Patents Assigned to Volvo Aero Corporation
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Patent number: 8944139Abstract: A method for manufacturing an engine component includes forming the component by deposition of powder, which is melted by a heat source, in subsequent Layers to form the component into a desired shape, the component having an outer surface, and re-melting at least part of the outer surface.Type: GrantFiled: April 24, 2009Date of Patent: February 3, 2015Assignee: Volvo Aero CorporationInventors: Peter Jonsson, Dzevad Imamovic, Börje Nordin, Per Thorin
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Publication number: 20140377719Abstract: In a method for training a person while operating a vehicle, the vehicle has a control system for receiving vehicle operating commands from the person for controlling the vehicle. A calculation unit is provided for simulating a state of the vehicle and/or the environment to which the vehicle is subjected, the simulated state being a possible real state of the vehicle and/or the environment which is different from the actual state of the vehicle and/or the environment. The vehicle operating commands and the calculation unit are used for calculating vehicle command signals. The vehicle command signals are used for controlling the vehicle so as to cause the vehicle to respond to the vehicle operating commands in a way that corresponds to the state simulated by the calculation unit instead of the actual state of the vehicle and/or the environment.Type: ApplicationFiled: September 4, 2014Publication date: December 25, 2014Applicant: VOLVO AERO CORPORATIONInventors: Thomas JOHNSSON, Anders LUNDBLADH, Dan RING, Olof HANNIUS
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Patent number: 8888451Abstract: A method for producing a vane for application in a component in a gas turbine engine includes casting at least one of a vane leading edge part and a vane trailing edge part and connecting the leading edge part and the trailing edge part.Type: GrantFiled: October 11, 2007Date of Patent: November 18, 2014Assignee: Volvo Aero CorporationInventors: Lisa Falk, Elin Skoglund
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Patent number: 8794912Abstract: A strut for application between an outer ring and an inner ring in a gas turbine structure and a gas turbine structure including such a strut are provided. The strut includes an end portion which has a diverging shape so that an internal space is formed in the end portion for receiving at least part of an engine mount. Engine mounting lugs can be positioned at such struts.Type: GrantFiled: May 7, 2009Date of Patent: August 5, 2014Assignee: Volvo Aero CorporationInventors: Martin Nilsson, Hans Mårtensson
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Patent number: 8757919Abstract: A component includes a first member, a second member and a device for fastening the first member to the second member. A first hole extends through a portion of the first member and a second hole extends through a portion of the second member. The first member and the second member are positioned such that the first hole and the second hole coincide. The fastening device includes an elongated fastening element arranged in the coinciding holes and a bushing arrangement arranged around the fastening element and adapted to establish a load transmission path between the first member and the second member. A first part of the bushing arrangement is arranged such that an inner surface thereof is positioned at a distance from an exterior surface of the fastening element for establishing a first load transmission path via the bushing arrangement and bypassing the fastening element in a first load condition.Type: GrantFiled: August 29, 2008Date of Patent: June 24, 2014Assignee: Volvo Aero CorporationInventors: Rickard Samuelsson, Niklas Jansson
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Patent number: 8757979Abstract: A rotor element includes at least one irregularity with regard to rotational properties in its circumferential direction and the irregularity is positioned so as to separate the mechanical natural frequencies of the rotor element.Type: GrantFiled: October 5, 2006Date of Patent: June 24, 2014Assignee: Volvo Aero CorporationInventor: Hans Martensson
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Patent number: 8757965Abstract: A gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor structure (14) arranged between the low pressure compressor section (8) and the high pressure compressor section (9). The compressor structure (14) is designed to conduct a gas flow in the gas channel and comprises a plurality of radial struts (15,16,21,24,25) for transmission of load, wherein at least one of the struts (15,16,21,24,25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream of a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from the rotor (10) by a plurality of the struts (15,16,21,24,25) having a cambered shape.Type: GrantFiled: June 2, 2005Date of Patent: June 24, 2014Assignee: Volvo Aero CorporationInventor: Stephane Baralon
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Patent number: 8747066Abstract: A gas turbine housing component includes a wall structure including two adjacent wall parts and a connection arrangement arranged between adjacent edges of the two wall parts. The connection arrangement includes an elongated seal strip positioned along the wall part edges and bridging the distance between the wall part edges.Type: GrantFiled: March 18, 2008Date of Patent: June 10, 2014Assignee: Volvo Aero CorporationInventors: Linda Ström, Jonas Lindskog, Per Widström
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Patent number: 8708647Abstract: A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed.Type: GrantFiled: December 6, 2006Date of Patent: April 29, 2014Assignee: Volvo Aero CorporationInventor: Arne Boman
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Patent number: 8689540Abstract: A component configured for being subjected to a high thermal load during operation includes a wall structure with cooling channels adapted for handling a coolant flow. At least one first cooling channel is adapted to convey the coolant from a first portion of the component to a second portion of the component. At least one second cooling channel in the second portion is closed so that the coolant is at least substantially-prevented from entering the closed second cooling channel from a cooling channel in the first portion.Type: GrantFiled: February 13, 2007Date of Patent: April 8, 2014Assignee: Volvo Aero CorporationInventors: Jan Häggander, Arne Boman
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Patent number: 8551266Abstract: A method for heat treating a nickel base alloy includes the steps of: a. heating a nickel base alloy to at least its delta (?) phase solvus temperature, and lower than its incipient melting temperature for a predetermined time sufficient to dissolve substantially all of the nickel base alloy's delta (?) phase, and b. cooling the nickel base alloy to a temperature below the gamma prime (?) precipitation temperature at a rate sufficient to precipitate the alloy's chromium carbide and gamma prime (?) in a serrated grain boundary.Type: GrantFiled: October 25, 2007Date of Patent: October 8, 2013Assignee: Volvo Aero CorporationInventors: Dzevad Imamovic, Göran Sjöberg
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Patent number: 8528344Abstract: A bleed structure for a bleed passage in a gas turbine engine includes a first wall portion defining a first side of an opening for the passage, and a second wall portion defining a second side, opposite the first side of the opening. The first and second wall portions end at different positions in an extension direction of the opening.Type: GrantFiled: April 1, 2010Date of Patent: September 10, 2013Assignee: Volvo Aero CorporationInventors: Hans Mårtensson, Martin Nilsson
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Patent number: 8485783Abstract: A gas turbine engine includes in serial flow relationship: a first compressor provided with at least one row of compressor blades distributed circumferentially around the first compressor; a combustion chamber; and a first turbine provided with at least one row of turbine blades distributed circumferentially around the first turbine, wherein the first compressor and the first turbine are rotationally rigidly connected by a first shaft. The first turbine is adapted to influence a gas flow rate through the gas turbine engine depending on a rotational speed of the first turbine, wherein the gas turbine engine further includes an arrangement for controlling the rotational speed of the first turbine. A method for controlling a gas flow rate in an axial flow gas turbine engine is also provided.Type: GrantFiled: December 20, 2007Date of Patent: July 16, 2013Assignee: Volvo Aero CorporationInventor: Anders Erik Lundbladh
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Patent number: 8484982Abstract: A bleed structure for a bleed passage in a gas turbine engine includes a first wall portion defining a first side of an opening for the passage, and a second wall portion defining a second side, opposite the first side of the opening. The first and second wall portions end at different positions in an extension direction of the opening.Type: GrantFiled: February 14, 2006Date of Patent: July 16, 2013Assignee: Volvo Aero CorporationInventors: Hans Mårtensson, Martin Nilsson
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Patent number: 8464831Abstract: A noise attenuation panel includes a first wall, a second wall and partition walls connected to the first and second walls and defining cells between the first and second walls. The first wall is provided with a plurality of through holes. At least two of the cells are interconnected via a communication hole. One of the through holes leads to a first of the at least two interconnected cells and a second of the interconnected cells is configured to prevent any gas flow through the second cell.Type: GrantFiled: September 17, 2009Date of Patent: June 18, 2013Assignee: Volvo Aero CorporationInventors: Marcus Olander Burak, Lars-Erik Eriksson
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Patent number: 8459942Abstract: A gas turbine engine component is provided including at least one ring element, and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. The load carrying vanes have an internal structure with an anisotropic load carrying property, and the internal structure is configured so that a main load carrying direction is in parallel with the extension direction of the load carrying vane. The component includes a stiffening structure bridging the distance between at least two adjacent load carrying vanes in the circumferential direction of the ring element, and the at least two adjacent load carrying vanes are attached to the stiffening structure.Type: GrantFiled: March 28, 2008Date of Patent: June 11, 2013Assignee: Volvo Aero CorporationInventors: Anders Sjunnesson, Niklas Jansson, Robert Reimers, Rickard Samuelsson
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Patent number: 8448335Abstract: A method of manufacturing a wall structure includes producing at least one elongated web in a workpiece by feeding a machining tool along the workpiece, wherein the machining tool simultaneously machines a first side surface of the web, a second side surface of the web and a top surface of the web.Type: GrantFiled: December 19, 2006Date of Patent: May 28, 2013Assignee: Volvo Aero CorporationInventors: Jan Lundgren, Mats Hallqvist
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Patent number: 8419324Abstract: In a method for controlling a tool during machining a work piece using the tool, a first measuring arrangement which has a first ultrasonic probe for emitting ultrasonic waves is used, the first measuring arrangement being arranged ahead of the tool with respect to the relative tool movement direction and being moved relative to the work piece in the relative tool movement direction. The ultrasonic waves emitted by the first ultrasonic probe are transmitted to the work piece, and are transmitted back to the first ultrasonic probe, by a first column of liquid which is created by the first measuring arrangement and situated between the first ultrasonic probe and the work piece for measurement. The measurements are used for automatically adjusting the position of the tool relative to the work piece during machining the work piece.Type: GrantFiled: October 21, 2005Date of Patent: April 16, 2013Assignee: Volvo Aero CorporationInventor: Per Henrikson
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Patent number: 8403629Abstract: A stator for installation in a rear section of a jet engine includes a plurality of guide vanes which extend in the radial direction of the stator and between them define ducts for leading a gas. A first side of the stator in its axial direction defines an inlet for the gas and a second side, opposite the first side, defines an outlet for the gas. The guide vanes have such a shape that together they at least substantially cover the gas inlet viewed in the axial direction of the stator from the outlet side thereof.Type: GrantFiled: October 20, 2005Date of Patent: March 26, 2013Assignee: Volvo Aero CorporationInventor: Anders Lundbladh
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Patent number: 8387389Abstract: A gas turbine engine includes a first flow passage and a main combustion arrangement in the first flow passage. The engine further includes a second flow passage and a first catalytic combustion arrangement in the second flow passage, wherein the second flow passage can communicate with the first flow passage at at least one upstream passage junction upstream of the main combustion arrangement and upstream of the first catalytic combustion arrangement, and the second flow passage can communicate with the first flow passage at at least one downstream passage junction downstream of the main combustion arrangement and downstream of the first catalytic combustion arrangement.Type: GrantFiled: December 20, 2007Date of Patent: March 5, 2013Assignee: Volvo Aero CorporationInventors: Richard Avellan, Tomas Grönstedt