# US 2019/0170352 A1 · Combustion chamber arrangement > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0170352 A1 - Document ID: US20190170352A1 - Status: Published application - Kind: A1 - Application number: 16/187,022 - Filed: 2018-11-12 - Published: 2019-06-06 - Earliest claimed: 2017-12-05 - Assignees: ROLLS-ROYCE plc - Applicants: ROLLS-ROYCE plc - Inventors: David P. WILSON; John E. RIMMER; Damian MARTIN - Web page: https://patentgrep.com/patent/US20190170352A1 ## CPC - F23R 3/06: Arrangement of apertures along the flame tube - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F23R 3/005: {Combined with pressure or heat exchangers} - F23R 3/007: {constructed mainly of ceramic components} - F23R 3/48: Flame tube interconnectors, e.g. cross-over tubes - F05D 2210/12: gaseous, i.e. compressible - F05D 2210/43: Radial inlet and axial outlet - F05D 2220/32: in gas turbines - F05D 2240/35: Combustors or associated equipment - F05D 2300/20: Oxide or non-oxide ceramics - F23R 2900/03042: Film cooled combustion chamber walls or domes - F23R 2900/03043: Convection cooled combustion chamber walls with means for guiding the cooling air flow - F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies - 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) - 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 combustion chamber arrangement comprises an annular combustion chamber, a plurality of circumferentially arranged vanes and a radially inner sealing ring. The vanes are arranged at the axially downstream end of the annular combustion chamber. Each of the vanes comprises an aerofoil extending radially between a radially inner platform and a radially outer platform. The radially inner sealing ring forms a seal between a downstream end of a radially inner annular wall structure of the combustion chamber and the radially inner platforms of the vanes. A portion of the axial length of the radially inner sealing ring comprises a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define a chamber. The radially inner wall has apertures to supply coolant into the chamber and the radially outer wall has effusion cooling apertures to supply coolant onto the surface of the radially outer wall. ## Claims ### Claim 1 A combustion chamber arrangement comprising an annular combustion chamber, a plurality of circumferentially arranged vanes, a radially inner sealing ring and a radially outer sealing ring, the annular combustion chamber comprising a radially inner annular wall structure, a radially outer annular wall structure spaced radially outwardly from the radially inner annular wall structure and an axially upstream annular wall structure, an upstream end of the radially inner annular wall structure being secured to a radially inner end of the axially upstream annular wall structure and an upstream end of the radially outer annular wall structure being secured to a radially outer end of the axially upstream annular wall structure, the vanes being arranged at the axially downstream end of the annular combustion chamber, each of the vanes comprising a radially inner platform, a radially outer platform and an aerofoil extending radially between the radially inner platform and the radially outer platform, the radially inner sealing ring being arranged to form a seal between a downstream end of the radially inner annular wall structure and the radially inner platforms of the vanes and the radially outer sealing ring being arranged to form a seal between a downstream end of the radially outer annular wall structure and the radially outer platforms of the vanes, at least a portion of the axial length of the radially inner sealing ring comprising a dual wall structure, the dual wall structure including a radially inner wall and a radially outer wall spaced radially from the radially inner wall to define at least one chamber, the radially inner wall having a plurality of apertures to supply coolant into the at least one chamber and the radially outer wall having a radially outer surface and a plurality of effusion cooling apertures to supply coolant from the at least one chamber onto the radially outer surface of the radially outer wall. ### Claim 2 (depends on 1) A combustion chamber arrangement as claimed in claim 1 wherein the radially inner wall and the radially outer wall are parallel. ### Claim 3 (depends on 1) A combustion chamber arrangement as claimed in claim 1, wherein an upstream end of the radially inner sealing ring having an annular circumferentially and axially extending slot arranged to receive an annular axially extending member at the downstream end of the radially outer annular wall structure, and a downstream end of the radially inner sealing ring having an annular circumferentially and radially extending slot arranged to receive radially extending members at the upstream ends of the radially inner platforms of the vanes. ### Claim 4 (depends on 1) A combustion chamber arrangement as claimed in claim 1, wherein the downstream end of the radially inner sealing ring being at a greater radius than the upstream end of the radially inner sealing ring. ### Claim 5 (depends on 1) A combustion chamber arrangement as claimed in claim 1, wherein the dual wall structure extends the full axial length of the radially inner sealing ring. ### Claim 6 (depends on 1) A combustion chamber arrangement as claimed in claim 1, wherein the radially inner wall of the dual wall structure comprising a ring and the radially outer wall comprising a plurality of circumferentially arranged tiles secured on the ring. ### Claim 7 (depends on 6) A combustion chamber arrangement as claimed in claim 6, wherein the tiles extend the full length of the radially inner wall of the dual wall structure. ### Claim 8 (depends on 6) A combustion chamber arrangement as claimed in claim 6, wherein an upstream end of the radially inner wall of the dual wall structure has an annular circumferentially and axially extending slot arranged to receive an annular axially extending member at the downstream end of the radially outer annular wall structure, and a downstream end of the radially inner wall of the dual wall structure has an annular circumferentially and radially extending slot arranged to receive radially extending members at the upstream ends of the radially inner platforms of the vanes. ### Claim 9 (depends on 6) A combustion chamber arrangement as claimed in claim 6, wherein each tile is secured to the ring by at least one fastener arrangement. ### Claim 10 (depends on 1) A combustion chamber arrangement as claimed in claim 1, wherein the radially outer wall of the dual wall structure comprises a ring and the radially inner wall comprises at least one member secured on the ring. ### Claim 11 (depends on 10) A combustion chamber arrangement as claimed in claim 10, wherein an upstream end of the radially outer wall of the dual wall structure has an annular circumferentially and axially extending slot arranged to receive an annular axially extending member at the downstream end of the radially outer annular wall structure, and a downstream end of the radially outer wall of the dual wall structure has an annular circumferentially and radially extending slot arranged to receive radially extending members at the upstream ends of the radially inner platforms of the vanes. ### Claim 12 (depends on 11) A combustion chamber arrangement as claimed in claim 11, wherein an upstream end of the at least one member is secured to a structure defining the annular circumferentially and axially extending slot and a downstream end of the at least one member is secured to a structure defining the annular circumferentially and radially extending slot to define a single chamber. ### Claim 13 (depends on 10) A combustion chamber arrangement as claimed in claim 10, wherein a plurality of members are secured to the ring to define a plurality of chambers and at least one of the members has apertures to supply coolant into one of the chambers. ### Claim 14 (depends on 1) A combustion chamber arrangement as claimed in claim 1, wherein the radially outer wall and the radially inner wall of the dual wall structure are an integral structure, a single piece, a unitary piece or a monolithic piece. ### Claim 15 (depends on 14) A combustion chamber arrangement as claimed in claim 14, wherein the radially inner sealing ring comprises a plurality of circumferentially arranged segments, at least a portion of the axial length of each of the segments comprising a dual wall structure, the radially outer wall and the radially inner wall of the dual wall structure of each segment is an integral structure, a single piece, a unitary piece or a monolithic piece. ### Claim 16 (depends on 15) A combustion chamber arrangement as claimed in claim 15, wherein each segment has at least one chamber. ### Claim 17 (depends on 15) A combustion chamber arrangement as claimed in claim 15, wherein each segment has circumferential ends and the circumferential end of each segment has interlocking features to enable adjacent segments to be secured together. ### Claim 18 (depends on 15) A combustion chamber arrangement as claimed in claim 15, wherein an upstream end of each segment has a part annular circumferentially and axially extending slot arranged to receive an annular axially extending member at the downstream end of the radially outer annular wall structure, and a downstream end of the each segment has a part annular circumferentially and radially extending slot arranged to receive radially extending members at the upstream ends of the radially inner platforms of the vanes. ### Claim 19 (depends on 15) A combustion chamber arrangement as claimed in claim 15, wherein each segment has a single chamber arranged at the upstream end of the segment, and each segment has a single wall structure downstream of the upstream end of the segment. ### Claim 20 (depends on 15) A combustion chamber arrangement as claimed in claim 15, wherein each segment has two axially spaced chambers, there is a single wall structure between the two axially spaced chambers, and there are ballistic cooling apertures in the single wall structure. ### Claim 21 (depends on 15) A combustion chamber arrangement as claimed in claim 15, wherein each segment has two axially spaced chambers, there is a single wall structure between the two axially spaced chambers, the single wall structure is set back from a frustoconical radially outer surface to form an annular recess. ### Claim 22 (depends on 21) A combustion chamber arrangement as claimed in claim 21, wherein each segment has a radial wall to define an upstream chamber upstream of the single wall structure and a radially inner wall parallel to the radially outer wall to define a downstream chamber, each segment has at least one aperture to supply coolant into the annular recess and over the frustoconical radially outer surface, the upstream end of the downstream chamber of each segment defines an inlet to the downstream chamber and the radially inner wall is imperforate. ### Claim 23 (depends on 22) A combustion chamber arrangement as claimed in claim 22, wherein the downstream chamber of each segment has a plurality of pedestals. ### Claim 24 (depends on 15) A combustion chamber arrangement as claimed in claim 15, wherein the radially outer wall has a first frustoconical radially outer surface, a second frustoconical radially outer surface parallel to and downstream of the first frustoconical radially outer surface, a radial surface from the upstream end of the second frustoconical radially outer surface to the downstream end of the first frustoconical radially outer surface and the downstream end of the first frustoconical radially outer surface is spaced radially inwardly of the upstream end of the second frustoconical radially outer surface, at least one aperture is arranged in the radial surface to direct coolant over the second frustoconical radially outer surface. ### Claim 25 (depends on 24) A combustion chamber arrangement as claimed in claim 24, wherein each segment has a single chamber arranged at the upstream end of the segment, each segment has a single wall structure downstream of the upstream end of the segment, the single chamber is arranged to supply coolant through the at least one aperture in the radial surface over the second frustoconical radially outer surface. ### Claim 26 (depends on 24) A combustion chamber arrangement as claimed in claim 24, wherein each segment has three axially spaced chambers, there is a single wall structure between a middle chamber and a downstream chamber of the three axially spaced chambers, there are ballistic cooling apertures in the single wall structure, the at least one aperture in the radial surface is arranged to direct coolant over a portion of the radially outer wall defining the middle chamber and downstream chamber.