# US 2008/0166240 A1 · Advanced cooling method for combustion turbine airfoil fillets > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2008/0166240 A1 - Document ID: US20080166240A1 - Status: Published application - Kind: A1 - Application number: 11/649,573 - Filed: 2007-01-04 - Published: 2008-07-10 - Earliest claimed: 2007-01-04 - Assignees: Siemens Power Generation, Inc. - Inventors: Robert Kenmer Scott; Alexander Ralph Beeck - Web page: https://patentgrep.com/patent/US20080166240A1 ## CPC - F01D 5/187: {Convection cooling} - 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)} - F05B 2240/801: cooled platforms - F05D 2240/126: Baffles or ribs - F05D 2240/81: Cooled platforms - F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05B: INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract The present invention is directed to a hollow turbine airfoil having a cooling system designed to provide enhanced cooling to the fillet of a turbine airfoil. The turbine airfoil may include at least one fillet cooling channel, passing proximate to the fillet. A portion of the fillet cooling channel may be positioned proximate to the fillet outer surface without breaching an outer surface of the turbine airfoil. The turbine airfoil may include a vortex plate positioned adjacent to the end wall inner surface proximate to the fillet and an opening of the fillet cooling channel may be in fluid communication with the vortex chamber. The turbine airfoil may also include at least one end wall film cooling channel that may extend obliquely through the end wall and may be in fluid communication with the vortex chamber. ## Claims ### Claim 1 A turbine airfoil, comprising: a generally elongated airfoil having a leading edge, a trailing edge, a pressure side wall and a suction side wall, an end wall extending generally orthogonal to the generally elongated airfoil and proximate an end of the generally elongated airfoil, and an internal cooling system formed from at least one cooling cavity in the turbine airfoil; at least one fillet cooling channel, passing proximate to an intersection between a side wall and the end wall, positioned such that a first opening of the at least one fillet cooling channel is situated in an inner surface of the side wall and a second opening of the at least one fillet cooling channel is situated in the inner surface of the end wall; and wherein a portion of the at least one fillet cooling channel is positioned proximate to the intersection between the side wall and the end wall without breaching an outer surface of the turbine airfoil. ### Claim 2 (depends on 1) The turbine airfoil of claim 1, further comprising a first impingement plate positioned in the internal cooling system proximate to an inner surface of the end wall, wherein a first impingement plate cavity is formed between the inner surface of the end wall and the first impingement plate; ### Claim 3 (depends on 1) The turbine airfoil of claim 1, further comprising a fillet on the outer surface of the turbine airfoil that extends along the intersection between the generally elongated airfoil and the end wall. ### Claim 4 (depends on 2) The turbine airfoil of claim 2, wherein the cooling system further comprises a second impingement plate, wherein the second impingement plate is positioned generally along the inner surface of the side wall of the generally elongated airfoil. ### Claim 5 (depends on 4) The turbine airfoil of claim 4, further comprising a closure plug attached to the inner surface of the side wall and proximate to an end of the second impingement plate closest to the end wall, thereby forming a second impingement cavity between the inner surface of the side wall, the second impingement plate and the closure plug. ### Claim 6 (depends on 5) The turbine airfoil of claim 5, wherein the closure plug is positioned on the side wall such that the end of the side wall proximate the end wall and the closure plug are on opposite sides of the first opening of the at least one fillet cooling channel in the inner surface of the side wall. ### Claim 7 (depends on 1) The turbine airfoil of claim 1, further comprising a vortex plate positioned proximate to an end of the end wall proximate a side wall, wherein a vortex chamber is formed proximate to the inner surface of the end wall and the vortex plate. ### Claim 8 (depends on 7) The turbine airfoil of claim 7, wherein the second opening of the at least one fillet cooling channel is in fluid communication with the vortex chamber. ### Claim 9 (depends on 8) The turbine airfoil of claim 8, further comprising at least one end wall film cooling channel, extending obliquely relative to the end wall, positioned such that a first opening of the at least one end wall film cooling channel is situated on the inner surface of the end wall and a second opening of the at least one end wall film cooling channel is situated on an outer surface of the end wall. ### Claim 10 (depends on 9) The turbine airfoil of claim 9, wherein the vortex plate includes at least one vortex orifice in fluid communication with the at least one cooling cavity. ### Claim 11 (depends on 9) The turbine airfoil of claim 9, wherein the first opening of the at least one end wall film cooling channel is in fluid communication with the vortex chamber. ### Claim 12 (depends on 11) The turbine airfoil of claim 11, wherein the at least one end wall film cooling channels are offset from the at least one fillet cooling channels such that none of the at least one end wall film cooling channels intersect with any of the at least one fillet cooling channels. ### Claim 13 (depends on 11) The turbine airfoil of claim 11, wherein the cooling system further comprises a second impingement plate, wherein the second impingement plate is positioned generally along the inner surface of the side wall. ### Claim 14 (depends on 13) The turbine airfoil of claim 13, further comprising a closure plug attached to the inner surface of the side wall and proximate to an end of the second impingement plate closest to the end wall, thereby forming a second impingement cavity between the inner surface of the side wall, the second impingement plate and the closure plug. ### Claim 15 (depends on 14) The turbine airfoil of claim 14, wherein the closure plug is positioned on the side wall such that the end of the side wall proximate the end wall and the closure plug are on opposite sides of the first opening of the at least one fillet cooling channel in the inner surface of the side wall. ### Claim 16 (depends on 11) The turbine airfoil of claim 11, wherein the vortex plate includes at least one vortex orifice in fluid communication with the at least one cooling cavity. ### Claim 17 (depends on 8) The turbine airfoil of claim 8, wherein the cooling system further comprises a second impingement plate, wherein the second impingement plate is positioned generally along the inner surface of the side wall. ### Claim 18 (depends on 17) The turbine airfoil of claim 17, further comprising a closure plug attached to the inner surface of the side wall and proximate to an end of the second impingement plate closest to the end wall, thereby forming a second impingement plate cavity between the inner surface of the side wall, the second impingement plate and the closure plug. ### Claim 19 (depends on 18) The turbine airfoil of claim 18, wherein the closure plug is positioned on the side wall such that the end of the side wall proximate the end wall and the closure plug are on opposite sides of the first opening of the at least one fillet cooling channel in the inner surface of the side wall. ### Claim 20 (depends on 19) The turbine airfoil of claim 19, wherein the vortex plate includes at least one vortex orifice in fluid communication with the first impingement plate cavity.