Patents by Inventor Alan Robert Maguire
Alan Robert Maguire 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: 9879603Abstract: This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.Type: GrantFiled: August 13, 2014Date of Patent: January 30, 2018Assignee: ROLLS-ROYCE plcInventors: Alan Robert Maguire, Timothy John Scanlon, Colin Young
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Patent number: 9777576Abstract: A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack. The first 62a and last 62c discs have the greatest axial separation of all discs 62a-c in the drum pack. The sealing body 84 engaging the first 62a and last 62c discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity 76 defined between the first 62a and last 62c discs, the drive arms 68 and the sealing body 84.Type: GrantFiled: December 3, 2013Date of Patent: October 3, 2017Assignee: ROLLS-ROYCE plcInventor: Alan Robert Maguire
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Patent number: 9658132Abstract: A method of determining the axial load on load-sharing thrust bearings including: providing first and second thrust bearings, each including an inner race and an outer race supported by at least one resilient element; applying a test axial load to each of the first and second thrust bearings to elastically deform the at least one resilient element so as to axially displace the outer race; determining the test axial displacement of each outer race to obtain calibration data comprising values of axial load versus axial displacement; applying an in-service axial load to the first and second thrust bearings to elastically deform the resilient elements so as to axially displace the respective outer races; measuring the in-service axial displacement of each outer race; and based on the measured in-service axial displacements, inferring from the calibration data the values of the in-service axial loads on the first and second thrust bearings.Type: GrantFiled: September 13, 2016Date of Patent: May 23, 2017Assignee: ROLLS-ROYCE plcInventors: Stephen Gallimore, Paul Fletcher, John Richard Webster, Alan Robert Maguire
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Patent number: 9546570Abstract: A bearing arrangement is disclosed. The bearing arrangement includes first and second bearings, with each bearing including a respective support element and a respective set of rolling elements and defining a respective load path extending through the respective support element and rolling elements. The support elements are coupled such that a load applied to either support element is transmitted through both the first and second load paths. The arrangement further includes a pair of superelastic titanium alloy elements located in the respective load paths to provide resilient movement between the bearings when a load is applied to the bearing arrangement.Type: GrantFiled: May 29, 2014Date of Patent: January 17, 2017Assignee: ROLLS-ROYCE plcInventors: Paul Fletcher, John Richard Webster, Alan Robert Maguire
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Publication number: 20170003196Abstract: A method of determining the axial load on load-sharing thrust bearings including: providing first and second thrust bearings, each including an inner race and an outer race supported by at least one resilient element; applying a test axial load to each of the first and second thrust bearings to elastically deform the at least one resilient element so as to axially displace the outer race; determining the test axial displacement of each outer race to obtain calibration data comprising values of axial load versus axial displacement; applying an in-service axial load to the first and second thrust bearings to elastically deform the resilient elements so as to axially displace the respective outer races; measuring the in-service axial displacement of each outer race; and based on the measured in-service axial displacements, inferring from the calibration data the values of the in-service axial loads on the first and second thrust bearings.Type: ApplicationFiled: September 13, 2016Publication date: January 5, 2017Applicant: ROLLS-ROYCE plcInventors: Stephen GALLIMORE, Paul FLETCHER, John Richard WEBSTER, Alan Robert MAGUIRE
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Patent number: 9470262Abstract: A bearing arrangement comprises: first and second thrust bearings, each including an inner race which is disposed on a shaft and an outer race which is supported by at least one resilient element. Applying a shaft thrust load elastically deforms the resilient elements so as to axially displace the respective outer races in order that the thrust load is shared between the first and second thrust bearings.Type: GrantFiled: February 25, 2015Date of Patent: October 18, 2016Assignee: ROLLS-ROYCE plcInventors: Stephen Gallimore, Paul Fletcher, John Richard Webster, Alan Robert Maguire
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Publication number: 20160258310Abstract: A turbine secondary air system seal arrangement (62). The arrangement comprises a first seal land (70) facing radially inwardly; a second seal land (80) facing radially outwardly; and first labyrinth seal teeth (76) directed radially outwardly to seal against the first seal land (70). Also second labyrinth seal teeth (78) directed radially inwardly to seal against the second seal land (80). The first seal land (70) is configured to move radially relative to the second seal land (80) or the first seal teeth (76) are configured to move radially relatively to the second seal teeth (78) to accommodate differential movement of the lands (70, 80) and teeth (76, 78) during use of the seal arrangement (62).Type: ApplicationFiled: February 18, 2016Publication date: September 8, 2016Applicant: ROLLS-ROYCE PLCInventors: Lynne Helen TURNER, Alan Robert MAGUIRE, Sean Alan WALTERS, Matthew Kieran DUNK
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Publication number: 20150267744Abstract: A bearing arrangement comprises: first and second thrust bearings, each including an inner race which is disposed on a shaft and an outer race which is supported by at least one resilient element. Applying a shaft thrust load elastically deforms the resilient elements so as to axially displace the respective outer races in order that the thrust load is shared between the first and second thrust bearings.Type: ApplicationFiled: February 25, 2015Publication date: September 24, 2015Inventors: Stephen GALLIMORE, Paul FLETCHER, John Richard WEBSTER, Alan Robert MAGUIRE
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Publication number: 20150047359Abstract: This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.Type: ApplicationFiled: August 13, 2014Publication date: February 19, 2015Inventors: Alan Robert MAGUIRE, Timothy John SCANLON, Colin YOUNG
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Publication number: 20140369830Abstract: A bearing arrangement is disclosed. The bearing arrangement includes first and second bearings, with each bearing including a respective support element and a respective set of rolling elements and defining a respective load path extending through the respective support element and rolling elements. The support elements are coupled such that a load applied to either support element is transmitted through both the first and second load paths. The arrangement further includes a pair of superelastic titanium alloy elements located in the respective load paths to provide resilient movement between the bearings when a load is applied to the bearing arrangement.Type: ApplicationFiled: May 29, 2014Publication date: December 18, 2014Applicant: ROLLS-ROYCE PLCInventors: Paul FLETCHER, John Richard WEBSTER, Alan Robert MAGUIRE
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Publication number: 20140169953Abstract: A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack. The first 62a and last 62c discs have the greatest axial separation of all discs 62a-c in the drum pack. The sealing body 84 engaging the first 62a and last 62c discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity 76 defined between the first 62a and last 62c discs, the drive arms 68 and the sealing body 84.Type: ApplicationFiled: December 3, 2013Publication date: June 19, 2014Applicant: ROLLS-ROYCE PLCInventor: Alan Robert MAGUIRE
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Publication number: 20100089019Abstract: A gas turbine engine having three shafts connecting respective high, intermediate and low-pressure turbines and compressors is characterised by an intermediate pressure turbine that includes two rotor stages.Type: ApplicationFiled: May 20, 2009Publication date: April 15, 2010Applicant: ROLLS-ROYCE PLCInventors: GLENN ALEXANDER KNIGHT, Martyn Richards, Mark David Taylor, Alan Robert Maguire