# US 9,039,371 B2 · Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,039,371 B2 - Document ID: US9039371B2 - Status: Granted - Kind: B2 - Application number: 14/068,070 - Filed: 2013-10-31 - Published: 2015-04-30 - Granted: 2015-05-26 - Earliest claimed: 2013-10-31 - Assignees: Siemens Aktiengesellschaft; Mikro Systems, Inc. - Applicants: Ching-Pang Lee; Benjamin E. Heneveld; Glenn E. Brown; Jill Klinger - Inventors: Ching-Pang Lee; Benjamin E. Heneveld; Glenn E. Brown; Jill Klinger - Web page: https://patentgrep.com/patent/US9039371B2 ## CPC - F01D 5/187: {Convection cooling} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F05D 2240/122: related to the trailing edge of a stator vane - F05D 2240/304: related to the trailing edge of a rotor blade - F05D 2260/201: by impingement of a fluid - F05D 2260/2212: by creating turbulence - 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 A gas turbine engine component, including: a pressure side (12) having an interior surface (34); a suction side (14) having an interior surface (36); a trailing edge portion (30); and a plurality of suction side and pressure side impingement orifices (24) disposed in the trailing edge portion (30). Each suction side impingement orifice is configured to direct an impingement jet (48) at an acute angle (52) onto a target area (60) that encompasses a tip (140) of a chevron (122) within a chevron arrangement (120) formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface. ## Claims ### Claim 1 A gas turbine engine component, comprising: a pressure side comprising an interior surface; a suction side comprising an interior surface; a trailing edge portion; a plurality of suction side and pressure side impingement orifices disposed in the trailing edge portion, wherein each suction side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the suction side interior surface, wherein each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto a target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface, wherein at least one chevron arrangement comprises a plurality of chevrons, a tip of each chevron of the plurality of chevrons being disposed in the respective target area and wings of the chevrons of the plurality of chevrons forming at least one groove there between in which spent cooling air flows. ### Claim 2 (depends on 1) The component of claim 1, wherein outlets of the suction side impingement orifices are disposed on a suction side of a mean-line, and outlets of the pressure side impingement orifices are disposed on a pressure side of the mean-line. ### Claim 3 (depends on 1) The component of claim 1, wherein for after impinging the tip of the chevron spent impingement air diverges in conjunction with a divergence of wings of the chevron each impinged chevron arrangement. ### Claim 4 (depends on 1) The component of claim 1, wherein the pressure side interior surface , the chevron arrangement formed in the pressure side interior surface and the pressure side are integrally cast. ### Claim 5 (depends on 1) The component of claim 1, wherein at least one chevron is discontinuous. ### Claim 6 (depends on 5) The component of claim 5, wherein the tip of at least one chevron is open. ### Claim 7 (depends on 1) The component of claim 1, wherein at least one chevron is continuous. ### Claim 8 (depends on 1) The component of claim 1, wherein the plurality of suction side and pressure side impingement orifices are disposed in a plurality of rows extending radially from a base to a tip of the airfoil, wherein impingement orifices in consecutive rows are at a different elevation between the base and the tip of the airfoil. ### Claim 9 (depends on 1) The component of claim 1, wherein each impingement orifice is configured to position a stagnation point in the target area upstream of the tip of the respective chevron with respect to a direction of flow of spent impingement air. ### Claim 10 (depends on 1) The component of claim 1, further comprising a second stage of impingement orifices disposed downstream of the plurality of impingement orifices, wherein each suction side second stage impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement into the suction side interior wall, wherein each pressure side second stage impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement into the pressure side interior wall, and wherein spent impingement air from the plurality of impingement orifices is guided by the wings of respective chevrons into respective second stage impingement orifices. ### Claim 11 (depends on 10) The component of claim 10, wherein spent impingement air from each of the plurality of impingement orifices is guided by the wings of the respective chevrons into two respective second stage impingement orifices. ### Claim 12 A gas turbine engine component, comprising: an internal surface comprising a chevron arrangement, the chevron arrangement comprising a plurality of chevrons formed in the internal surface, each chevron comprising a tip and a pair of wings, and an impingement orifice configured to direct an impingement jet of cooling fluid onto the internal surface at an angle other than perpendicular, wherein a target area of the impingement jet encompasses the tips of all of the plurality of chevrons within the chevron arrangement, and wherein wings of each chevron of the plurality of chevrons diverge in conjunction with a divergence of spent impingement air. ### Claim 13 (depends on 12) The component of claim 12, comprising: an opposing internal surface; and a plurality of impingement orifices disposed between the internal surface and the opposing internal surface, wherein some of the plurality of impingement orifices are configured to direct a respective impingement jet of cooling fluid onto the internal surface, wherein some of the plurality of impingement orifices are configured to direct a respective impingement jet of cooling fluid onto the opposing internal surface, wherein a target area of each impingement jet encompasses a tip of a chevron within a respective chevron arrangement on the opposing internal surface, and wherein wings of the respective chevron diverge in conjunction with a divergence of respective spent impingement air. ### Claim 14 (depends on 13) The component of claim 13, wherein the impingement orifices alternate between directing an impingement jet onto the internal surface and directing an impingement jet onto the opposing internal surface. ### Claim 15 (depends on 13) The component of claim 13, wherein the plurality of impingement orifices are disposed in a trailing edge portion of an airfoil, the internal surface is disposed on a suction side of the airfoil, and the opposing internal surface is disposed on the pressure side of the airfoil. ### Claim 16 (depends on 12) The component of claim 12, wherein the chevron is discontinuous. ### Claim 17 (depends on 12) The component of claim 12, wherein the tip of the chevron is open. ### Claim 18 (depends on 12) The component of claim 12, wherein the wings of the chevron are oriented at an angle to streamlines the spent impingement air would naturally follow.