# US 11,441,428 B2 · Turbine blade and steam turbine including the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,441,428 B2 - Document ID: US11441428B2 - Status: Granted - Kind: B2 - Application number: 17/312,277 - Filed: 2019-10-21 - Published: 2022-04-07 - Granted: 2022-09-13 - Earliest claimed: 2018-12-18 - Assignees: Mitsubishi Power, Ltd. - Applicants: Mitsubishi Power, Ltd. - Inventors: Shigeki Senoo; Kazuhiro Momma; Reza Abhari; Anestis Kalfas; Ilias Papagiannis; Vahid Iranidokht - Web page: https://patentgrep.com/patent/US11441428B2 ## CPC - F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour} - F01D 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F05D 2220/31: in steam turbines - F05D 2240/301: Cross-sectional characteristics - F05D 2250/711: convex - F05D 2250/712: concave - 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 ## Abstract A turbine blade includes an airfoil portion having a pressure surface and a suction surface each of which extends between a leading edge and a trailing edge, and a platform including an end wall to which a base-end portion of the airfoil portion is connected. The end wall includes a concave portion on suction surface disposed at least in a region of suction surface of the end wall, and a convex portion on pressure surface disposed at least in a region of pressure surface of the end wall. The concave portion on suction surface has a bottom point located on an axially upstream side of a tangent point on the suction surface, the suction surface having a tangential line extending in an axial direction through the tangent point. ## Claims ### Claim 1 A turbine blade, comprising: an airfoil portion having a pressure surface and a suction surface each of which extends between a leading edge and a trailing edge; and a platform including an end wall to which a base-end portion of the airfoil portion is connected, wherein the end wall includes: a concave portion on suction surface disposed at least in a region of suction surface of the end wall; and a convex portion on pressure surface disposed at least in a region of pressure surface of the end wall, wherein the concave portion on suction surface has a bottom point located on an axially upstream side of a tangent point on the suction surface, the suction surface having a tangential line extending in an axial direction through the tangent point, wherein the end wall has at least one contour line on the concave portion on suction surface, the at least one contour line having a normal line on an intersection point between the at least one contour line and the suction surface such that a normal vector having a negative gradient along the normal line is directed toward the airfoil portion, and wherein the convex portion on pressure surface has a peak point located on an axially downstream side of the tangent point. ### Claim 2 (depends on 1) The turbine blade according to claim 1, wherein the convex portion on pressure surface has at least one contour line having a normal line on an intersection point between the at least one contour line and the pressure surface such that a normal vector having a positive gradient along the normal line is directed toward the airfoil portion. ### Claim 3 (depends on 1) The turbine blade according to claim 1, wherein the convex portion on pressure surface expands along the pressure surface at least from a position of the peak point to a position of the bottom point of the concave portion on suction surface in the axial direction. ### Claim 4 (depends on 1) The turbine blade according to claim 1, wherein a ratio L1/L0 of an axial distance L1 between the bottom point of the concave portion on suction surface and the peak point of the convex portion on pressure surface to an axial length L0 of the airfoil portion on the end wall is at least 0.1 and at most 0.9. ### Claim 5 (depends on 1) The turbine blade according to claim 1, wherein an angle between an axial straight line, and a straight line that connects the bottom point of the concave portion on suction surface and the peak point of the convex portion on pressure surface of an adjacent turbine blade is not less than 10 degrees and not greater than 80 degrees. ### Claim 6 (depends on 1) The turbine blade according to claim 1, wherein the convex portion on pressure surface extends along the pressure surface over not less than 90% of an axial length L0 of the airfoil portion on the end wall. ### Claim 7 (depends on 1) The turbine blade according to claim 1, wherein the turbine blade is configured such that the concave portion on suction surface and the convex portion on pressure surface of an adjacent turbine blade form a smooth slope from the bottom point of the concave portion on suction surface to the peak point of the convex portion on pressure surface. ### Claim 8 (depends on 1) The turbine blade according to claim 1, wherein the end wall further includes a convex portion on suction surface disposed at least in the region of suction surface, and wherein the convex portion on suction surface expands along the suction surface over a range that includes a throat forming position located on the axially downstream side of the tangent point on the suction surface. ### Claim 9 (depends on 8) The turbine blade according to claim 8, wherein the convex portion on pressure surface and the convex portion on suction surface of an adjacent turbine blade share at least one contour line. ### Claim 10 (depends on 1) The turbine blade according to claim 1, wherein a ratio L2/L0 of an axial distance L2 between the leading edge and a front end of the platform to an axial length L0 of the airfoil portion on the end wall is at most 0.1. ### Claim 11 (depends on 1) The turbine blade according to claim 1, wherein the base-end portion of the airfoil portion includes a fillet portion disposed in a connection portion to the platform, and wherein an axial distance L2 between the leading edge and a front end of the platform is not less than 50% and not greater than 100% of a width of the fillet portion in a planar view. ### Claim 12 (depends on 1) The turbine blade according to claim 1, wherein the concave portion on suction surface extends without crossing a dividing line forming a boundary with an adjacent turbine blade. ### Claim 13 (depends on 1) A steam turbine, comprising: the turbine blade according to claim 1. ### Claim 14 (depends on 13) The steam turbine according to claim 13, comprising: a rotor blade which is the turbine blade; and a stator vane disposed adjacent to the rotor blade on an upstream side of the rotor blade in an axial direction of the steam turbine, wherein a ratio L3/L0 of an axial width L3 of a cavity formed between the rotor blade and the stator vane to an axial length L0 of the airfoil portion on the end wall is at least 0.15.