# US 2014/0154087 A1 · Gas turbine engine airfoil > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0154087 A1 - Document ID: US20140154087A1 - Status: Published application - Kind: A1 - Application number: 13/898,672 - Filed: 2013-05-21 - Published: 2014-06-05 - Earliest claimed: 2008-12-17 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Jody Kirchner; Yuan Dong; Sanjay S. Hingorani - Web page: https://patentgrep.com/patent/US20140154087A1 ## CPC - F01D 5/12: Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - F04D 29/324: {Blades} - F05D 2240/301: Cross-sectional characteristics - Y10T 29/49321: Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member - Y10T 29/49336: Blade making - Y10T 29/49337: Composite blade - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span. ## Claims ### Claim 1 A blade for a gas turbine engine, comprising: a platform; an airfoil that extends from said platform, said airfoil extending in span between a root and a tip region and in chord between a leading edge and a trailing edge; a sweep angle defined at said leading edge; a dihedral angle defined relative to said chord of said airfoil; and said sweep angle and said dihedral angle localized at said tip region and extending over a distance of said airfoil equivalent to about 10% to about 40% of said span. ### Claim 2 (depends on 1) The blade as recited in claim 1, wherein said sweep angle is a forward sweep angle that extends in an upstream direction relative to the gas turbine engine. ### Claim 3 (depends on 1) The blade as recited in claim 1, wherein said dihedral angle is a positive dihedral angle. ### Claim 4 (depends on 3) The blade as recited in claim 3, wherein said positive dihedral angle extends between a suction surface of said airfoil and a shroud assembly adjacent said tip region. ### Claim 5 (depends on 1) The blade as recited in claim 1, wherein said sweep angle is defined parallel to said chord. ### Claim 6 (depends on 1) The blade as recited in claim 1, wherein said dihedral angle is defined tangentially relative to said chord as measured from a center of gravity of said airfoil. ### Claim 7 (depends on 1) The blade as recited in claim 1, wherein said sweep angle and said dihedral angle extend from an outer edge of said tip region radially inward along a radial axis over a distance equal to about 10% to about 40% of said span. ### Claim 8 (depends on 1) The blade as recited in claim 1, wherein said sweep angle and said dihedral angle extend over a distance equal to about 20% to about 30% of said span. ### Claim 9 (depends on 1) The blade as recited in claim 1, wherein said sweep angle and said dihedral angle extend over a distance equal to about 25% to about 30% of said span. ### Claim 10 (depends on 1) The blade as recited in claim 1, wherein said sweep angle and said dihedral angle extend over a distance equal to about 35% of said span. ### Claim 11 (depends on 1) The blade as recited in claim 1, wherein said blade is a rotor blade. ### Claim 12 (depends on 1) The blade as recited in claim 1, wherein said blade is a stator blade. ### Claim 13 (depends on 1) The blade as recited in claim 1, wherein said blade is a fan blade. ### Claim 14 A gas turbine engine, comprising: a shroud assembly; a blade at least partially surrounded by said shroud assembly; said blade having an airfoil extending in span between a root and a tip region and in chord between a leading edge and a trailing edge, said airfoil including a sweep angle defined at said leading edge and a dihedral angle defined relative to said chord; and said sweep angle and said dihedral angle are localized at said tip region of said airfoil. ### Claim 15 (depends on 14) The gas turbine engine as recited in claim 14, wherein said sweep angle is a forward sweep angle that extends in an upstream direction relative to the gas turbine engine. ### Claim 16 (depends on 14) The gas turbine engine as recited in claim 14, wherein said dihedral angle is a positive dihedral angle. ### Claim 17 (depends on 14) The gas turbine engine as recited in claim 14, wherein said dihedral angle extends between a suction surface of said airfoil and said shroud assembly adjacent said tip region. ### Claim 18 (depends on 14) The gas turbine engine as recited in claim 14, wherein said sweep angle and said dihedral angle extend over a distance of said airfoil equivalent to about 10% to about 40% of said span. ### Claim 19 (depends on 14) The gas turbine engine as recited in claim 14, wherein said sweep angle and said dihedral angle extend from an outer edge of said tip region radially inward along a radial axis over a distance equal to about 10% to about 40% of said span. ### Claim 20 (depends on 14) The gas turbine engine as recited in claim 14, wherein said sweep angle and said dihedral angle extend over a distance equal to about 25% to about 30% of said span.