Patents by Inventor Cathal Clancy
Cathal Clancy 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: 11473594Abstract: A compressor has a rotor assembly having an impeller for generating an airflow through the compressor, a stator core assembly for causing rotation of the impeller, and a diffuser assembly for acting on the airflow generated by the impeller. The diffuser assembly has a first diffuser stage and a second diffuser stage. The first and second diffuser stages are separate components connected to one another by a fastener.Type: GrantFiled: March 12, 2019Date of Patent: October 18, 2022Assignee: Dyson Technology LimitedInventors: Mark Andrew Johnson, Simon Alexander Locke, Matthew John Childe, Cathal Clancy, Vadivel Kumaran Sivashanmugam, Nora Er-Rouhly, Lukasz Andrzej Kowalczyk, Alan Glynn Sanderson, Thomas Richard Stafford, Sarah Elizabeth Elson, Alexander Thomas Wells, Jim Ray Lluisma
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Publication number: 20210207617Abstract: A compressor has a rotor assembly having an impeller for generating an airflow through the compressor, a stator core assembly for causing rotation of the impeller, and a diffuser assembly for acting on the airflow generated by the impeller. The diffuser assembly has a first diffuser stage and a second diffuser stage. The first and second diffuser stages are separate components connected to one another by a fastener.Type: ApplicationFiled: March 12, 2019Publication date: July 8, 2021Applicant: Dyson Technology LimitedInventors: Mark Andrew JOHNSON, Simon Alexander LOCKE, Matthew John CHILDE, Cathal CLANCY, Vadivel Kumaran SIVASHANMUGAM, Nora ER-ROUHLY, Lukasz Andrzej KOWALCZYK, Alan Glynn SANDERSON, Thomas Richard STAFFORD, Sarah Elizabeth ELSON, Alexander Thomas WELLS, Jim Ray LLUISMA
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Patent number: 10125687Abstract: A turbine engine assembly includes a core compressor configured to discharge a first airflow at a first temperature and a first pressure. The turbine engine assembly also includes a cooling system turbine configured to receive the first airflow at the first temperature and the first pressure and discharge a second airflow at a second pressure less than the first pressure. The turbine engine assembly further includes a heat exchanger configured to receive the second airflow and discharge a third airflow at a second temperature less than the first temperature. The turbine engine assembly also includes a cooling system compressor rotatably coupled to the cooling system turbine. The cooling system compressor is configured to receive the third airflow and discharge a fourth airflow at a third pressure greater than the first pressure.Type: GrantFiled: February 29, 2016Date of Patent: November 13, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Florian Stefan Hoefler, Cathal Clancy, Andrew Maxwell Peter
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Publication number: 20170248079Abstract: A turbine engine assembly includes a core compressor configured to discharge a first airflow at a first temperature and a first pressure. The turbine engine assembly also includes a cooling system turbine configured to receive the first airflow at the first temperature and the first pressure and discharge a second airflow at a second pressure less than the first pressure. The turbine engine assembly further includes a heat exchanger configured to receive the second airflow and discharge a third airflow at a second temperature less than the first temperature. The turbine engine assembly also includes a cooling system compressor rotatably coupled to the cooling system turbine. The cooling system compressor is configured to receive the third airflow and discharge a fourth airflow at a third pressure greater than the first pressure.Type: ApplicationFiled: February 29, 2016Publication date: August 31, 2017Inventors: Florian Stefan Hoefler, Cathal Clancy, Andrew Maxwell Peter
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Patent number: 9500122Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.Type: GrantFiled: June 28, 2013Date of Patent: November 22, 2016Assignee: General Electric CompanyInventors: Cathal Clancy, Daniel Edward Loringer, Rodrigo Rodriguez Erdmenger, Vittorio Michelassi
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Patent number: 8925317Abstract: An exemplary turbocharger system for an internal combustion engine is provided. The turbocharger system includes a first turbine and a second turbine. The first turbine is in fluid communication with the internal combustion engine. The first turbine receives a first portion exhaust gas discharged from the internal combustion engine and provides a first turbine exhaust gas. The second turbine is in fluid communication with the first turbine via an inter-stage channel. The inter-stage channel transports the first turbine exhaust gas from the first turbine to the second turbine. The inter-stage channel is in thermal connection with an exhaust gas recirculation channel defined between an inlet and an outlet of the internal combustion engine. The first turbine exhaust gas flowing through the inter-stage channel is capable of being heated by a second portion exhaust gas discharged from the internal combustion engine and flowing through the exhaust gas recirculation channel.Type: GrantFiled: July 16, 2012Date of Patent: January 6, 2015Assignee: General Electric CompanyInventors: Rodrigo Rodriguez Erdmenger, Cathal Clancy, Daniel Edward Loringer, Jassin Marcel Fritz, Neil Xavier Blythe, Lukas William Johnson, Sebastian Walter Freund, Pierre Sébastien Huck, Jonathan Edward Nagurney, Yu Du, Matthias Lang, Rudolf Konrad Selmeier, Elisa Jubany Arribas
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Publication number: 20150000268Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.Type: ApplicationFiled: June 28, 2013Publication date: January 1, 2015Inventors: Cathal Clancy, Daniel Edward Loringer, Rodrigo Rodriguez Erdmenger, Vittorio Michelassi
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Publication number: 20140017099Abstract: An exemplary compressor is provided. The compressor includes a plurality of blades, a hub defining a front surface and a back surface, and a first flow restriction structure provided at the back surface of the hub. The plurality of blades are arranged in a predefined manner on the front surface for receiving input air flow at a first pressure and compressing the input air flow to provide an output air flow at a second pressure higher than the first pressure. The first flow restriction member is configured for preventing at least a portion of the output air flow at the second pressure from entering into the back surface of the hub to reduce an air pressure at the back surface of the hub.Type: ApplicationFiled: July 16, 2012Publication date: January 16, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Rodrigo Rodriguez Erdmenger, Kendall Roger Swenson, Daniel Edward Loringer, Anthony Holmes Furman, Neil Xavier Blythe, Lukas William Johnson, Jonathan Edward Nagurney, Yu Du, Cathal Clancy, Matthias Lang
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Publication number: 20140013740Abstract: An exemplary turbocharger system for an internal combustion engine is provided. The turbocharger system includes a first turbine and a second turbine. The first turbine is in fluid communication with the internal combustion engine. The first turbine receives a first portion exhaust gas discharged from the internal combustion engine and provides a first turbine exhaust gas. The second turbine is in fluid communication with the first turbine via an inter-stage channel. The inter-stage channel transports the first turbine exhaust gas from the first turbine to the second turbine. The inter-stage channel is in thermal connection with an exhaust gas recirculation channel defined between an inlet and an outlet of the internal combustion engine. The first turbine exhaust gas flowing through the inter-stage channel is capable of being heated by a second portion exhaust gas discharged from the internal combustion engine and flowing through the exhaust gas recirculation channel.Type: ApplicationFiled: July 16, 2012Publication date: January 16, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Rodrigo Rodriguez Erdmenger, Cathal Clancy, Daniel Edward Loringer, Jassin Marcel Fritz, Neil Xavier Blythe, Lukas William Johnson, Sebastian Walter Freund, Pierre Sébastien Huck, Jonathan Edward Nagurney, Yu Du, Matthias Lang, Rudolf Konrad Selmeier, Elisa Jubany Arribas