# US 2013/0156549 A1 · Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2013/0156549 A1 - Document ID: US20130156549A1 - Status: Published application - Kind: A1 - Application number: 13/326,372 - Filed: 2011-12-15 - Published: 2013-06-20 - Earliest claimed: 2011-12-15 - Assignees: General Electric Company - Inventors: Jaime Javier Maldonado - Web page: https://patentgrep.com/patent/US20130156549A1 ## CPC - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape} - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F05D 2250/131: polygonal - 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 An improved nozzle vane for a gas turbine engine, comprising a vane wall having inner and outer wall surfaces, the wall surfaces being spaced from one another to define a plurality of fluid passageways for a cooling medium; discreet cavities formed by interior wall members disposed between the inner and outer wall surfaces and within the fluid passageway for the cooling medium; a plurality of impingement cooling sleeves disposed in the discreet cavities defined by the inner and outer wall surfaces and by interior wall members; and a plurality of non-round, e.g., serrated, openings in each of the impingement cooling sleeves, with the openings being sufficient in size and number to accommodate the flow of a cooling media. ## Claims ### Claim 1 A nozzle vane for a gas turbine engine, comprising: a vane wall having inner and outer wall surfaces, said wall surfaces being uniformly spaced from one another to define a fluid passageway for a cooling medium; a plurality of cavities formed by interior wall members disposed between said inner and outer wall surfaces and within said fluid passageway; a plurality of impingement cooling sleeves disposed in said discreet cavities defined by said inner and outer wall surfaces and said interior wall members; and a plurality of non-round impingement openings in each of said impingement cooling sleeves, said openings being sufficient in size and number to accommodate the flow of said cooling medium into the interior of said fluid passageway. ### Claim 2 (depends on 1) A nozzle vane according to claim 1, wherein said non-round openings in said impingement cooling sleeves comprise generally star-like fluid passages having a radial array of projections emanating from the center of each opening. ### Claim 3 (depends on 1) A nozzle vane according to claim 1, wherein said non-round openings in said impingement cooling sleeves define an array of generally uniform, equidistant fluid pathways emanating from the center of each opening. ### Claim 4 (depends on 1) A nozzle vane according to claim 1, wherein said non-round openings in said impingement cooling sleeves are disposed substantially along the length of each insert sleeve. ### Claim 5 (depends on 1) A nozzle vane according to claim 1, wherein said non-round openings in said impingement cooling sleeves comprise a chevron configuration. ### Claim 6 (depends on 1) A nozzle vane according to claim 1, wherein said flow of said cooling medium impinges on said interior wall surfaces of said nozzle. ### Claim 7 (depends on 1) A nozzle vane according to claim 1, wherein said non-round openings in said impingement cooling sleeves are formed in first and second walls of each one of a plurality of impingement cooling sleeves. ### Claim 8 (depends on 1) A nozzle vane according to claim 1, wherein said discreet cavities formed by said impingement cooling sleeves have the same general configuration as said interior wall members. ### Claim 9 (depends on 1) A nozzle vane according to claim 1, wherein said discreet cavities and said impingement sleeves define a specific fluid flow gap for said cooling medium. ### Claim 10 (depends on 1) A nozzle vane according to claim 1, wherein said discreet cavities extend lengthwise and parallel to one another in said nozzle vane. ### Claim 11 (depends on 1) A nozzle vane according to claim 1, wherein said cooling medium includes compressed air. ### Claim 12 (depends on 1) A nozzle vane according to claim 1, wherein said cooling medium includes steam. ### Claim 13 (depends on 1) A nozzle vane according to claim 1, wherein said cooling medium is a mixture of steam and compressed air. ### Claim 14 (depends on 1) A nozzle vane according to claim 1, wherein the forward edge of said insert sleeve is curved in shape and the side walls of said sleeve generally correspond in shape to the side walls of said cavities. ### Claim 15 (depends on 1) A nozzle vane according to claim 1, wherein said impingement openings in said cooling sleeves result in improved air mixing along said nozzle vane. ### Claim 16 (depends on 1) A nozzle vane according to claim 1, wherein said impingement openings in said cooling sleeves result in increased impingement air jet velocities along said nozzle vane. ### Claim 17 (depends on 1) A nozzle vane according to claim 1, wherein said impingement openings reduce cross flow heat transfer degradation along said nozzle vane.