# US 10,119,404 B2 · Gas turbine engines with improved leading edge airfoil cooling > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,119,404 B2 - Document ID: US10119404B2 - Status: Granted - Kind: B2 - Application number: 14/515,131 - Filed: 2014-10-15 - Published: 2016-04-21 - Granted: 2018-11-06 - Earliest claimed: 2014-10-15 - Assignees: Honeywell International Inc. - Applicants: Honeywell International Inc. - Inventors: Balamurugan Srinivasan; Sridharan Reghupathy Narayanan; Karthikeyan Paramanandam; Chandiran Jayamurugan; Malak Fouad Malak - Web page: https://patentgrep.com/patent/US10119404B2 ## CPC - F01D 5/187: {Convection cooling} - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - F01D 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02C 7/04: Air intakes for gas-turbine plants or jet-propulsion plants - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2240/303: related to the leading edge of a rotor blade - F05D 2240/35: Combustors or associated equipment - F05D 2260/201: by impingement of a fluid - F05D 2260/2214: by increasing the heat transfer surface - 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 for a gas turbine engine includes a body with a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface. The airfoil further includes an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage. The internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge. The airfoil further includes a first plurality of grooves formed in the first interior surface, each the first plurality of grooves extending in a chordwise direction within the leading edge passage. ## Claims ### Claim 1 An airfoil for a gas turbine engine, comprising: a body comprising a first side wall and a second side wall joined at a leading edge and a trailing edge, the first side wall having a first interior surface and the second side wall having a second interior surface; an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage, wherein the internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge; and a first plurality of grooves formed into the first interior surface by removing portions of the first interior surface such that the first side wall has a reduced thickness within respective grooves of the first plurality of grooves relative to areas in between the respective grooves and areas along and adjacent to the leading edge, each of the first plurality of grooves extending in a chordwise direction within the leading edge passage, wherein each of the first plurality of grooves is formed by a continuously concave curved side wall in cross-section along a radial direction; and a second plurality of grooves formed in the second interior surface by removing portions of the second interior surface, each of the second plurality of grooves extending in the chordwise direction within the leading edge chamber. ### Claim 2 (depends on 1) The airfoil of claim 1, wherein the first plurality of grooves and the second plurality of grooves are aligned in the chordwise direction such that each of the first plurality of grooves shares the same radial position with a corresponding groove from the second plurality of grooves. ### Claim 3 (depends on 1) The airfoil of claim 1, wherein the first plurality of grooves and the second plurality of grooves are radially offset relative to one another. ### Claim 4 (depends on 1) The airfoil of claim 1, each of the plurality of cooling holes is associated with one of the first plurality of grooves and one of the second plurality of grooves. ### Claim 5 (depends on 1) The airfoil of claim 1, wherein each of the first plurality of grooves and each of the second plurality of grooves have approximately the same length. ### Claim 6 (depends on 1) The airfoil of claim 1, wherein each of the first plurality of grooves and each of the second plurality of grooves are parallel to one another. ### Claim 7 (depends on 1) The airfoil of claim 1, wherein the first plurality of grooves and the second plurality of grooves are non-parallel to one another. ### Claim 8 (depends on 1) The airfoil of claim 1, wherein the first interior surface is generally flat between adjacent grooves of the first plurality of grooves. ### Claim 9 (depends on 1) The airfoil of claim 1, wherein a width of each of the first plurality of grooves decreases in the chordwise direction toward the leading edge and terminates with a closed groove end. ### Claim 10 (depends on 1) The airfoil of claim 1, wherein each of the first plurality of grooves has a width and a depth, the width being at least three times the depth. ### Claim 11 (depends on 10) The airfoil of claim 10, wherein the width is approximately six times the depth. ### Claim 12 A gas turbine engine, comprising: a compressor section configured to receive and compress air; a combustion section coupled to the compressor section and configured to receive the compressed air, mix the compressed air with fuel, and ignite the compressed air and fuel mixture to produce combustion gases; and a turbine section coupled to the combustion section and configured to receive the combustion gases, the turbine section defining a combustion gas path and comprising a turbine rotor positioned within the combustion gas path, the turbine rotor comprising a platform at least partially defining the combustion gas path; and an airfoil extending from the platform, the airfoil including a body comprising a first side wall and a second side wall joined at a leading edge and a trailing edge, the leading edge having an apex, and the first side wall having a first interior surface and the second side wall having a second interior surface; an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage, wherein the internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge; a first plurality of grooves formed into the first interior surface such that the first side wall has a reduced thickness within respective grooves of the first plurality of grooves relative to areas in between the respective grooves, each of the first plurality of grooves extending in a chordwise direction within the leading edge passage from the internal wall and terminate at a first position upstream of the apex along the chordwise direction; and a second plurality of grooves formed into the second interior surface, each of the second plurality of grooves extending in the chordwise direction within the leading edge chamber from the internal wall and terminate at a second position upstream of the apex along the chordwise direction, wherein each of the first plurality of grooves has a width and a depth, and wherein the width of each of the first plurality of grooves decreases in the chordwise direction toward the leading edge, and wherein the first plurality of grooves and the second plurality of grooves are aligned in the chordwise direction such that each of the first plurality of grooves shares the same radial position with, and extends parallel to, a corresponding groove from the second plurality of grooves. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, each of the plurality of cooling holes is associated with one of the first plurality of grooves and one of the second plurality of grooves. ### Claim 14 (depends on 12) The gas turbine engine of claim 12, wherein each of the first plurality of grooves and each of the second plurality of grooves have approximately the same length. ### Claim 15 (depends on 12) The gas turbine engine of claim 12, wherein, for each of the first plurality of grooves, the width is at least three times the depth. ### Claim 16 (depends on 12) The gas turbine engine of claim 12, wherein each of the first plurality of grooves and the second plurality of grooves is formed by a continuously concave curved side wall in cross-section along the radial direction. ### Claim 17 A gas turbine engine, comprising: a compressor section configured to receive and compress air; a combustion section coupled to the compressor section and configured to receive the compressed air, mix the compressed air with fuel, and ignite the compressed air and fuel mixture to produce combustion gases; and a turbine section coupled to the combustion section and configured to receive the combustion gases, the turbine section defining a combustion gas path and comprising a turbine rotor positioned within the combustion gas path, the turbine rotor comprising a platform at least partially defining the combustion gas path; and an airfoil extending from the platform, the airfoil including a body comprising a first side wall and a second side wall joined at a leading edge and a trailing edge, the leading edge having an apex, and the first side wall having a first interior surface and the second side wall having a second interior surface; an internal wall disposed within of the body and extending between the first interior surface and the second interior surface to define a supply passage and a leading edge passage, wherein the internal wall defines a plurality of cooling holes to direct cooling air from the supply passage to the leading edge passage such that the cooling air impinges upon the leading edge; a first plurality of grooves formed into the first interior surface, each of the first plurality of grooves extending in a chordwise direction within the leading edge passage from the internal wall and terminate at a first position upstream of the apex along the chordwise direction; and a second plurality of grooves formed into the second interior surface, each of the second plurality of grooves extending in the chordwise direction within the leading edge chamber from the internal wall and terminate at a second position upstream of the apex along the chordwise direction, wherein each of the first plurality of grooves has a width and a depth, and wherein the width of each of the first plurality of grooves decreases in the chordwise direction toward the leading edge, wherein each of the first plurality of grooves and the second plurality of grooves terminates with a closed groove end. ### Claim 18 (depends on 17) The gas turbine engine of claim 17, wherein the first plurality of grooves is formed into the first interior surface by removing portions of the first interior surface such that the first side wall has a reduced thickness within respective grooves of the first plurality of grooves relative to areas in between the respective grooves.