Patents by Inventor Brian HANDLEY
Brian HANDLEY 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: 9309777Abstract: A tip clearance control device adapted to control the clearance of a rotating aerofoil structure with a surrounding casing portion, and a method of controlling the tip clearance of a rotating aerofoil structure with a surrounding casing portion. The device includes a member operatively connected to the casing portion; the member having at least a first configuration in which the casing portion is at a first radial position and a second configuration in which the casing portion is at a second radial position, wherein the configuration of the member is controlled by magnetic flux in a magnetic circuit which includes at least one ferromagnetic element including ferromagnetic material, where the configuration of the member is responsive to the temperature of the ferromagnetic element.Type: GrantFiled: July 12, 2012Date of Patent: April 12, 2016Assignee: ROLLS-ROYCE plcInventors: John R. Webster, Nicolas Evanno, Brian Handley
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Patent number: 9243513Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.Type: GrantFiled: October 6, 2011Date of Patent: January 26, 2016Assignee: ROLLS-ROYCE PLCInventors: Zahid M Hussain, Christopher T J Sheaf, Andrew J Mullender, David MacManus, Brian A Handley
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Patent number: 8882422Abstract: A seal having an integral attachment arrangement. The attachment arrangement comprises at least one attachment feature and at least one locking feature. The at least one attachment feature is configured and arranged to interdigitate with features of another component in a first orientation and to lock to the other component in a second orientation. The second orientation is rotationally displaced from the first orientation.Type: GrantFiled: May 17, 2011Date of Patent: November 11, 2014Assignee: Rolls-Royce PLCInventors: Zahid M. Hussain, Brian A. Handley, Andrew J. Mullender
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Patent number: 8845273Abstract: A fluid transfer arrangement comprising a duct having a first end and a second end, a pulse generation mechanism located at the first end of the duct to direct fluid pulses towards the second end of the duct in use, and a baffle located at the second end of the duct that defines an aperture having sharp edges. The sharp edges generate ring vortex fluid flow from the aperture in use. Applications include impingement heating and cooling.Type: GrantFiled: May 17, 2011Date of Patent: September 30, 2014Assignee: Rolls-Royce PLCInventors: Zahid M. Hussain, Christopher T. J. Sheaf, Brian A. Handley
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Patent number: 8511095Abstract: A flow discharge device, such as a bleed assembly in a gas turbine engine, comprises a discharge outlet member having a skirt which is accommodated telescopically in a housing so as to be displaceable with respect to wall of a duct from a retracted position in which slots in the skirt lie outside the duct, and an extended position in which the slots open into the duct for the discharge of a secondary fluid into the flow in the duct. The discharge outlet member is moved to the extended position by the pressure of the secondary fluid acting on a silencer element. A spring returns the discharge outlet member to the retracted position when the flow of the secondary fluid is terminated.Type: GrantFiled: June 24, 2010Date of Patent: August 20, 2013Assignee: Rolls-Royce PLC.Inventors: Andrew J. Mullender, Brian A. Handley, Zahid M. Hussain
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Patent number: 8511056Abstract: Breather air, containing oil mist, is discharged from a nacelle 4 of a gas turbine engine through an exhaust port 26 at a surface 22 of the nacelle 4. Energized air, at relatively high velocity is discharged from a clean air outlet 28, and forms a barrier between the breather air and the external surface 22, so preventing contamination of the surface 22 by oil deposited from the breather air.Type: GrantFiled: April 27, 2010Date of Patent: August 20, 2013Assignee: Rolls-Royce PLCInventors: Brian A Handley, Andrew J Mullender, Zahid M Hussain
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Publication number: 20130034424Abstract: A tip clearance control device adapted to control the clearance of a rotating aerofoil structure with a surrounding casing portion, and a method of controlling the tip clearance of a rotating aerofoil structure with a surrounding casing portion. The device includes a member operatively connected to the casing portion; the member having at least a first configuration in which the casing portion is at a first radial position and a second configuration in which the casing portion is at a second radial position, wherein the configuration of the member is controlled by magnetic flux in a magnetic circuit which includes at least one ferromagnetic element including ferromagnetic material, where the configuration of the member is responsive to the temperature of the ferromagnetic element.Type: ApplicationFiled: July 12, 2012Publication date: February 7, 2013Applicant: ROLLS-ROYCE PLCInventors: John R. WEBSTER, Nicolas EVANNO, Brian HANDLEY
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Publication number: 20120137650Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.Type: ApplicationFiled: October 6, 2011Publication date: June 7, 2012Applicant: ROLLS-ROYCE PLCInventors: Zahid M. HUSSAIN, Christopher T.J. SHEAF, Andrew J. MULLENDER, David MACMANUS, Brian A. HANDLEY
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Publication number: 20110309587Abstract: A seal having an integral attachment arrangement. The attachment arrangement comprises at least one attachment feature and at least one locking feature. The at least one attachment feature is configured and arranged to interdigitate with features of another component in a first orientation and to lock to the other component in a second orientation. The second orientation is rotationally displaced from the first orientation.Type: ApplicationFiled: May 17, 2011Publication date: December 22, 2011Applicant: ROLLS-ROYCE PLCInventors: Zahid M. HUSSAIN, Brian A. HANDLEY, Andrew J. MULLENDER
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Publication number: 20110296848Abstract: A fluid transfer arrangement comprising a duct having a first end and a second end, a pulse generation mechanism located at the first end of the duct to direct fluid pulses towards the second end of the duct in use, and a baffle located at the second end of the duct that defines an aperture having sharp edges. The sharp edges generate ring vortex fluid flow from the aperture in use. Applications include impingement heating and cooling.Type: ApplicationFiled: May 17, 2011Publication date: December 8, 2011Applicant: ROLLS-ROYCE PLCInventors: Zâhid M. HUSSAIN, Christopher T.J. SHEAF, Brian A. HANDLEY
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Patent number: 8052377Abstract: A gas turbine engine including a bypass duct defined by radially outer and inner walls, the radially inner wall defined by acoustic panels. The acoustic panels define the outer wall of a heated fire zone. In conventional engines an insulating blanket is attached to the panels, however, this is heavy and costly. Cooling film means are configured to pass bypass air through and over an internal surface of the panel.Type: GrantFiled: October 30, 2007Date of Patent: November 8, 2011Assignee: Rolls-Royce PLC.Inventors: Michael H. Coney, Andrew J. Mullender, Brian A. Handley, David M. Parkin
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Publication number: 20110011477Abstract: A flow discharge device, such as a bleed assembly in a gas turbine engine, comprises a discharge outlet member 38 having a skirt 44 which is accommodated telescopically in a housing 36 so as to be displaceable with respect to a wall 27 of a duct 22 from a retracted position (FIG. 2) in which slots 48 in the skirt 44 lie outside the duct 22, and an extended position (FIG. 3) in which the slots 48 open into the duct 22 for the discharge of a secondary fluid into the flow in the duct 22. The discharge outlet member 38 is moved to the extended position by the pressure of the secondary fluid acting on a silencer element 46. A spring 52 returns the discharge outlet member to the retracted position when the flow of the secondary fluid is terminated.Type: ApplicationFiled: June 24, 2010Publication date: January 20, 2011Applicant: ROLLS-ROYCE PLCInventors: Andrew J. MULLENDER, Brian A. Handley, Zahid M. Hussain
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Publication number: 20100293917Abstract: Breather air, containing oil mist, is discharged from a nacelle 4 of a gas turbine engine through an exhaust port 26 at a surface 22 of the nacelle 4. Energised air, at relatively high velocity is discharged from a clean air outlet 28, and forms a barrier between the breather air and the external surface 22, so preventing contamination of the surface 22 by oil deposited from the breather air.Type: ApplicationFiled: April 27, 2010Publication date: November 25, 2010Applicant: ROLLS-ROYCE PLCInventors: Brian A. HANDLEY, Andrew J. Mullender, Zahid M. Hussain
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Publication number: 20080110593Abstract: An aircraft electrical component cooling arrangement comprises at least one electrical component (40) housed in a body (38), for example an engine's electronic controller, characterised in that fuel is passed through the body (38) and directly over the component (40). Advantageously, this maintains a uniform temperature of the electronic components, protection against internal and external fire, ability to further miniaturise electrical components and/or combine units due to enhanced cooling effectiveness over convention air cooled systems.Type: ApplicationFiled: October 30, 2007Publication date: May 15, 2008Applicant: ROLLS-ROYCE PLCInventors: Michael H. Coney, Andrew J. Mullender, Brian A. Handley, David M. Parkin
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Publication number: 20080112796Abstract: A gas turbine engine (10) comprising a bypass duct (22) defined by radially outer and inner walls (27, 30), the radially inner wall (30) defined by acoustic panels (30). The acoustic panels (30) define the outer wall of a heated fire zone. In conventional engines an insulating blanket is attached to the panels, however, this is heavy and costly. The present invention comprises cooling film means (50) to pass bypass air through and over an internal surface (39) of the panel (30).Type: ApplicationFiled: October 30, 2007Publication date: May 15, 2008Applicant: ROLLS-ROYCE PLCInventors: Michael H. Coney, Andrew J. Mullender, Brian A. Handley, David M. Parkin
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Patent number: 6418806Abstract: The fire resistance of components normally subject to a standard flame test is evaluated using low temperature model tests. Reynolds number, Froude number, the pressure ratio of the flame to the surrounding atmosphere are matched in the modelling parameters and account is taken of the Prandtl number. Also, the model flow is controlled so as to match the change of momentum flux ratio in the flow through the burner used in a standard flame test. The method allows testing of easily produced model components at temperatures less than 90° C., with savings of cost and time.Type: GrantFiled: November 4, 1999Date of Patent: July 16, 2002Assignee: Rolls-Royce plcInventors: Andrew J Mullender, Brian A Handley, Michael H Coney, Peter T Ireland, Andrew Neely