Patents by Inventor Roger Sjoqvist
Roger Sjoqvist 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: 9822652Abstract: A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, wherein the supporting structure has an inlet side for primary gas flow entrance and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side, a trailing edge directed towards the outlet side, and two opposite sides connecting the leading edge and the trailing edge, and wherein at least a first of said radial elements is connected to an adjacent part of the supporting structure via a weld joint that extends across the leading edge and circumferentially at least partly around the first radial element.Type: GrantFiled: July 3, 2012Date of Patent: November 21, 2017Assignee: GKN Aerospace Sweden ABInventors: Roger Sjoqvist, Hakan Jakobsson, Dan Gustafsson
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Patent number: 9689312Abstract: The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein an annular load transfer structure (23) extends circumferentially along an inner side of the inner ring (20) and also inwards in a radial direction of the component (27). The first portion (23a), at least along a part of the circumference, is inclined in the radial direction in relation to a second portion (23b), wherein the two inclined portions (23a, 23b) are connected in a connection zone (26) between the inclined portions (23a, 23b), and wherein a radial and/or axial position of the connection zone (26) varies along the circumference such that the radial/axial position of the connection zone in a location that circumferentially corresponds to a first element (22a), i.e.Type: GrantFiled: December 22, 2011Date of Patent: June 27, 2017Assignee: GKN Aerospace Sweden ABInventor: Roger Sjöqvist
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Publication number: 20150176420Abstract: A supporting structure for a gas turbine engine comprises an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings, said radial elements being configured to transfer loads between the inner ring and the outer ring, wherein a gas channel for a primary axial gas flow is defined between the inner and outer rings, wherein the supporting structure has an inlet side for primary gas flow entrance and an outlet side for primary gas outflow, wherein the radial elements have an airfoil shape with a leading edge directed towards the inlet side, a trailing edge directed towards the outlet side, and two opposite sides connecting the leading edge and the trailing edge, and wherein at least a first of said radial elements is connected to an adjacent part of the supporting structure via a weld joint that extends across the leading edge and circumferentially at least partly around the first radial elementType: ApplicationFiled: July 3, 2012Publication date: June 25, 2015Inventors: Roger Sjoqvist, Hakan Jakobsson, Dan Gustafsson
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Patent number: 9003812Abstract: A supporting structure for a gas turbine engine includes at least one annular member, and a plurality of circumferentially spaced elements that extend in a radial direction of the annular member and that are connected to the annular member. At least one of the circumferentially spaced elements has an airfoil shape in cross section. The annular member includes at least two substantially flat panel segments that are arranged side by side in a circumferential direction of the annular member. The panel segments are connected to each other in a connection region that extends along facing end parts of the two panel segments. The airfoil shaped element is connected to the annular member at the connection region. A mean camber line of the airfoil shaped element at least along a portion of its length is inclined in relation to an axial direction of the annular member, and the connection region at least along a portion of its length is inclined in relation to the axial direction of the annular member.Type: GrantFiled: May 8, 2009Date of Patent: April 14, 2015Assignee: GKN Aerospace Sweden ABInventor: Roger Sjöqvist
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Publication number: 20150033759Abstract: The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein an annular load transfer structure (23) extends circumferentially along an inner side of the inner ring (20) and also inwards in a radial direction of the component (27). The first portion (23a), at least along a part of the circumference, is inclined in the radial direction in relation to a second portion (23b), wherein the two inclined portions (23a, 23b) are connected in a connection zone (26) between the inclined portions (23a, 23b), and wherein a radial and/or axial position of the connection zone (26) varies along the circumference such that the radial/axial position of the connection zone in a location that circumferentially corresponds to a first element (22a), i.e.Type: ApplicationFiled: December 22, 2011Publication date: February 5, 2015Applicant: GKN Aerospace Sweden ABInventor: Roger Sjöqvist
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Publication number: 20120111023Abstract: A supporting structure for a gas turbine engine includes at least one annular member, and a plurality of circumferentially spaced elements that extend in a radial direction of the annular member and that are connected to the annular member. At least one of the circumferentially spaced elements has an airfoil shape in cross section. The annular member includes at least two substantially flat panel segments that are arranged side by side in a circumferential direction of the annular member. The panel segments are connected to each other in a connection region that extends along facing end parts of the two panel segments. The airfoil shaped element is connected to the annular member at the connection region. A mean camber line of the airfoil shaped element at least along a portion of its length is inclined in relation to an axial direction of the annular member, and the connection region at least along a portion of its length is inclined in relation to the axial direction of the annular member.Type: ApplicationFiled: May 8, 2009Publication date: May 10, 2012Applicant: VOLVO AERO CORPORATIONInventor: Roger Sjöqvist
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Publication number: 20110262277Abstract: A gas turbine composite workpiece, such as a workpiece forming a part of a gas turbine casing, is provided. The workpiece includes at least two components joined by at least one weld seam. In order to reduce thermal stresses of the workpiece during operation, the weld seam is interrupted by at least one aperture. In order to reduce the exchange of gases between the workpiece's sides, the workpiece may be equipped with an arrangement for preventing gas flow through the aperture.Type: ApplicationFiled: December 18, 2008Publication date: October 27, 2011Applicant: VOLVO AERO CORPORATIONInventors: Roger Sjöqvist, Dan Gustafsson, Hasse Lindell
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Patent number: 7802962Abstract: A bearing support structure is provided for installation in a gas turbine engine between radially inner first and second bearings adapted to rotatably support a first and a second rotor, respectively, and a radially outer engine frame. The support structure includes a first annular plate-shaped part and an arrangement for supporting the first bearing at one end thereof and a second annular plate-shaped part and an arrangement for supporting the second bearing at one end thereof. The first and second plate-shaped parts are joined together forming a one-piece unit for installation in the gas turbine engine.Type: GrantFiled: September 13, 2005Date of Patent: September 28, 2010Assignee: Volvo Aero CorporationInventor: Roger Sjöqvist
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Publication number: 20100163671Abstract: A mounting element for transferring loads between a gas turbine engine and an airframe is provided, the mounting element presenting a cylindrical hole for receiving a fastening element, such as a pin or a bolt. The mounting element includes a collapsible element surrounding the hole, and is adapted to operate in a first mode, and to operate, upon a collapse of the collapsible element, in a second mode, in which the stiffness of the mounting element is lower than in the first mode. In a second aspect of the invention the energy absorption capacity of the mounting element is higher in the second mode than in the first mode.Type: ApplicationFiled: June 9, 2008Publication date: July 1, 2010Applicant: VOLVO AERO CORPORATIONInventors: Jan-Erik Svensson, Roger Sjoqvist
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Publication number: 20080031727Abstract: A bearing support structure is provided for installation in a gas turbine engine between radially inner first and second bearings adapted to rotatably support a first and a second rotor, respectively, and a radially outer engine frame. The support structure includes a first annular plate-shaped part and an arrangement for supporting the first bearing at one end thereof and a second annular plate-shaped part and an arrangement for supporting the second bearing at one end thereof. The first and second plate-shaped parts are joined together forming a one-piece unit for installation in the gas turbine engine.Type: ApplicationFiled: September 13, 2005Publication date: February 7, 2008Applicant: VOLVO AERO CORPORATIONInventor: Roger Sjoqvist
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Patent number: 7140834Abstract: A turbine including a rotor (1) that is driven by gas and that has a housing (2) enclosing the rotor. The turbine includes a component (6) suspended from the housing (2) that is arranged inside the housing (2) and at least partially beside the rotor (1) with respect to the direction (5) of the gas flow in order to impede any fragments which may come loose from the rotor from penetrating the housing in radial direction.Type: GrantFiled: December 3, 2004Date of Patent: November 28, 2006Assignee: Volvo Aero CorporationInventors: Jan Svensson, Eva Dahl, David Russberg, Roger Sjoqvist, Jan Nilsson, Sten Johansson
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Publication number: 20060233636Abstract: A turbine including a rotor (1) that is driven by gas and that has a housing (2) enclosing the rotor. The turbine includes a component (6) suspended from the housing (2) that is arranged inside the housing (2) and at least partially beside the rotor (1) with respect to the direction (5) of the gas flow in order to impede any fragments which may come loose from the rotor from penetrating the housing in radial direction.Type: ApplicationFiled: December 3, 2004Publication date: October 19, 2006Applicant: VOLVO AERO CORPORATIONInventors: Jan SVENSSON, Eva DAHL, David RUSSBERG, Roger SJOQVIST, Jan NILSSON, Sten JOHANSSON