# US 2017/0284221 A1 · Shield member and jet engine using the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2017/0284221 A1 - Document ID: US20170284221A1 - Status: Published application - Kind: A1 - Application number: 15/623,954 - Filed: 2017-06-15 - Published: 2017-10-05 - Earliest claimed: 2015-04-07 - Assignees: IHI Corporation - Applicants: IHI Corporation - Inventors: Fumiaki WATANABE; Akane OHBO; Hiroyuki YAGI; Tomotake OGAWA; Tsuyoshi TAKEMOTO - Web page: https://patentgrep.com/patent/US20170284221A1 ## CPC - F01D 11/006: {Sealing the gap between rotor blades or blades and rotor} - F01D 25/08: Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) - C04B 35/80: Fibres, filaments, whiskers, platelets, or the like - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - F01D 5/30: Fixing blades to rotors; Blade roots {; Blade spacers} - F01D 11/00: Preventing or minimising internal leakage of working-fluid, e.g. between stages (sealings in general F16J {; sealing arrangements for transition ducts of combustor cans F01D9/023}) - F01D 25/00: Component parts, details, or accessories, not provided for in, or of interest apart from, other groups - F02C 7/28: Arrangement of seals - C04B 2235/3826: Silicon carbides - C04B 2235/5224: Alumina or aluminates - C04B 2235/5244: Silicon carbide - F01D 5/3007: {of axial insertion type} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/80: Platforms for stationary or moving blades - F05D 2260/231: Preventing heat transfer - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - C04B: LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE {(roofing granules E04D7/005)}; CERAMICS (devitrified glass-ceramics C03C10/00); REFRACTORIES; TREATMENT OF NATURAL STONE - 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 shield member is disposed over a gap between platform portions of adjacent turbine rotor blades, made from a ceramic matrix composite, and configured to shield the gap between the platform portions. ## Claims ### Claim 1 A shield member, disposed over a gap between platform portions of adjacent turbine rotor blades, made from a ceramic matrix composite, and configured to shield the gap between the platform portions. ### Claim 2 (depends on 1) The shield member according to claim 1, wherein the platform portions each include a platform portion body formed extending in a direction intersecting a longitudinal direction of a corresponding one of the turbine rotor blades, and a front skirt provided on a leading edge side of the platform portion body, and the shield member comprises a shield member body formed elongated and including a first shield surface located between shank portions connected to the platform portions of the adjacent turbine rotor blades, the first shield surface configured to shield a gap between the platform portion bodies of the adjacent turbine rotor blades by coming into contact with inner surfaces of the platform portion bodies along the inner surfaces of the platform portion bodies, and a leading edge-side shield portion formed elongated and including a second shield surface located between the shank portions of the adjacent turbine rotor blades, a first end in a longitudinal direction of the leading edge-side shield portion integrally provided to a first end in a longitudinal direction of the shield member body while bent from the shield member body, the second shield surface configured to shield a gap between the front skirts of the adjacent turbine rotor blades by coming into contact with inner surfaces of the front skirts along the inner surfaces of the front skirts. ### Claim 3 (depends on 2) The shield member according to claim 2, further comprising restriction portions provided at parts of both sides in the longitudinal direction of the shield member body, the restriction portions formed projecting in a width direction intersecting the longitudinal direction of the shield member body, and curving toward a back surface of the first shield surface, the restriction portions configured to restrict movement of the shield member in the width direction by coming into contact with side surfaces of the shank portions of the adjacent turbine rotor blades. ### Claim 4 (depends on 2) The shield member according to claim 2, wherein the platform portions each include a rear skirt provided on a trailing edge side of the corresponding platform portion body, the rear skirt includes a holding portion, provided to an inner surface of the rear skirt, for holding a second end in the longitudinal direction of the shield member body, and the shield member further comprises a curving portion provided to the second end in the longitudinal direction of the shield member body, formed curving toward a back surface of the first shield surface, and configured to come into contact with the holding portions of the rear skirts of the adjacent turbine rotor blades. ### Claim 5 (depends on 3) The shield member according to claim 3, wherein the platform portions each include a rear skirt provided on a trailing edge side of the corresponding platform portion body, the rear skirt includes a holding portion, provided to an inner surface of the rear skirt, for holding a second end in the longitudinal direction of the shield member body, and the shield member further comprises a curving portion provided to the second end in the longitudinal direction of the shield member body, formed curving toward a back surface of the first shield surface, and configured to come into contact with the holding portions of the rear skirts of the adjacent turbine rotor blades. ### Claim 6 (depends on 2) The shield member according to claim 2, wherein the platform portions each include a rear skirt provided on a trailing edge side of the corresponding platform portion body, the rear skirt includes a holding portion, provided to an inner surface of the rear skirt, for holding a second end in the longitudinal direction of the shield member body, and the shield member further comprises first contact portions provided to full lengths of both sides in the longitudinal direction of the shield member body, the first contact portions formed projecting in a width direction intersecting the longitudinal direction of the shield member body, and curving toward a back surface of the first shield surface, the first contact portions configured to come into contact with side surfaces of the shank portions of the adjacent turbine rotor blades, and with the holding portions of the rear skirts, and second contact portions provided to full lengths of both sides in a longitudinal direction of the leading edge-side shield portion, the second contact portions formed projecting in a width direction intersecting the longitudinal direction of the leading edge-side shield portion, and curving toward a back surface of the second shield surface, the second contact portions configured to come into contact with the side surfaces of the shank portions of the adjacent turbine rotor blades. ### Claim 7 (depends on 2) The shield member according to claim 2, wherein the shank portions are each formed curving corresponding to a shape of an airfoil portion of the corresponding turbine rotor blade, and the shield member body is formed curved in a plane corresponding to side surfaces of the shank portions of the adjacent turbine rotor blades. ### Claim 8 (depends on 3) The shield member according to claim 3, wherein the shank portions are each formed curving corresponding to a shape of an airfoil portion of the corresponding turbine rotor blade, and the shield member body is formed curved in a plane corresponding to side surfaces of the shank portions of the adjacent turbine rotor blades. ### Claim 9 (depends on 4) The shield member according to claim 4, wherein the shank portions are each formed curving corresponding to a shape of an airfoil portion of the corresponding turbine rotor blade, and the shield member body is formed curved in a plane corresponding to side surfaces of the shank portions of the adjacent turbine rotor blades. ### Claim 10 (depends on 5) The shield member according to claim 5, wherein the shank portions are each formed curving corresponding to a shape of an airfoil portion of the corresponding turbine rotor blade, and the shield member body is formed curved in a plane corresponding to side surfaces of the shank portions of the adjacent turbine rotor blades. ### Claim 11 (depends on 2) The shield member according to claim 2, wherein the platform portions each include a platform portion body-side fitting groove provided to the inner surface of the platform portion body, and a front skirt-side fitting groove provided to the inner surface of the front skirt, the shield member body includes a shield member body-side fitting portion provided to a second end in the longitudinal direction of the shield member body, and configured to be fitted into the platform portion body-side fitting groove, and the leading edge-side shield portion includes a leading edge-side shield portion-side fitting portion provided to a second end in a longitudinal direction of the leading edge-side shield portion, and configured to be fitted into the front skirt-side fitting groove. ### Claim 12 (depends on 3) The shield member according to claim 3, wherein the platform portions each include a platform portion body-side fitting groove provided to the inner surface of the platform portion body, and a front skirt-side fitting groove provided to the inner surface of the front skirt, the shield member body includes a shield member body-side fitting portion provided to a second end in the longitudinal direction of the shield member body, and configured to be fitted into the platform portion body-side fitting groove, and the leading edge-side shield portion includes a leading edge-side shield portion-side fitting portion provided to a second end in a longitudinal direction of the leading edge-side shield portion, and configured to be fitted into the front skirt-side fitting groove. ### Claim 13 (depends on 4) The shield member according to claim 4, wherein the platform portion includes a front skirt-side fitting groove provided in the inner surface of the front skirt, and the leading edge-side shield portion includes a leading edge-side shield portion-side fitting portion provided to a second end in a longitudinal direction of the leading edge-side shield portion, and configured to be fitted into the front skirt-side fitting groove. ### Claim 14 (depends on 5) The shield member according to claim 5, wherein the platform portion includes a front skirt-side fitting groove provided in the inner surface of the front skirt, and the leading edge-side shield portion includes a leading edge-side shield portion-side fitting portion provided to a second end in a longitudinal direction of the leading edge-side shield portion, and configured to be fitted into the front skirt-side fitting groove. ### Claim 15 (depends on 6) The shield member according to claim 6, wherein the platform portion includes a front skirt-side fitting groove provided in the inner surface of the front skirt, and the leading edge-side shield portion includes a leading edge-side shield portion-side fitting portion provided to a second end in a longitudinal direction of the leading edge-side shield portion, and configured to be fitted into the front skirt-side fitting groove. ### Claim 16 (depends on 1) A jet engine comprising the shield member according to claim 1. ### Claim 17 (depends on 2) A jet engine comprising the shield member according to claim 2. ### Claim 18 (depends on 3) A jet engine comprising the shield member according to claim 3. ### Claim 19 (depends on 4) A jet engine comprising the shield member according to claim 4. ### Claim 20 (depends on 5) A jet engine comprising the shield member according to claim 5.