# US 2018/0023407 A1 · Gas turbine engine turbine vane baffle and serpentine cooling passage > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2018/0023407 A1 - Document ID: US20180023407A1 - Status: Published application - Kind: A1 - Application number: 15/708,603 - Filed: 2017-09-19 - Published: 2018-01-25 - Earliest claimed: 2015-02-06 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Brandon W. Spangler; Ryan Alan Waite; Steven Bruce Gautschi; Benjamin F. Hagan - Web page: https://patentgrep.com/patent/US20180023407A1 ## CPC - 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)} - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 5/187: {Convection cooling} - F01D 25/12: Cooling - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F05D 2240/126: Baffles or ribs - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/202: by film cooling - F05D 2260/204: by the use of microcircuits - 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 airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity. ## Claims ### Claim 1 An airfoil for a gas turbine engine comprising: pressure and suction side walls joined to one another at leading and trailing edges, the pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface; a baffle arranged in the airfoil cavity, the baffle includes a supply hole; ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls, the ribs configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls, the serpentine cooling passage has first and second passes joined by a bend, the ribs form a film cooling cavity between the first and second passes, and the supply hole fluidly connects the baffle to the film cooling cavity; and film cooling holes extend through the at least one of the pressure and suction side walls, the film cooling holes in fluid communication with the film cooling cavity. ### Claim 2 (depends on 1) The airfoil according to claim 1, comprising inner and outer platforms secured to the airfoil. ### Claim 3 (depends on 2) The airfoil according to claim 2, wherein the baffle extends radially through the outer platform. ### Claim 4 (depends on 1) The airfoil according to claim 1, wherein the ribs include spaced first and second apart ribs that extend radially along and adjacent to the first and second passes, and a lateral rib interconnects the first and second ribs and is adjacent to the bend, the first and second ribs and the lateral rib are arranged in a U-shape. ### Claim 5 (depends on 4) The airfoil according to claim 4, wherein the supply hole is arranged near the lateral rib. ### Claim 6 (depends on 4) The airfoil according to claim 4, wherein the first and second ribs are unbroken along their radial length. ### Claim 7 (depends on 4) The airfoil according to claim 4, wherein the ribs form an inlet pass upstream from and parallel to the first and second passes, the inlet pass and first and second passes form an S-shape. ### Claim 8 (depends on 7) The airfoil according to claim 7, wherein the baffle and the second rib separate the airfoil cavity to provide the second pass, the exterior airfoil surface has trailing edge cooling apertures at the trailing edge, the second pass configured to provide cooling fluid to the trailing edge cooling apertures. ### Claim 9 (depends on 7) The airfoil according to claim 7, wherein the film cooling holes are oriented toward the trailing edge and at a position upstream from the second pass. ### Claim 10 (depends on 1) The airfoil according to claim 1, wherein the serpentine cooling passage is provided between the baffle and both of the pressure and suction sides. ### Claim 11 (depends on 1) The airfoil according to claim 1, wherein the baffle is a separate, discrete structure from the pressure and suction side walls. ### Claim 12 A method of cooling an airfoil for a gas turbine engine, the method comprising: providing an airfoil that includes: pressure and suction side walls joined to one another at leading and trailing edges, the pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface; a baffle arranged in the airfoil cavity, the baffle includes a supply hole; ribs extend between at least one of the pressure and suction side walls into the airfoil cavity and to support the baffle relative to the at least one of the pressure and suction side walls, the ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls, the serpentine cooling passage has first and second passes joined by a bend, the ribs form an inlet pass upstream from and parallel to the first and second passes, the inlet pass and first and second passes form an S-shape, the ribs form a film cooling cavity between the first and second passes, and the supply hole fluidly connects the baffle to the film cooling cavity; and film cooling holes extend through the at least one of the pressure and suction side walls, the film cooling holes in fluid communication with the film cooling cavity; and supplying a first cooling fluid to the inlet pass, the first cooling fluid flows along the inlet pass in a first radial direction; turning the first cooling fluid and flowing the first cooling fluid along the first pass in a second radial direction opposite the first radial direction; turning the first cooling fluid at the bend and flowing the first cooling fluid along the second pass in the first direction; and supplying a second cooling fluid through the baffle and through the supply hole, flowing the second cooling fluid through the film cooling cavity and out the film cooling holes. ### Claim 13 (depends on 12) The method according to claim 12, comprising inner and outer platforms secured to the airfoil. ### Claim 14 (depends on 13) The method according to claim 13, wherein the baffle extends radially through the outer platform. ### Claim 15 (depends on 12) The method according to claim 12, wherein the ribs include spaced first and second apart ribs that extend radially along and adjacent to the first and second passes, and a lateral rib interconnects the first and second rib and is adjacent to the bend, the first and second ribs and the lateral rib arranged in a U-shape and fluidly separating the first and second cooling fluids. ### Claim 16 (depends on 15) The method according to claim 15, wherein the supply hole is arranged near the lateral rib. ### Claim 17 (depends on 15) The method according to claim 15, wherein the first and second ribs are unbroken along their radial length. ### Claim 18 (depends on 15) The method according to claim 15, wherein the baffle and the second rib separate the airfoil cavity to provide the second pass, the exterior airfoil surface has trailing edge cooling apertures at the trailing edge, comprising the step of the second pass supplying the first cooling fluid to the trailing edge cooling apertures. ### Claim 19 (depends on 15) The method according to claim 15, wherein the film cooling holes are oriented toward the trailing edge and at a position upstream from the second pass. ### Claim 20 (depends on 12) The method according to claim 12, wherein the serpentine cooling passage is provided between the baffle and both of the pressure and suction sides.