# US 11,028,703 B2 · Gas turbine engine airfoil with tip leading edge shelf discourager > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,703 B2 - Document ID: US11028703B2 - Status: Granted - Kind: B2 - Application number: 16/002,688 - Filed: 2018-06-07 - Published: 2019-12-12 - Granted: 2021-06-08 - Earliest claimed: 2018-06-07 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Emma J. Place - Web page: https://patentgrep.com/patent/US11028703B2 ## CPC - F01D 5/20: Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F05D 2240/305: related to the pressure side of a rotor blade - F05D 2240/307: related to the tip of a rotor blade - F05D 2250/182: crenellated, notched - F05D 2260/202: by film cooling - 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 ## Abstract An airfoil including a pressure sidewall and a suction sidewall extending from a root section of the airfoil to a tip region of the airfoil and a leading edge and a trailing edge defines a chord length of the airfoil therebetween. A tip shelf is formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall with a tip shelf discourager that extends from the tip shelf. ## Claims ### Claim 1 An airfoil for a gas turbine engine, comprising: a pressure sidewall and a suction sidewall extending to a tip region of the airfoil; a leading edge and a trailing edge defining a chord length of the airfoil therebetween; a suction side squealer tip wall that extends axially along the suction sidewall of the airfoil at the tip region from the leading edge to the trailing edge; a pressure side squealer tip wall that extends axially along the tip region, from leading edge to trailing edge; a squealer pocket formed within the tip region between the pressure sidewall and the suction sidewall, the squealer pocket defines a closed perimeter radial recess in the tip region between the pressure side squealer tip wall and suction side squealer tip wall as the pressure side squealer tip wall is of the same radial height from a bottom of the squealer pocket as the suction side squealer tip wall; a tip shelf formed along the tip region of the airfoil transverse to the pressure side squealer tip wall; and a tip shelf discourager that extends from the tip shelf, the tip shelf discourager is equal to a radial height of the pressure side squealer tip wall and the suction side squealer tip wall, the tip shelf discourager comprises cooling apertures to permit cooling flow from tip shelf cooling holes to flow through the tip shelf discourager, wherein the tip shelf discourager extends for only a portion of a length of the tip shelf to form a discourager pocket along the pressure sidewall adjacent the trailing edge. ### Claim 2 (depends on 1) The airfoil as recited in claim 1, wherein the squealer pocket extends for more than 15% of the chord length and less than 75% of the chord length. ### Claim 3 (depends on 1) The airfoil as recited in claim 1, further comprising a plurality of cooling holes formed in the squealer pocket to maintain a pocket of cooling fluid along the tip region of the airfoil between the pressure side squealer tip wall and the suction side squealer tip wall. ### Claim 4 (depends on 1) The airfoil as recited in claim 1, wherein the tip shelf discourager is about 0.01 inches in width. ### Claim 5 (depends on 1) The airfoil as recited in claim 1, wherein the squealer pocket is formed along a portion of the chord of the tip region, the squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge. ### Claim 6 (depends on 1) The airfoil as recited in claim 1, wherein the pressure side squealer tip wall is defined between the tip shelf or discourager pocket and the squealer pocket, spaced from the pressure sidewall by the discourager pocket, and spaced from the suction sidewall by the squealer pocket. ### Claim 7 (depends on 1) The airfoil as recited in claim 1, wherein the width of the tip shelf may be a minimum of 1.5 times the width of the tip shelf discourager. ### Claim 8 (depends on 1) The airfoil as recited in claim 1, wherein the tip shelf and the tip shelf discourager is longer than the squealer pocket along the chord. ### Claim 9 A method of directing a cooling flow from an airfoil for a gas turbine engine, comprising: discouraging a tip shelf cooling air from being mixed with core gas path air and pushed over a blade tip region with a tip shelf discourager that is equal to a radial height of a pressure side squealer tip wall and a suction side squealer tip wall that defines a closed perimeter radial recess in the tip region between the pressure side squealer tip wall and suction side squealer tip wall as the pressure side squealer tip wall is of the same radial height from a bottom of the squealer pocket as the suction side squealer tip wall, the tip shelf discourager comprises cooling apertures to permit cooling flow from tip shelf cooling holes to flow through the tip shelf discourager, wherein the tip shelf discourager extends for only a portion of a length of the tip shelf to form a discourager pocket along the pressure sidewall adjacent the trailing edge maintaining a region of cooling fluid along the pressure sidewall; and directing a portion of a tip shelf cooling air through cooling holes in the tip shelf discourager that extends from a tip shelf toward the pressure side of the airfoil. ### Claim 10 (depends on 9) The method as recited in claim 9, further comprising directing a portion of the tip shelf cooling air along a length of a tip shelf discourager that extends from a tip shelf. ### Claim 11 An airfoil for a gas turbine engine, comprising: a pressure sidewall and a suction sidewall extending to a tip region of the airfoil; a leading edge and a trailing edge defining a chord length of the airfoil therebetween; a tip shelf formed along the tip region of the airfoil between the pressure sidewall and a pressure side squealer tip wall; a suction side squealer tip wall that extends axially along the suction sidewall of the airfoil at the tip region from the leading edge to the trailing edge; a pressure side squealer tip wall that extends axially along the tip region, from leading edge to trailing edge; a squealer pocket formed within the tip region between the pressure sidewall and the suction sidewall, the squealer pocket defines a closed perimeter radial recess in the tip region between the pressure side squealer tip wall and suction side squealer tip wall as the pressure side squealer tip wall is of the same radial height from a bottom of the squealer pocket as the suction side squealer tip wall; a tip shelf discourager that extends from the tip shelf, wherein the tip shelf extends from the leading edge of a pressure side squealer tip wall to an intersection of the pressure sidewall and the suction sidewall adjacent the trailing edge such that the tip shelf communicates with both the pressure sidewall and the suction sidewall proximate to the trailing edge, the tip shelf discourager is equal to a radial height of the pressure side squealer tip wall and the suction side squealer tip wall, the tip shelf discourager comprises cooling apertures to permit cooling flow from tip shelf cooling holes to flow through the tip shelf discourager, wherein the tip shelf extends from the leading edge to an intersection of the pressure sidewall and the suction sidewall adjacent the trailing edge such that the tip shelf communicates with both the pressure sidewall and the suction sidewall proximate to the trailing edge, wherein the tip shelf extends around the leading edge and onto the suction sidewall to terminate on the suction sidewall between the leading edge and the trailing edge of the airfoil, wherein the tip shelf discourager extends for only a portion of a length of the tip shelf to form a discourager pocket along the pressure sidewall adjacent the trailing edge; a multiple of tip shelf cooling holes that direct a portion of a tip shelf cooling air between the pressure side squealer tip wall and the tip shelf discourager; and a multiple of cooling holes through the tip shelf discourager that direct a portion of a tip shelf cooling air from the multiple of tip shelf cooling holes through the tip shelf discourager toward the pressure side of the airfoil. ### Claim 12 (depends on 11) The airfoil as recited in claim 11, further comprising a squealer pocket formed within the tip region, the squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge. ### Claim 13 (depends on 12) The airfoil as recited in claim 12, wherein the squealer pocket extends for more than 15% of the chord length and less than 75% of the chord length.