# US 2019/0170014 A1 · Gas turbine engine cooling component > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0170014 A1 - Document ID: US20190170014A1 - Status: Published application - Kind: A1 - Application number: 15/832,925 - Filed: 2017-12-06 - Published: 2019-06-06 - Earliest claimed: 2017-12-06 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Brandon W. Spangler; Adam P. Generale; Ky H. Vu - Web page: https://patentgrep.com/patent/US20190170014A1 ## CPC - F01D 25/12: 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} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/122: related to the trailing edge of a stator vane - F05D 2240/81: Cooled platforms - F05D 2250/185: serpentine-like - F05D 2260/201: by impingement of a fluid - 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 component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn. ## Claims ### Claim 1 A component for a gas turbine engine comprising: a platform having a gas path side and a non-gas path side; at least one airfoil extending from the gas path side of the platform, wherein the at least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform; and a cover plate located adjacent the non-gas path side of the platform, the cover plate including: a first plurality of fluid openings extending through the cover plate; and at least one bulge at least partially defining a fluid passageway with the serpentine turn. ### Claim 2 (depends on 1) The gas turbine engine component of claim 1, wherein a perimeter of the cover plate is attached to a land on the non-gas path side of the platform and the at least one bulge is spaced inward from a perimeter of the cover plate. ### Claim 3 (depends on 1) The gas turbine engine component of claim 1, wherein the non-gas path side of the platform includes a feed cavity surrounding an inlet to the serpentine cavity. ### Claim 4 (depends on 3) The gas turbine engine component of claim 3, wherein the cover plate encloses the inlet to the serpentine feed cavity. ### Claim 5 (depends on 4) The gas turbine engine component of claim 4, wherein the at least one airfoil includes a cooling cavity forward of the serpentine cavity having an inlet spaced from the cover plate. ### Claim 6 (depends on 1) The gas turbine engine component of claim 1, wherein the cover plate includes a pair of airfoils each having a corresponding serpentine turn on the non-gas path side of the platform and the cover plate includes a pair of bulges each aligned with one of the serpentine turns. ### Claim 7 (depends on 6) The gas turbine engine component of claim 6, wherein the first plurality of fluid openings in the cover plate are located on a first circumferential side of the at least one bulge and a second plurality of fluid openings are located on a second circumferential side of the at least one bulge. ### Claim 8 (depends on 1) The gas turbine engine component of claim 1, wherein the cover plate includes at least one elongated slot opening. ### Claim 9 (depends on 8) The gas turbine engine component of claim 8, wherein the cover plate and the non-gas path side of the platform each at least partially define a fluid opening into a feed cavity in the non-gas path side of the platform. ### Claim 10 (depends on 1) The gas turbine engine component of claim 1, wherein the cover plate is free of non-cooling apertures. ### Claim 11 (depends on 1) The gas turbine engine component of claim 1, wherein the serpentine cavity feeds trailing edge cooling apertures on the at least one airfoil. ### Claim 12 A gas turbine engine, comprising: a compressor section; a combustor section in fluid communication with said compressor section; a turbine section in fluid communication with said combustor section; and wherein one of the compressor section or the turbine section includes at least one component having a platform having a gas path side and a non-gas path side; at least one airfoil extending from the gas path side of the platform, wherein the at least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform; and a cover plate located adjacent the non-gas path side of the platform, the cover plate including: a first plurality of fluid openings extending through the cover plate; and at least one bulge at least partially defining a fluid passageway with the serpentine turn. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein a perimeter of the cover plate is attached to a land on the non-gas path side of the platform and the at least one bulge is spaced inward from a perimeter of the cover plate. ### Claim 14 (depends on 12) The gas turbine engine of claim 12, wherein the non-gas path side of the platform includes a feed cavity surrounding an inlet to the serpentine cavity. ### Claim 15 (depends on 14) The gas turbine engine of claim 14, wherein the cover plate encloses the inlet to the serpentine feed cavity. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the at least one airfoil includes a cooling cavity forward of the serpentine cavity having an inlet spaced from the cover plate. ### Claim 17 (depends on 12) The gas turbine engine of claim 12, wherein the cover plate includes a pair of airfoils each having a corresponding serpentine turn on the non-gas path side of the platform and the cover plate includes a pair of bulges each aligned with one of the serpentine turns. ### Claim 18 (depends on 17) The gas turbine engine of claim 17, wherein the first plurality of fluid openings in the cover plate are located on a first circumferential side of the at least one bulge and a second plurality of fluid openings are located on a second circumferential side of the at least one bulge. ### Claim 19 (depends on 12) The gas turbine engine of claim 12, wherein the cover plate includes at least one elongated slot opening and the serpentine cavity feeds trailing edge cooling apertures on the at least one airfoil. ### Claim 20 (depends on 19) The gas turbine engine of claim 19, wherein the cover plate and the non-gas path side of the platform each at least partially define a fluid opening into the feed cavity in the non-gas path side of the platform.