# US 11,078,793 B2 · Gas turbine engine airfoil with large thickness properties > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,078,793 B2 - Document ID: US11078793B2 - Status: Granted - Kind: B2 - Application number: 16/574,359 - Filed: 2019-09-18 - Published: 2020-05-07 - Granted: 2021-08-03 - Earliest claimed: 2014-06-06 - Assignees: Raytheon Technologies Corporation - Applicants: Raytheon Technologies Corporation - Inventors: Wolfgang Balzer; Thomas J. Praisner; Atul Kohli; Mark F. Zelesky; Dominic J. Mongillo, Jr. - Web page: https://patentgrep.com/patent/US11078793B2 ## CPC - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F05D 2220/32: in gas turbines - F05D 2250/10: Two-dimensional - F05D 2260/202: by film cooling - 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) - 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 an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location. ## Claims ### Claim 1 An airfoil for a gas turbine engine comprising: an airfoil including pressure and suction sides joined at leading and trailing edges, the airfoil extends a span in a radial direction from 0% span position at a support to a 100% span position at an end, the leading and trailing edges are spaced apart from one another an axial chord in an axial direction, a cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides, the diameter corresponds to the largest circle fitting within the cross-section, a ratio of the diameter to the axial chord is at least 0.45 between 50% and 70% span location wherein the airfoil is configured to be arranged in a circumferential array of airfoils having an airfoil pitch defined as a circumferential distance between the airfoil and an adjacent airfoil at the 50% span location or greater, and wherein a ratio of the airfoil pitch to the axial chord is between 1.5 and 1.9. ### Claim 2 (depends on 1) The airfoil according to claim 1, comprising a root supporting a platform that corresponds to the support, the end providing a terminal end of the airfoil. ### Claim 3 (depends on 2) The airfoil according to claim 2, wherein the root includes a fir tree. ### Claim 4 (depends on 1) The airfoil according to claim 1, wherein the airfoil is a rotating airfoil. ### Claim 5 (depends on 1) The airfoil according to claim 1, wherein the ratio of the diameter to the axial chord does not exceed 0.7. ### Claim 6 (depends on 5) The airfoil according to claim 5, wherein the ratio of the diameter to the axial chord is at least 0.5, but does not exceed 0.65. ### Claim 7 (depends on 5) The airfoil according to claim 5, wherein the ratio of the airfoil pitch to the axial chord is at least 1.6 at 60% span. ### Claim 8 (depends on 1) The airfoil according to claim 1, wherein the span location is between 75% and 95%. ### Claim 9 (depends on 8) The airfoil according to claim 8, wherein the ratio of the airfoil pitch to the axial chord is at least 1.8 at 80% span. ### Claim 10 (depends on 1) The airfoil according to claim 1, wherein the airfoil is a turbine blade. ### Claim 11 (depends on 10) The airfoil according to claim 10, wherein the airfoil includes cooling holes provided on at least one of the leading edge and the pressure side. ### Claim 12 (depends on 1) The airfoil according to claim 1, wherein the airfoil is unshrouded. ### Claim 13 A circumferential array of airfoils, comprising: a circumferential array of airfoils, the array has an airfoil including pressure and suction sides joined at leading and trailing edges, the airfoil extends a span from a support to an end in a radial direction, 0% span and 100% span positions respectively correspond to the exterior wall at the support and the end, the leading and trailing edges are spaced apart from one another an axial chord in an axial direction, a cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides, the diameter corresponds to the largest circle fitting within the cross-section, a ratio of the diameter to the axial chord is at least 0.45 at a 50% span location or greater, and an airfoil pitch defined as a circumferential distance between adjacent airfoils at the 50% span location or greater, wherein a ratio of the airfoil pitch to the axial chord is between 1.5 and 1.9. ### Claim 14 (depends on 13) The circumferential array of airfoils according to claim 13, wherein the array of airfoils are rotating airfoils. ### Claim 15 (depends on 13) The circumferential array of airfoils according to claim 13, wherein the ratio of the diameter to the axial chord does not exceed 0.7. ### Claim 16 (depends on 15) The circumferential array of airfoils according to claim 15, wherein the ratio of the diameter to the axial chord is at least 0.5, but does not exceed 0.65. ### Claim 17 (depends on 13) The circumferential array of airfoils according to claim 13, wherein the ratio of the airfoil pitch to the axial chord is between 1.65 and 1.8. ### Claim 18 (depends on 13) The circumferential array of airfoils according to claim 13, wherein the span location is between 50% and 70%. ### Claim 19 (depends on 13) The circumferential array of airfoils according to claim 13, wherein the span location is between 75% and 95%. ### Claim 20 (depends on 13) The circumferential array of airfoils according to claim 13, wherein the airfoil is unshrouded.