Patents by Inventor Steven Aleksy Radomski
Steven Aleksy Radomski 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: 9879545Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.Type: GrantFiled: January 17, 2014Date of Patent: January 30, 2018Assignee: ROLLS-ROYCE plcInventors: Steven Aleksy Radomski, Clive Grafton-Reed, Ian Crowston, Andrea Lelio Maurizio
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Patent number: 9855628Abstract: A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. The pre-formed filler insert (400) provides a lightweight core for the finished aerofoil component in use.Type: GrantFiled: September 2, 2014Date of Patent: January 2, 2018Assignee: ROLLS-ROYCE plcInventor: Steven Aleksy Radomski
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Patent number: 9777599Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.Type: GrantFiled: October 3, 2014Date of Patent: October 3, 2017Assignee: ROLLS-ROYCE plcInventors: Steven Aleksy Radomski, Simon Read
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Patent number: 9771807Abstract: A method of manufacturing a hollow aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a mandrel (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. Remotely detectable elements (700) may be provided to the mandrel (400) to enable the location of the pocket (310) to be accurately determined from outside the aerofoil (100).Type: GrantFiled: August 29, 2014Date of Patent: September 26, 2017Assignee: ROLLS-ROYCE plcInventor: Steven Aleksy Radomski
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Publication number: 20160047257Abstract: The present disclosure provides an aerofoil body comprising a root portion and a tip portion, each having a pressure surface and a suction surface. The pressure surface and suction surface of the root and/or tip portion each comprise a respective ridge portion. Each ridge portion has an inclined first face and an oppositely inclined second face. Each ridge portion may be, for example, a triangular or semi-circular prism.Type: ApplicationFiled: August 4, 2015Publication date: February 18, 2016Inventors: Steven Aleksy RADOMSKI, Matthew Paul JEVONS
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Publication number: 20150252675Abstract: A method of manufacturing a hollow aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a mandrel (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. Remotely detectable elements (700) may be provided to the mandrel (400) to enable the location of the pocket (310) to be accurately determined from outside the aerofoil (100).Type: ApplicationFiled: August 29, 2014Publication date: September 10, 2015Inventor: Steven Aleksy RADOMSKI
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Publication number: 20150125308Abstract: A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. The pre-formed filler insert (400) provides a lightweight core for the finished aerofoil component in use.Type: ApplicationFiled: September 2, 2014Publication date: May 7, 2015Inventor: Steven Aleksy RADOMSKI
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Publication number: 20150104306Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.Type: ApplicationFiled: October 3, 2014Publication date: April 16, 2015Inventors: Steven Aleksy RADOMSKI, Simon READ
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Publication number: 20140271227Abstract: A method of manufacturing a hollow aerofoil component for a gas turbine engine includes using a capping panel to cover a pocket in a pocketed aerofoil body. During manufacture, the outer surface of the capping panel is located relative to the pocketed aerofoil body. This ensures that the outer surface of the capping panel is located as accurately as possible. This means that the capping panel can be made to be as thin as possible, which in turn reduces weight and material wastage. Once the capping panel has been located in position, it may be welded to the aerofoil body in order to produce the hollow aerofoil component.Type: ApplicationFiled: January 17, 2014Publication date: September 18, 2014Applicant: ROLLS-ROYCE PLCInventors: Steven Aleksy RADOMSKI, Clive GRAFTON-REED, Ian CROWSTON, Andrea Lelio MAURIZIO
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Patent number: 8475118Abstract: Within such machines as gas turbine engines it is desirable to provide close association between rotating assemblies and a rotor path arrangement to reduce leakage. However, such arrangements of rotor assemblies and rotor path arrangements are subject to thermal cycling and differentials between the respective parts can lead to rub associations. In order to allow closer thermal responses between the respective rotor path arrangement and rotor assembly, a flexible assembly is provided for a liner. A face surface is presented upon a backer plate or floating ring such that the thermal response can be tuned to the reciprocal similar effects under the same conditions of the rotor assembly. In such circumstances, closer gap control can be achieved. Furthermore, rather than requiring an entire integral casing to be overhauled, generally only the face surfaces and/or the flexible assembly will require remedial action.Type: GrantFiled: June 24, 2009Date of Patent: July 2, 2013Assignee: Rolls-Royce PLCInventors: Thomas Gerard Mulcaire, Steven Aleksy Radomski
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Publication number: 20100034645Abstract: Within such machines as gas turbine engines it is desirable to provide close association between rotating assemblies and a rotor path arrangement to reduce leakage. However, such arrangements of rotor assemblies and rotor path arrangements are subject to thermal cycling and differentials between the respective parts can lead to rub associations. In order to allow closer thermal responses between the respective rotor path arrangement and rotor assembly, a flexible assembly (8, 9, 10, 100) is provided for a liner (6). A face surface (5, 103) is presented upon a backer plate (10) or floating ring (101) such that the thermal response can be tuned to the reciprocal similar effects under the same conditions of the rotor assembly. In such circumstances, closer gap (111) control can be achieved. Furthermore, rather than requiring an entire integral casing to be overhauled, generally only the face surfaces (5, 108) and/or the flexible assembly will require remedial action.Type: ApplicationFiled: June 24, 2009Publication date: February 11, 2010Applicant: ROLLS-ROYCE PLCInventors: Thomas Gerard Mulcaire, Steven Aleksy Radomski