Sjoqvist
Dan Sjoqvist, Anderstorp SE
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20100038496 | CABLE LADDER DEVICE - A cable support device ( | 02-18-2010 |
Fredrik Sjöqvist, Torslanda SE
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20140324309 | METHOD AND SYSTEM FOR CALIBRATING AN ESTIMATED CLUTCH CHARACTERISTIC CURVE - A method and a system for calibrating an estimated clutch characteristic curve of a dual-clutch vehicle transmission are provided. The method includes | 10-30-2014 |
Fredrik Sjöqvist, Torslanda SE
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20110297502 | VEHICLE CLUTCH WITH VARIABLE LEVER RATIO - A vehicle clutch includes a clutch disc, a moveable pressure plate, a plurality of clutch levers, and an actuator to cause pressure plate to move by pivoting the clutch levers. Each of the clutch levers are pivotable around a first fulcrum, which is part of a clutch housing, a second fulcrum, which is part of the pressure plate, and a third fulcrum, which is part of the actuator. A pivot surface of each of the fulcrums around which the clutch levers pivot with a rolling action over the pivot surface is defined by a radius, which measures from a geometrical centre in each of the fulcrums and out to the pivot surface. A magnitude of the radius varies along the pivot surface in order to have a lever ratio of the clutch levers that varies as the clutch levers pivot. | 12-08-2011 |
Roger Sjoqvist, Trollhättan SE
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20100163671 | A MOUNTING ELEMENT FOR A GAS TURBINE ENGINE, AND A STRUCTURE AND AN AIRCRAFT WITH SUCH A MOUNTING ELEMENT - 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. | 07-01-2010 |
Roger Sjoqvist, Trollhättan SE
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20100163671 | A MOUNTING ELEMENT FOR A GAS TURBINE ENGINE, AND A STRUCTURE AND AN AIRCRAFT WITH SUCH A MOUNTING ELEMENT - 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. | 07-01-2010 |
20150033759 | GAS TURBINE ENGINE COMPONENT - The invention concerns a gas turbine engine component ( | 02-05-2015 |
Roger Sjöqvist, Trollhattan SE
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20110262277 | GAS TURBINE COMPOSITE WORKPIECE TO BE USED IN GAS TURBINE ENGINE - 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. | 10-27-2011 |
Roger Sjöqvist, Trollhättan SE
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20120111023 | SUPPORTING STRUCTURE FOR A GAS TURBINE ENGINE - 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. The inclined portion of the connection region is directed substantially in parallel to the inclined portion of the mean camber line of the airfoil shaped element. A gas turbine engine including a supporting structure of the above type is also provided. | 05-10-2012 |