# US 10,119,406 B2 · Blade with stress-reducing bulbous projection at turn opening of coolant passages > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,119,406 B2 - Document ID: US10119406B2 - Status: Granted - Kind: B2 - Application number: 15/152,698 - Filed: 2016-05-12 - Published: 2017-11-16 - Granted: 2018-11-06 - Earliest claimed: 2016-05-12 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Brendon James Leary; Elisabeth Kraus Black; Gregory Thomas Foster; Michelle Jessica Iduate; Jacob Charles Perry, II - Web page: https://patentgrep.com/patent/US10119406B2 ## CPC - F01D 5/187: {Convection cooling} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/12: Cooling - F05D 2220/32: in gas turbines - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor - F05D 2250/75: given by its similarity to a letter, e.g. T-shaped - F05D 2260/22141: using fins or ribs - F05D 2260/941: particularly aimed at mechanical or thermal stress reduction - 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 blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and forming a radially extending coolant receiving chamber. A rib partitions the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib. Each passage is enclosed at an end of the radially extending chamber by an end member of the radially extending chamber. A turn opening is defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber. A bulbous projection extends along the end of the rib and on opposing radially extending sides of the turn opening to reduce stress in the rib and/or connecting fillets. ## Claims ### Claim 1 A blade comprising an airfoil defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant, the blade further comprising: a rib configuration including: a rib partitioning the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib, each passage enclosed at an end of the radially extending chamber by an end member of the radially extending chamber, and a turn opening defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber; and a bulbous projection extending along the end of the rib and on opposing radially extending sides of the turn opening. ### Claim 2 (depends on 1) The blade of claim 1, wherein the bulbous projection extends in a U-shape, an open end of the U-shape facing towards the end member of the radially extending chamber. ### Claim 3 (depends on 2) The blade of claim 2, wherein the bulbous projection extends only along the U-shape and terminates into the end member of the radially extending chamber. ### Claim 4 (depends on 2) The blade of claim 2, wherein a first end of the U-shape is angled relative to a second end of the U-shape. ### Claim 5 (depends on 1) The blade of claim 1, wherein the bulbous projection further extends along the end member of the radially extending chamber between the opposing radially extending sides of the turn opening. ### Claim 6 (depends on 1) The blade of claim 1, wherein the rib has a first thickness along a length thereof, and the bulbous projection has a second thickness greater than the first thickness. ### Claim 7 (depends on 1) The blade of claim 1, wherein the rib includes a curved camber line rib coupled at each end to a selected outer wall at a fillet, the curved camber line rib defining the first passage as an outer passage between the selected outer wall and the curved camber line rib and the second passage as an inner passage adjacent the outer passage, wherein the turn opening is distanced from the fillet by the bulbous projection. ### Claim 8 (depends on 7) The blade of claim 7, wherein the curved camber line rib has a wavy profile. ### Claim 9 (depends on 7) The blade of claim 7, wherein the bulbous projection includes a portion extending towards the inner passage. ### Claim 10 (depends on 1) The blade of claim 1, wherein the bulbous projection has a cross-section defined by more than one radius of curvature. ### Claim 11 (depends on 1) The blade of claim 1, wherein the blade comprises one of a turbine rotor blade and a turbine stator blade. ### Claim 12 A turbine rotor blade comprising an airfoil defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant, the turbine rotor blade further comprising: a rib configuration including: a rib partitioning the radially extending chamber into a first passage on a first side of the rib and an adjacent second passage on an opposing second side of the rib, each passage enclosed at an end of the radially extending chamber by an end member of the radially extending chamber; and a turn opening defined in an end of the rib through which the coolant passes between the first passage and the second passage within the end member of the radially extending chamber; and a bulbous projection extending along the end of the rib and on opposing radially extending sides of the turn opening. ### Claim 13 (depends on 12) The turbine blade of claim 12, wherein the bulbous projection extends in a U-shape, an open end of the U-shape facing towards the end member of the radially extending chamber. ### Claim 14 (depends on 13) The turbine rotor blade of claim 13, wherein the bulbous projection extends only along the U-shape and terminates into the end member of the radially extending chamber. ### Claim 15 (depends on 13) The turbine rotor blade of claim 13, wherein a first end of the U-shape is angled relative to a second end of the U-shape. ### Claim 16 (depends on 12) The turbine rotor blade of claim 12, wherein the bulbous projection further extends along the end member of the radially extending chamber between the opposing radially extending sides of the turn opening. ### Claim 17 (depends on 12) The turbine rotor blade of claim 12, wherein the rib has a first thickness along a length thereof, and the bulbous projection has a second thickness greater than the first thickness. ### Claim 18 (depends on 12) The turbine rotor blade of claim 12, wherein the rib includes a curved camber line rib coupled at each end to a selected outer wall at a fillet, the curved camber line rib defining the first passage as an outer passage between the selected outer wall and the curved camber line rib and the second passage as an inner passage adjacent the outer passage, wherein the turn opening is distanced from the fillets by the bulbous projection. ### Claim 19 (depends on 18) The turbine rotor blade of claim 18, wherein the bulbous projection includes a portion extending towards the inner passage. ### Claim 20 (depends on 12) The turbine rotor blade of claim 12, wherein the bulbous projection has a cross-section defined by more than one radius of curvature.