# US 11,028,706 B2 · Captured compliant coil seal > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,028,706 B2 - Document ID: US11028706B2 - Status: Granted - Kind: B2 - Application number: 16/285,327 - Filed: 2019-02-26 - Published: 2020-08-27 - Granted: 2021-06-08 - Earliest claimed: 2019-02-26 - Assignees: ROLLS-ROYCE plc - Applicants: Rolls-Royce Corporation - Inventors: Kelly Jon McCormick - Web page: https://patentgrep.com/patent/US11028706B2 ## 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} - F02C 7/28: Arrangement of seals - F23R 3/60: Support structures; Attaching or mounting means - F05D 2240/55: Seals - F05D 2250/75: given by its similarity to a letter, e.g. T-shaped - F05D 2260/36: by a form fit connection, e.g. by interlocking - F05D 2260/37: by a press fit connection - F05D 2260/38: by a spring, i.e. spring loaded or biased towards a certain position - F23R 2900/00012: Details of sealing devices - F23R 2900/00017: Assembling combustion chamber liners or subparts - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A combustor seal system for a gas turbine engine is provided that includes a rear inner discharge nozzle (RIDN) configured to engage a liner of a combustor. The system further includes a nozzle guide vane (NGV) positioned adjacent the RIDN. The NGV and the RIDN together define a cavity. The system further includes a seal in contact with the RIDN and positioned in the cavity. The seal curves along a surface of the cavity and contacts the RIDN at a first point and a second point in the cavity. The seal contacts the NGV at a third point. ## Claims ### Claim 1 A combustor seal system for a gas turbine engine, the system comprising: a rear inner discharge nozzle (RIDN) configured to engage a liner of a combustor; a nozzle guide vane (NGV) positioned adjacent the RIDN, wherein the NGV and the RIDN together define a cavity, wherein the NGV comprises an inner upstream edge relative to a primary flow path of the gas turbine, the inner upstream edge comprising a plurality of channels; and a seal in contact with the RIDN and positioned in the cavity, wherein the seal curves along a surface of the cavity and contacts the RIDN at a first point and a second point in the cavity, and the seal contacts the NGV at a third point wherein the seal comprises a plurality of contracted portions, a plurality of expanded portions, and a plurality of slots, each slot positioned between a respective one of the contracted portions and a respective one of the expanded portions, and wherein the expanded portions contact the plurality of channels. ### Claim 2 (depends on 1) The system of claim 1, wherein the seal extends along the inner upstream edge, and wherein the seal contacts the inner upstream edge of the NGV at the third point. ### Claim 3 (depends on 2) The system of claim 2, wherein the inner upstream edge of the NGV comprises at least one flat section, and wherein the slots are positioned adjacent opposite ends of the at least one flat section. ### Claim 4 (depends on 1) The system of claim 1, wherein the RIDN comprises an upstream portion and a downstream portion relative to the primary flow path of the gas turbine engine, wherein the downstream portion comprises a first side, a second side, and a third side, and wherein the seal extends along at least a portion of the first side, the second side, and the third side. ### Claim 5 (depends on 4) The system of claim 4, wherein the RIDN further comprises a tang positioned downstream of the third side relative to the primary flow path of the gas turbine engine, the tang including a first edge extending away from the third side and a second edge extending from the first edge toward the NGV, wherein the seal extends along the first edge. ### Claim 6 (depends on 5) The system of claim 5, wherein the seal comprises at least one tab extending radially outward from the seal along the first edge, and wherein the at least one tab extends along at least one side of the tang. ### Claim 7 (depends on 5) The system of claim 5, wherein the seal extends along the second edge, wherein the seal comprises at least one tab extending radially outward from the seal along the second edge, and where the at least one tab extends along at least one side of the tang. ### Claim 8 A combustor seal assembly for a gas turbine engine, the assembly comprising: a seal comprising a first end, a second end, and a seal body extending between the first end and the second end; a rear inner discharge nozzle (RIDN) comprising an upstream portion and a downstream portion relative to a primary flow path of the gas turbine engine, wherein the downstream portion comprises a tang positioned downstream an attachment pin, wherein the seal extends along the tang, and wherein the attachment pin contacts the seal; and a nozzle guide vane (NGV), wherein the NGV is positioned adjacent the RIDN, the RIDN and the NGV together defining a cavity, wherein the seal is positioned in the cavity, wherein the seal curves along a surface of the cavity, wherein the seal contacts the upstream portion of the RIDN at a first point and a second point, and the seal contacts the NGV at a third point. ### Claim 9 (depends on 8) The assembly of claim 8, wherein the seal body is configured to bend, causing a distance between the second end of the seal and the first point to change. ### Claim 10 (depends on 8) The assembly of claim 8, wherein the seal body comprises a first portion, wherein the first portion is curved. ### Claim 11 (depends on 10) The assembly of claim 10, wherein the seal body further comprises a second portion, wherein the second portion extends along the downstream portion of the RIDN. ### Claim 12 (depends on 11) The assembly of claim 11, further comprising a flap seal positioned between the downstream portion of the RIDN and the NGV, wherein the attachment pin couples the flap seal to the NGV, and wherein the flap seal contacts the NGV and the seal. ### Claim 13 (depends on 8) The assembly of claim 8, wherein the NGV comprises an inner upstream edge relative to the primary flow path of the gas turbine engine, wherein the inner upstream edge includes a plurality of flat sections, wherein the seal includes a plurality of slots, wherein a first slot of the plurality of slots is positioned adjacent a point between two adjacent flat sections of the plurality of flat sections and between, and wherein a second slot of the plurality of slots is positioned adjacent a point between two adjacent segments of the NGV. ### Claim 14 A method of assembly of a combustor seal system, the method comprising: providing a rear inner discharge nozzle (RIDN), the RIDN comprising an upstream portion and a downstream portion relative to a primary flow path of a gas turbine engine; positioning a seal on the RIDN, the seal comprising a first end, a second end, and a seal body extending between the first end and the second end; positioning a nozzle guide vane (NGV) and the RIDN adjacent to each other, the RIDN and the NGV together defining a cavity, wherein the seal is positioned in the cavity and curves along a surface of the cavity, wherein the seal contacts the upstream portion of the RIDN at a first point and a second point, and wherein the seal contacts the NGV at a third point; and attaching a flap seal and an overlap seal to the NGV with an attachment pin, wherein the flap seal contacts the NGV and the seal. ### Claim 15 (depends on 14) The method of claim 14, wherein the positioning the seal on the RIDN further comprises attaching the seal to the RIDN at the first point. ### Claim 16 (depends on 14) The method of claim 14, wherein the downstream portion of the RIDN further comprises a tang, wherein the seal extends along the downstream portion of the RIDN, and wherein the positioning the seal on the RIDN further comprises attaching the seal to the downstream portion of the RIDN. ### Claim 17 (depends on 16) The method of claim 16 wherein the seal extends along a portion of the tang between the tang and the attachment pin, wherein the flap seal includes a first flap seal segment and a second flap seal segment, and wherein the overlap seal is positioned to contact the first and second flap seal segments downstream of the flap seal. ### Claim 18 (depends on 16) The method of claim 16, wherein the seal comprises a tab extending from a downstream portion of the seal, wherein the tab contacts the tang, wherein the tabs are configured to hold the seal in place during the positioning of the seal on the RIDN. ### Claim 19 A combustor seal assembly for a gas turbine engine, the assembly comprising: a seal comprising a first end, a second end, and a seal body extending between the first end and the second end; a rear inner discharge nozzle (RIDN) comprising an upstream portion and a downstream portion relative to a primary flow path of the gas turbine engine; and a nozzle guide vane (NGV), wherein the NGV is positioned adjacent the RIDN, the RIDN and the NGV together defining a cavity, wherein the seal is positioned in the cavity, wherein the seal curves along a surface of the cavity, wherein the seal contacts the upstream portion of the RIDN at a first point and a second point, and the seal contacts the NGV at a third point, and wherein the NGV comprises an inner upstream edge relative to the primary flow path of the gas turbine engine, wherein the inner upstream edge includes a plurality of flat sections, wherein the seal includes a plurality of slots, wherein a first slot of the plurality of slots is positioned adjacent a point between two adjacent flat sections of the plurality of flat sections and between, and wherein a second slot of the plurality of slots is positioned adjacent a point between two adjacent segments of the NGV. ### Claim 20 A method of assembly of a combustor seal system, the method comprising: providing a rear inner discharge nozzle (RIDN), the RIDN comprising an upstream portion and a downstream portion relative to a primary flow path of a gas turbine engine; positioning a seal on the RIDN, the seal comprising a first end, a second end, and a seal body extending between the first end and the second end, wherein the seal comprises a tab extending from a downstream portion of the seal, wherein the tab contacts a tang, wherein the tab is configured to hold the seal in place during the positioning of the seal on the RIDN; and positioning a nozzle guide vane (NGV) and the RIDN adjacent to each other, the RIDN and the NGV together defining a cavity, wherein the seal is positioned in the cavity and curves along a surface of the cavity, wherein the seal contacts the upstream portion of the RIDN at a first point and a second point, and wherein the seal contacts the NGV at a third point.