Patents by Inventor Simon Lloyd JONES
Simon Lloyd JONES has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11578624Abstract: The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid supply channel (74) configured to direct a second working fluid to impart torque on the turbine rotor (60) in the same direction as the direction in which torque is imparted on the turbine rotor (60) by the first working fluid. The first working fluid is an exhaust gas from an internal combustion engine and the second fluid may be steam and the turbine may be an inverted-Brayton-cycle turbine for recovery of waste energy from the exhaust gas of said internal combustion engine. Thus, the number of turbine rotors is reduced in comparison to a system comprising a single turbine for each distinct working fluid.Type: GrantFiled: April 28, 2018Date of Patent: February 14, 2023Assignee: HIETA TECHNOLOGIES LIMITEDInventors: Colin Douglas Copeland, Robert Ceen, Simon Lloyd Jones, Andrew Robert Jones
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Patent number: 11560846Abstract: A combined heat and power system comprises a shaft (4), a compressor (6) coupled to the shaft to compress intake gas to form compressed gas; a recuperator (10) to heat the compressed gas to form heated compressed gas; a combustor (12) to combust a fuel and the heated compressed gas to form combustion gas; a turbine (8) coupled to the shaft to expand the combustion gas to form exhaust gas; a load (24) coupled to the shaft; an exhaust outlet (18) to expel the exhaust gas to a heater for heating a fluid based on heat from the exhaust gas; a recuperator channel (28) providing a path for the exhaust gas to flow from the turbine to the exhaust outlet through the recuperator; and a bypass channel (22) providing a path for the exhaust gas to flow from the turbine to the exhaust outlet bypassing the recuperator.Type: GrantFiled: February 12, 2019Date of Patent: January 24, 2023Assignee: HiETA Technologies LimitedInventor: Simon Lloyd Jones
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Patent number: 11543129Abstract: A combined combustor and recuperator is formed with the recuperator surrounding the combustor. Cold gas conduits (14, 16, 20) through the recuperator follow along involute paths toward the combustor. Hot has conduits (26) through the recuperator follow counterflow paths along corresponding involute curves outward from the combustor. The openings (18) in the combustion chamber wall through which cold gas enters the combustion chamber may be directed to impart flow direct to the cold gas to support particular desired behaviour of the cold gas in the portions of the combustion chamber concerned, e.g. supporting a stable vortex flame, enhancing mixing, providing a protective barrier layer.Type: GrantFiled: August 14, 2017Date of Patent: January 3, 2023Assignee: HIETA TECHNOLOGIES LIMITEDInventors: Simon Lloyd Jones, Calum Smith
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Patent number: 11340020Abstract: A heat exchanger component comprises a core portion with alternating first and second heat exchanging channels. A first ducting portion comprises first ducting channels for transfer a first fluid between a first fluid inlet/outlet and the first heat exchanging channels of the core portion, and second ducting channels for transfer of second fluid between a second fluid inlet/outlet and the second heat exchanging channels of the core portion. The first ducting channels direct the first fluid around the turn of at least 45 degrees and the second ducting channels direct the second fluid around a turn of at least 90 degrees. The first and second ducting channels are interleaved.Type: GrantFiled: January 12, 2018Date of Patent: May 24, 2022Assignee: HIETA TECHNOLOGIES LIMITEDInventors: Niall Edward Hatfield, Simon Lloyd Jones
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Publication number: 20210156308Abstract: A combined heat and power system comprises a shaft (4), a compressor (6) coupled to the shaft to compress intake gas to form compressed gas; a recuperator (10) to heat the compressed gas to form heated compressed gas; a combustor (12) to combust a fuel and the heated compressed gas to form combustion gas; a turbine (8) coupled to the shaft to expand the combustion gas to form exhaust gas; a load (24) coupled to the shaft; an exhaust outlet (18) to expel the exhaust gas to a heater for heating a fluid based on heat from the exhaust gas; a recuperator channel (28) providing a path for the exhaust gas to flow from the turbine to the exhaust outlet through the recuperator; and a bypass channel (22) providing a path for the exhaust gas to flow from the turbine to the exhaust outlet bypassing the recuperator.Type: ApplicationFiled: February 12, 2019Publication date: May 27, 2021Inventor: Simon Lloyd JONES
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Patent number: 10808614Abstract: A radial flow turbine heat engine includes a compressor, a recuperator, a combustor and a turbine. A compressor outlet manifold collects compressed gas from the compressor through a plurality of compressor outlets. A turbine inlet manifold supplies combustion gas to the turbine through a plurality of turbine inlets. The compressor outlet manifold comprises a plurality of compressor outlet manifold ducts and the turbine inlet manifold comprises a plurality of turbine inlet manifold ducts. These manifold ducts are circumferentially interdigitated with respect of each other around the shaft of the turbine to provide a flow path for compressed gas through the recuperator located radially inwardly with respect to the rotation axis of the shaft compared to the flow path for the combustion gas in the hot side portion of the heat engine.Type: GrantFiled: March 24, 2017Date of Patent: October 20, 2020Assignee: HiETA Technologies LimitedInventors: Simon Lloyd Jones, Drummond Watson Hislop, Keith Robert Pullen
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Publication number: 20200263568Abstract: The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid supply channel (74) configured to direct a second working fluid to impart torque on the turbine rotor (60) in the same direction as the direction in which torque is imparted on the turbine rotor (60) by the first working fluid. The first working fluid is an exhaust gas from an internal combustion engine and the second fluid may be steam and the turbine may be an inverted-Brayton-cycle turbine for recovery of waste energy from the exhaust gas of said internal combustion engine. Thus, the number of turbine rotors is reduced in comparison to a system comprising a single turbine for each distinct working fluid.Type: ApplicationFiled: April 28, 2018Publication date: August 20, 2020Inventors: Colin Douglas COPELAND, Robert CEEN, Simon Lloyd JONES, Andrew Robert JONES
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Publication number: 20200263932Abstract: A heat exchanger component comprises a core portion with alternating first and second heat exchanging channels. A first ducting portion comprises first ducting channels for transfer a first fluid between a first fluid inlet/outlet and the first heat exchanging channels of the core portion, and second ducting channels for transfer of second fluid between a second fluid inlet/outlet and the second heat exchanging channels of the core portion. The first ducting channels direct the first fluid around the turn of at least 45 degrees and the second ducting channels direct the second fluid around a turn of at least 90 degrees. The first and second ducting channels are interleaved.Type: ApplicationFiled: January 12, 2018Publication date: August 20, 2020Inventors: Niall Edward HATFIELD, Simon Lloyd JONES
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Publication number: 20200025379Abstract: A combined combustor and recuperator is formed with the recuperator surrounding the combustor. Cold gas conduits (14, 16, 20) through the recuperator follow along involute paths toward the combustor. Hot has conduits (26) through the recuperator follow counterflow paths along corresponding involute curves outward from the combustor. The openings (18) in the combustion chamber wall through which cold gas enters the combustion chamber may be directed to impart flow direct to the cold gas to support particular desired behaviour of the cold gas in the portions of the combustion chamber concerned, e.g. supporting a stable vortex flame, enhancing mixing, providing a protective barrier layer.Type: ApplicationFiled: August 14, 2017Publication date: January 23, 2020Applicant: Hieta Technologies LimitedInventors: Simon Lloyd JONES, Calum SMITH
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Publication number: 20190292984Abstract: A radial flow turbine heat engine includes a compressor, a recuperator, a combustor and a turbine. A compressor outlet manifold collects compressed gas from the compressor through a plurality of compressor outlets. A turbine inlet manifold supplies combustion gas to the turbine through a plurality of turbine inlets. The compressor outlet manifold comprises a plurality of compressor outlet manifold ducts and the turbine inlet manifold comprises a plurality of turbine inlet manifold ducts. These manifold ducts are circumferentially interdigitated with respect of each other around the shaft of the turbine to provide a flow path for compressed gas through the recuperator located radially inwardly with respect to the rotation axis of the shaft compared to the flow path for the combustion gas in the hot side portion of the heat engine.Type: ApplicationFiled: March 24, 2017Publication date: September 26, 2019Inventors: Simon Lloyd JONES, Drummond Watson HISLOP, Keith Robert PULLEN
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Patent number: 10208617Abstract: A carrier segment of a carrier section for circumscribing an array of circumferentially spaced turbine blades of a gas turbine engine, the blades being disposed radially inwardly of a turbine casing, the carrier segment including a carrier wall disposed radially inwardly of the casing and radially outwardly of the turbine blades, and the carrier wall including one or more portions facing the casing, wherein at least one of the one or more portions of the carrier wall is provided with one or more impingement apertures therein for passage therethrough of air of a predetermined temperature, heating air, from a feed source into impingement onto the turbine casing. The application of heating air onto the casing during transient stages of enhanced engine power, e.g. during step climbs, results in better matching of radial expansion of the casing relative to the turbine blades, thereby enabling improved blade tip clearance control.Type: GrantFiled: December 14, 2015Date of Patent: February 19, 2019Assignee: ROLLS-ROYCE plcInventors: Simon Lloyd Jones, Leo V. Lewis
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Patent number: 10119413Abstract: An engine includes circumferentially spaced turbine blades radially inward a casing and circumscribed by a carrier section having segments, each having a carrier wall radially inward the casing and radially outward the turbine blades. The wall has one or more portions facing the casing. At least one of the portions has one or more impingement apertures for air passage of a predetermined temperature from a feed source into impingement onto the casing. The segments are radially inward the casing and radially outward the turbine blades, with the portions of their respective walls facing the casing. A method of controlling the gas turbine engine turbine casing temperature includes: passing air of a predetermined temperature from a feed source through the apertures in the one or more portions and into impingement on the casing; and optionally exhausting the air impinged onto the casing from a space between the segment and the casing.Type: GrantFiled: December 14, 2015Date of Patent: November 6, 2018Assignee: ROLLS-ROYCE plcInventor: Simon Lloyd Jones
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Patent number: 10099277Abstract: There is described a core for an investment casting process, comprising: a core passage which extends between a first point and a second point along a tortuous path having length L, wherein the first point and second point are separated by a direct line of sight distance, S, wherein L is greater than S; and, a core bridge which extends between the first and second points away from the core passage.Type: GrantFiled: February 23, 2016Date of Patent: October 16, 2018Assignee: ROLLS-ROYCE plcInventors: Simon Lloyd Jones, Mark John Simms
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Patent number: 9920647Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.Type: GrantFiled: May 12, 2014Date of Patent: March 20, 2018Assignee: ROLLS-ROYCE plcInventors: Simon Lloyd Jones, Rupert John Taylor, Julian Glyn Balsdon
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Patent number: 9752780Abstract: Described is an abradable component for a gas turbine engine that includes a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon. The walls intersect one another to define an abradable network of open faced cells on a gas washed surface thereof, and at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use.Type: GrantFiled: June 19, 2014Date of Patent: September 5, 2017Assignee: ROLLS-ROYCE plcInventors: Simon Lloyd Jones, Kevin Paul Self, Mark John Simms
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Patent number: 9689273Abstract: Described is a shroud arrangement for a gas turbine engine, comprising: a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a casing of the engine via at least one fore attachment and at least one aft attachment, the fore and aft attachment restricting radial movement of the seal segment relative to the engine casing; and, an axial restrictor which prevents axial movement of the seal segment relative to the engine casing, the axis being the principal rotational axis of the engine, wherein the fore and aft retention features are slidably engaged with a carrier segment or engine casing from a common direction. Also described is a gas turbine engine having the shroud arrangement.Type: GrantFiled: May 12, 2014Date of Patent: June 27, 2017Assignee: ROLLS-ROYCE plcInventors: Simon Lloyd Jones, Mark John Simms
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Patent number: 9677412Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine.Type: GrantFiled: May 12, 2014Date of Patent: June 13, 2017Assignee: ROLLS-ROYCE plcInventors: Simon Lloyd Jones, Mark John Simms
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Publication number: 20160332259Abstract: A method for providing a component, the method comprising; defining the geometry of the component, defining a second geometry which incorporates a component geometry portion (1) and a sacrificial geometry portion (2) and using an ALM method, manufacturing an intermediate (1,2) having the second geometry. Prior to removal of the sacrificial geometry portion, a heat treatment is applied to the intermediate.Type: ApplicationFiled: April 22, 2016Publication date: November 17, 2016Applicant: ROLLS-ROYCE plcInventors: Simon Lloyd JONES, Julian Charles MASON-FLUCKE, Nunzio Maria Andrea PALUMBO, Benjamin Charles SAUNDERS, Rhys Owen MANSELL, Kevin Augustine LONG
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Publication number: 20160256919Abstract: There is described a core for an investment casting process, comprising: a core passage which extends between a first point and a second point along a tortuous path having length L, wherein the first point and second point are separated by a direct line of sight distance, S, wherein L is greater than S; and, a core bridge which extends between the first and second points away from the core passage.Type: ApplicationFiled: February 23, 2016Publication date: September 8, 2016Applicant: ROLLS-ROYCE PLCInventors: Simon Lloyd JONES, Mark John SIMMS
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Publication number: 20160169026Abstract: An engine includes circumferentially spaced turbine blades radially inward a casing and circumscribed by a carrier section having segments, each having a carrier wall radially inward the casing and radially outward the turbine blades. The wall has one or more portions facing the casing. At least one of the portions has one or more impingement apertures for air passage of a predetermined temperature from a feed source into impingement onto the casing. The segments are radially inward the casing and radially outward the turbine blades, with the portions of their respective walls facing the casing. A method of controlling the gas turbine engine turbine casing temperature includes: passing air of a predetermined temperature from a feed source through the apertures in the one or more portions and into impingement on the casing; and optionally exhausting the air impinged onto the casing from a space between the segment and the casing.Type: ApplicationFiled: December 14, 2015Publication date: June 16, 2016Applicant: ROLLS-ROYCE plcInventor: Simon Lloyd JONES