# US 2017/0284218 A1 · Seal structure > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2017/0284218 A1 - Document ID: US20170284218A1 - Status: Published application - Kind: A1 - Application number: 15/507,436 - Filed: 2015-07-07 - Published: 2017-10-05 - Earliest claimed: 2014-09-26 - Assignees: Mitsubishi Hitachi Power Systems, Ltd. - Applicants: Mitsubishi Hitachi Power Systems, Ltd. - Inventors: Takahiro KONDO; Shinya HASHIMOTO; Kenta TANIGUCHI - Web page: https://patentgrep.com/patent/US20170284218A1 ## CPC - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 11/10: using sealing fluid, e.g. steam - F01D 25/12: Cooling - F02C 7/28: Arrangement of seals - F16J 15/162: {Special parts or details relating to lubrication or cooling of the sealing itself (F16J15/324, F16J15/3404, F16J15/40 take precedence)} - F16J 15/4476: {with radial path} - F01D 11/003: {by packing rings; Mechanical seals} - 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 2230/31: Layer deposition - F05D 2240/11: Shroud seal segments - F05D 2260/201: by impingement of a fluid - 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) - F16J: PISTONS {(specially adapted for dampers F16F9/32)}; CYLINDERS; SEALINGS - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A seal structure includes: a first member and a second member disposed so as to face a combustion gas flow passage; a third member disposed on the outer side of the combustion gas flow passage; a heat-resistant coating formed on at least one of a first end face and a second end face, on the side of the face closer to the combustion gas flow passage; and a contact part disposed in the first end face and the second end face, further on the outer side than the heat-resistant coating. When the first member and the second member move relatively toward each other, the contact part restricts the relative movement by coming in contact in a state where a clearance is left between the heat-resistant coating and the face facing the heat-resistant coating. ## Claims ### Claim at position 1 1-6. (canceled) ### Claim 7 A seal structure comprising: a first member disposed so as to face a combustion gas flow passage formed around a rotor axis; a second member disposed adjacent to the first member so as to face the combustion gas flow passage; a third member disposed on the outer side of the combustion gas flow passage between a first end face of the first member and a second end face of the second member facing the first end face, and engaging with the first member and the second member; a heat-resistant coating formed on at least one of the first end face and the second end face, on the side of the face closer to the combustion gas flow passage; and a contact part disposed in the first end face and the second end face, further on the outer side of the combustion gas flow passage than the heat-resistant coating, and, when the first member and the second member move relatively toward each other, restricting the relative movement by directly coming in contact with the first member and the second member, or indirectly coming in contact with the first member and the second member through the third member, in a state where a clearance is left between the heat-resistant coating and at least one of the first end face and the second end face facing the heat-resistant coating, wherein the first member is a combustor, wherein the second member is a vane disposed on the downstream side in a rotor axis direction relative to the combustor, wherein the third member is a seal member disposed on the outer side of the combustion gas flow passage, and wherein the seal member includes: cooling channels formed in a certain region extending in a circumferential direction based on the rotor axis, at positions including a position on the upstream side in the rotor axis direction relative to a leading edge of the vane facing the upstream side in the rotor axis direction; and a third end face having a plurality of openings which are provided in the circumferential direction and from which cooling air flowing through the cooling channels is discharged. ### Claim 8 (depends on 7) The seal structure according to claim 7 wherein the seal member includes a clearance forming portion that protrudes from the third end face toward the downstream side in the rotor axis direction and that has a fourth end face facing the downstream side in the rotor axis direction. ### Claim 9 (depends on 8) The seal structure according to claim 8, wherein the fourth end face is disposed so as to face the contact part of the second end face of the vane facing the upstream side in the rotor axis direction.