim 8 (depends on 7) The airfoil as recited in claim 7, wherein the first section and the second section are different composition metallic materials. ### Claim 9 (depends on 8) The airfoil as recited in claim 8, including a compositional gradient boundary between the first section and the second section. ### Claim 10 (depends on 7) The airfoil as recited in claim 7, wherein the core tapers along a span-wise direction of the airfoil body. ### Claim 11 (depends on 1) The airfoil as recited in claim 1, wherein the second section partially covers at least one of the pressure side or the suction side. ### Claim 12 A turbomachine comprising: an airfoil including an airfoil body having a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body, the second section being arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions, wherein the first section forms a pressure side of the airfoil body and a suction side of the airfoil body, and the second section is disposed on the first section and has a wedge shape that tapers toward a radially inner end of the airfoil body. ### Claim 13 (depends on 12) The turbomachine as recited in claim 12, further including a turbine section that includes the airfoil. ### Claim 14 (depends on 13) The airfoil as recited in claim 13, further including a compressor section and a combustor in fluid communication with the compressor section, the turbine section in fluid communication with the combustor. ### Claim 15 An airfoil comprising: an airfoil body including a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body, the second section being arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions, wherein the first section is a core and the second section is a shell circumscribing the core. ### Claim 16 (depends on 15) The airfoil as recited in claim 15, wherein the core terminates at an intermediate span between ends of the airfoil body. ### Claim 17 (depends on 16) The airfoil as recited in claim 16, wherein the first section and the second section are different composition metallic materials. ### Claim 18 (depends on 17) The airfoil as recited in claim 17, including a compositional gradient boundary between the first section and the second section. ### Claim 19 (depends on 16) The airfoil as recited in claim 16, wherein the core tapers along a span-wise direction of the airfoil body.