# US 2020/0400030 A1 · Turbomachine sealing system and turbomachine including the sealing system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2020/0400030 A1 - Document ID: US20200400030A1 - Status: Published application - Kind: A1 - Application number: 17/014,001 - Filed: 2020-09-08 - Published: 2020-12-24 - Earliest claimed: 2018-03-13 - Assignees: Nuovo Pignone Tecnologie Srl - Applicants: Nuovo Pignone Tecnologie - S.r.l. - Inventors: Luciano MEI; Marco BONCINELLI; Egidio PUCCI - Web page: https://patentgrep.com/patent/US20200400030A1 ## 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} - F16J 15/0887: {the sealing effect being obtained by elastic deformation of the packing} - F05D 2240/55: Seals - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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 sealing system is described for effecting a seal of a gap (G1; G2) in a turbomachine (1) between a first structural member (21; 23) and a second structural member (31). The sealing system includes a sealing apparatus comprising a sealing member (47; 77) comprising a first edge portion (49; 79) and a second edge portion (51; 81). The two edge portions are parallel to one another and the first edge portion (49; 79) forms a pivoting connection to the first structural member (21; 23). The first structural member (21; 23) further comprises a seat (55; 85) rotatably housing the first edge portion (49; 79) of the sealing member (47; 77). The second edge portion (51; 81) comprises a curved contact surface (51.1; 81.1), in sealing contact with a contact surface (67; 97) of the second structural member (31). Further disclosed herein is a gas turbine engine (1) with a combustor liner (31) and a sealing arrangement to seal a gap (G1; G2) between the combustor liner (31) and the turbine nozzles of the first turbine stage. ## Claims ### Claim 1 An apparatus (43; 45) for effecting a seal of a gap (G; G2) in a turbomachine (1) between a first structural member (21; 23) and a second structural member (31); the apparatus comprising a sealing member (47; 77) having a body comprising a first edge portion (49; 79) and a second edge portion (51; 81), parallel to one another; wherein the first edge portion (49; 79) forms a pivoting connection to the first structural member (21; 23); wherein the first structural member (21; 23) comprises a seat (55; 85) rotatably housing the first edge portion (49; 79) of the sealing member (47; 77); and wherein the second edge portion (51; 81) comprises a curved contact surface (51.1; 81.1), in sealing contact with a contact surface (67; 97) of the second structural member (31). ### Claim 2 (depends on 1) The apparatus (43; 45) of claim 1, further comprising a resilient member (61; 91), adapted to press the curved contact surface (51.1; 81.1) of the sealing member (47; 77) against the contact surface (67; 97) of the second structural member (31). ### Claim 3 (depends on 1) The apparatus (43; 45) of claim 1, wherein the contact surface (67; 97) of the second structural member (31) is a planar contact surface. ### Claim 4 (depends on 1) The apparatus (43; 45) of claim 1, wherein the first edge portion (49; 79) comprises a first cylindrical surface, said first cylindrical surface having an axis parallel to the first edge portion (49; 79). ### Claim 5 (depends on 1) The apparatus (43; 45) of claim 1, wherein the curved contact surface (51.1; 81.1) of the second edge portion (51; 81) comprises a second cylindrical surface having an axis parallel to the first edge portion (49; 79). ### Claim 6 (depends on 1) The apparatus (43; 45) of claim 1, wherein the first edge portion (49; 79) and the seat (55; 85) are adapted to co-act along at least a first line of sealing contact between the first edge portion and the seat. ### Claim 7 (depends on 1) The apparatus (43; 45) of claim 1, wherein the second edge portion (51; 81) and the contact surface (67; 97) of the second structural member (31) are adapted to co-act along at least a second straight line of sealing contact between the second edge portion and the contact surface. ### Claim 8 (depends on 1) The apparatus (43; 45) of claim 1, further comprising a restraining member (63), adapted to prevent or limit movement of the sealing member (47; 77) in the seat (55; 85) in a direction parallel to the first edge portion (49; 79). ### Claim 9 (depends on 1) The apparatus (43; 45) of claim 1, wherein the sealing member (47; 77) is substantially rigid. ### Claim 10 (depends on 1) A gas turbine (1) comprising: a casing (3); in said casing (3), at least one turbine stage comprised of a set of static nozzles (8) and a set of rotary blades (9); a combustor (5) and a combustor liner (31) extending from a forward end (31F) to an aft end (31A) thereof; an apparatus according to claim 1, sealing a gap between the combustor liner (31) and the stationary nozzles (8). ### Claim 11 (depends on 10) The gas turbine (1) of claim 10, wherein the combustor (5) is an annular combustor, and wherein the combustor liner (31) comprises an outer combustor liner portion (31.1) and an inner combustor liner portion (31.2). ### Claim 12 A sealing structure for sealing a gap (G; G2) between a combustor liner (31) and a surrounding structure of a gas turbine engine (1), comprising a plurality of sealing members (47; 77) arranged in an annular configuration; wherein each sealing member comprises a body having a first edge portion (49; 79) and a second edge portion (51; 81), parallel to one another; wherein the first edge portion (49; 79) forms a pivoting connection to the surrounding structure; wherein the surrounding structure comprises a seat (55; 85) rotatably housing the first edge portion (49; 79) of the sealing member (47; 77); and wherein the second edge portion (51; 81) comprises a curved contact surface (51.1; 81.1), in sliding contact with a contact surface (67; 97) of the combustor liner (31). ### Claim 13 (depends on 12) The sealing structure of claim 12, wherein each sealing member (47; 77) is provided with a resilient member (61; 91) adapted to press the curved contact surface (51.1; 81.1) of the sealing member (47; 77) against the contact surface (67; 97) of the combustor liner (31). ### Claim 14 (depends on 12) The sealing structure of claim 12, wherein the contact surface (67; 97) of the combustor liner (31) is planar. ### Claim 15 (depends on 12) The sealing structure of claim 12, wherein said surrounding structure comprises a set of stationary nozzles (8) of a gas turbine stage, fluidly coupled to the combustor liner (31). ### Claim 16 (depends on 12) The sealing structure of claim 12, further comprising a laminar sealing element (48) arranged between each pair of adjacent sealing members (47; 77).