# US 10,502,229 B2 · 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 10,502,229 B2 - Document ID: US10502229B2 - Status: Granted - Kind: B2 - Application number: 15/114,167 - Filed: 2015-02-12 - Published: 2016-12-15 - Granted: 2019-12-10 - Earliest claimed: 2014-02-19 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Edward J. Gallagher; Lisa I. Brilliant; Joseph C. Straccia; Stanley J. Balamucki; Mark A. Stephens; Kate Hudon - Web page: https://patentgrep.com/patent/US10502229B2 ## CPC - F04D 29/384: {characterised by form} - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F04D 29/324: {Blades} - F04D 29/325: {for axial flow fans (blade mountings F04D29/34, blades F04D29/38)} - F04D 29/544: {Blade shapes} - F04D 29/563: {specially adapted for elastic fluid pumps} - F05D 2220/32: in gas turbines - F05D 2240/121: related to the leading edge of a stator vane - F05D 2240/303: related to the leading edge of a rotor blade - F05D 2240/35: Combustors or associated equipment - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - 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 of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span. ## Claims ### Claim 1 A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged upstream of the combustor section; a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a fan pressure ratio of less than 1.55, wherein the low pressure compressor is counter-rotating relative to the fan blades, wherein the low pressure compressor is downstream from the fan section; a geared architecture coupling the fan section to the turbine section or the compressor section; and an airfoil provided in a compressor outside the high pressure compressor section, wherein the airfoil is rotatable relative to an engine static structure, the airfoil including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span wherein the leading edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the leading edge. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the gas turbine engine is a two-spool configuration. ### Claim 3 (depends on 1) The gas turbine engine according to claim 1, wherein the curve has a negative slope from 0% span to 20% span. ### Claim 4 (depends on 1) The gas turbine engine according to claim 1, wherein the curve has less than a 40° leading edge angle from 20% span to 50% span. ### Claim 5 (depends on 4) The gas turbine engine according to claim 4, wherein the curve has a slope that is generally constant from 20% span to 70% span. ### Claim 6 (depends on 1) The gas turbine engine according to claim 1, wherein the airfoil has a relationship between a trailing edge angle and span position that includes another curve with a non-positive slope from 90% span to 100% span. ### Claim 7 (depends on 6) The gas turbine engine according to claim 6, wherein the other curve is linear with a trailing edge angle of less than 75° at 0% span and a trailing edge angle of less than 40° at 100% span. ### Claim 8 A gas turbine engine comprising: a combustor section arranged between a compressor section and a turbine section, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged upstream of the combustor section; a fan section having an array of twenty-six or fewer fan blades, wherein the fan section has a fan pressure ratio of less than 1.55, wherein the low pressure compressor is counter-rotating relative to the fan blades, wherein the low pressure compressor is downstream from the fan section; a geared architecture coupling the fan section to the turbine section or the compressor section; and an airfoil provided in a compressor outside the high pressure compressor section, wherein the airfoil is rotatable relative to an engine static structure, the airfoil including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a trailing edge angle and span position that includes a curve with a non-positive slope from 90% span to 100% span, wherein the trailing edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the trailing edge. ### Claim 9 (depends on 8) The gas turbine engine according to claim 8, wherein the gas turbine engine is a two-spool configuration. ### Claim 10 (depends on 8) The gas turbine engine according to claim 8, wherein the curve is linear with a trailing edge angle of less than 85° at 0% span and a trailing edge angle of less than 55° at 100% span. ### Claim 11 (depends on 10) The gas turbine engine according to claim 10, wherein the trailing edge angle is less than 75° at 0% span and a trailing edge angle is less than 40° at 100% span. ### Claim 12 (depends on 11) The gas turbine engine according to claim 11, wherein the trailing edge angle is less than 35° at 100% span. ### Claim 13 (depends on 8) The gas turbine engine according to claim 8, wherein the airfoil has a relationship between a leading edge angle and span position that includes another curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span. ### Claim 14 (depends on 13) The gas turbine engine according to claim 13, wherein the other curve has a negative slope from 0% span to 20% span. ### Claim 15 (depends on 13) The gas turbine engine according to claim 13, wherein the other curve has less than a 40° leading edge angle from 20% span to 50% span. ### Claim 16 (depends on 15) The gas turbine engine according to claim 15, wherein the other curve has a slope that is constant from 20% span to 70% span.