# US 11,441,447 B2 · Ring-segment surface-side member, ring-segment support-side member, ring segment, stationary-side member unit, and method > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,441,447 B2 - Document ID: US11441447B2 - Status: Granted - Kind: B2 - Application number: 16/476,209 - Filed: 2017-12-22 - Published: 2021-05-13 - Granted: 2022-09-13 - Earliest claimed: 2017-01-12 - Assignees: Mitsubishi Heavy Industries, Ltd. - Applicants: Mitsubishi Hitachi Power Systems, Ltd. - Inventors: Yamato Shiramasa; Ryuta Ito; Takayuki Kurimura; Yoshifumi Tsuji - Web page: https://patentgrep.com/patent/US11441447B2 ## CPC - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/12: Cooling - F01D 9/04: forming ring or sector - F01D 25/00: Component parts, details, or accessories, not provided for in, or of interest apart from, other groups - F02C 7/00: Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 11/18: using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F05D 2240/11: Shroud seal segments - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2260/201: by impingement of a fluid - F05D 2260/30: Retaining components in desired mutual position - F05D 2300/6033: Ceramic matrix composites [CMC] - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A ring-segment surface-side member is included in a ring segment disposed at a position opposite to a turbine blade on a stationary side of a gas turbine, serves as a part of a combustion gas flow path through which combustion gas flows, and is formed of a ceramic matrix composite. The ring-segment surface-side member includes: a surface portion forming the combustion gas flow path; a turned-back portion including a first part extending outward in a radial direction of the gas turbine from the surface portion and a second part extending toward a central line of the surface portion from an end part of the first part; and a protrusion portion extending outward from the turned-back portion in the radial direction of the gas turbine. ## Claims ### Claim 1 A ring-segment surface-side member of a ring segment disposed at a position opposite to a turbine blade with respect to a radial direction of the gas turbine on a stationary side of a gas turbine, and forming a part of a combustion gas flow path through which combustion gas flows, the ring-segment surface-side member being supported by a ring-segment support-side member, the ring-segment surface-side member being formed of a ceramic matrix composite, the ring-segment surface-side member comprising: a surface portion forming the combustion gas flow path; a turned-back portion including a first part extending outward in a radial direction of the gas turbine from the surface portion and a second part extending toward a central line of the surface portion from an end part of the first part; and a protrusion portion extending outward from the turned-back portion in the radial direction of the gas turbine, wherein the surface portion has a back surface on an outer side in the radial direction, wherein a cooling space, in which cooling air flows, is formed by the back surface, an opposing portion that is an end face of the ring-segment support-side member on an inner side in the radial direction, and a flow-path resistance adjuster provided on the opposing portion, wherein the flow-path resistance adjuster includes: a plurality of dividing plates arranged to divide the cooling space into a plurality of cooling rooms arranged along a direction of combustion gas flow, and a plurality of through-holes each configured to supply cooling air to a respective one of the plurality of cooling rooms, and wherein the flow-path resistance adjuster is configured to adjust a pressure of the cooling air flowing in the cooling space such that a pressure of the cooling air in an upstream-most one of the cooling rooms with respect to a direction of combustion gas flow through the gas turbine is higher than a pressure of the cooling air in a downstream-most one of the cooling rooms with respect to the direction of combustion gas flow. ### Claim 2 A ring-segment support-side member that is included in a ring segment disposed at a position opposite to a turbine blade with respect to a radial direction of the gas turbine on a stationary side of a gas turbine, and supports a ring-segment surface-side member serving as a part of a combustion gas flow path through which combustion gas flows, the ring-segment support-side member being formed of metal, the ring-segment support-side member comprising: an engagement portion to be engaged with the ring-segment surface-side member; and an opposing portion that: faces a back surface of the surface portion of the ring-segment surface-side member, the surface portion forming the combustion gas flow path, and has a surface forming a cooling space in which cooling air flows between the opposing portion and the surface portion, wherein the opposing portion includes a flow-path resistance adjuster configured to adjust a flow-path resistance of the cooling space, the flow-path resistance adjuster including: a plurality of dividing plates arranged to divide the cooling space into a plurality of cooling rooms arranged along a direction of combustion gas flow, and a plurality of through-holes each configured to supply cooling air to a respective one of the plurality of cooling rooms, and and wherein the flow-path resistance adjuster is configured to adjust a pressure of the cooling air flowing in the cooling space such that a pressure of the cooling air in an upstream-most one of the cooling rooms with respect to a direction of combustion gas flow through the gas turbine is higher than a pressure of the cooling air in a downstream-most one of the cooling rooms with respect to the direction of combustion gas flow. ### Claim 3 (depends on 2) The ring-segment support-side member according to claim 2, further comprising a plurality of through-holes that connect the opposing portion with a cooling air supply space into which the cooling air is supplied, and through which the cooling air flows, wherein each of the plurality of through-holes has a cross-sectional area differing in a direction of combustion gas flow through the gas turbine. ### Claim 4 (depends on 2) The ring-segment support-side member according to claim 2, wherein the opposing portion is tilted in a direction so as to be closer to the back surface of the ring-segment surface-side member in a direction from a combustion gas flow upstream side of the ring-segment support-side member toward a combustion gas flow downstream side of the ring-segment support-side member. ### Claim 5 (depends on 2) The ring-segment support-side member according to claim 2, wherein the opposing portion of the flow-path resistance adjuster has at least one of (i) a surface having a surface roughness that varies with position, and (ii) a surface having a non-level part. ### Claim 6 (depends on 2) The ring-segment support-side member according to claim 2, wherein the flow-path resistance adjuster includes a dividing plate separating the cooling space into a plurality of spaces in a cross section orthogonal to a rotational direction. ### Claim 7 (depends on 6) The ring-segment support-side member according to claim 6, wherein the dividing plate is provided integrally with the opposing portion. ### Claim 8 (depends on 6) The ring-segment support-side member according to claim 6, wherein the dividing plate is a plate member inserted in a groove on the surface of the opposing portion facing the back surface. ### Claim 9 (depends on 6) The ring-segment support-side member according to claim 6, wherein a part of the dividing plate which comes in contact with a surface of the ring-segment surface-side member opposite to the surface portion with respect to a radial direction of the gas turbine is made of a material different from the material of the ring-segment support-side member. ### Claim 10 (depends on 1) A ring segment comprising: the ring-segment surface-side member according to claim 1; and the ring-segment support-side member disposed on the outer side of the ring-segment surface-side member in the radial direction of the gas turbine, the ring-segment support-side member supporting the ring-segment surface-side member to form a cooling space in which the cooling air flows between the ring-segment support-side member and the ring-segment surface-side member, and formed of metal, wherein the ring-segment surface-side member includes a seal at at least one of (i) a position upstream of the protrusion portion with respect to the direction of combustion gas flow and (ii) a position downstream of the protrusion portion with respect to the direction of combustion gas flow. ### Claim 11 (depends on 10) A gas turbine comprising: a turbine blade attached to a rotatable turbine shaft; a turbine vane fixed facing the turbine blade in an axial direction; the ring segment according to claim 10; and a turbine casing disposed on an outer periphery of the ring segment and supporting the turbine vane. ### Claim 12 A ring segment disposed at a position opposite to a turbine blade with respect to a radial direction of the gas turbine on a stationary side of a gas turbine, the ring segment comprising: a ring-segment surface-side member serving as a part of a combustion gas flow path through which combustion gas flows and formed of a ceramic matrix composite; and a ring-segment support-side member disposed on an outer side of the ring-segment surface-side member in a radial direction of the gas turbine, supporting the ring-segment surface-side member, forming a cooling space in which cooling air flows between the ring-segment support-side member and the ring-segment surface-side member, and formed of metal, wherein the ring-segment support-side member includes: a seal provided at an end face of the ring-segment support-side member in a rotational direction of the gas turbine, extending in an axial direction of the gas turbine, having both ends being in contact with members adjacent thereto in the axial direction, and sealing air flow in the radial direction of the gas turbine, and a flow-path resistance adjuster configured to adjust a flow-path resistance of the cooling space wherein the ring-segment surface-side member is disposed on an inner side of the seal in the radial direction of the gas turbine, and wherein the flow-path resistance dividing plate includes: a plurality of dividing plates arranged to divide the cooling space into a plurality of cooling rooms arranged along a direction of combustion gas flow, and a plurality of through-holes each configured to supply cooling air to a respective one of the plurality of cooling rooms, and wherein the flow-path resistance dividing plate is configured to adjust a pressure of cooling air flowing in the cooling space such that a pressure of the cooling air in an upstream-most one of the cooling rooms with respect to a direction of combustion gas flow through the gas turbine is higher than a pressure of the cooling air in a downstream-most one of the cooling rooms with respect to the direction of combustion gas flow. ### Claim 13 (depends on 12) The ring segment according to claim 12, wherein the ring-segment surface-side member is supported at a position separated, in the radial direction of the gas turbine, from a position at which the ring-segment support-side member is supported by another member. ### Claim 14 (depends on 12) A gas turbine comprising: a turbine blade attached to a rotatable turbine shaft; a turbine vane fixed facing the turbine blade in an axial direction; the ring segment according to claim 12; and a turbine casing disposed on an outer periphery of the ring segment and supporting the turbine vane.