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US 11,028,706 B2Granted
Captured compliant coil seal
AssigneeROLLS-ROYCE plc
InventorKelly Jon McCormick
Life of this patent
Estimating the term…
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.
Claims20
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.
2 more elements
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.
1 more element
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.
2 more elements
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.
2 more elements
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.
1 more element
Dependencies are inferred from the claim text.