| Volvo Aero Corporation Patent applications |
| Patent application number | Title | Published |
|---|
| 20120121395 | METHOD FOR FABRICATING A GAS TURBINE ENGINE COMPONENT AND A GAS TURBINE ENGINE COMPONENT - A method for fabricating a gas turbine engine component including an inner ring, an outer ring and at least one strut connecting the inner ring with the outer ring includes the steps of connecting the inner ring to the outer ring via a load carrying edge of the strut, and attaching a side face component of the strut in abutment with the load carrying edge after the step of connecting the inner ring to the outer ring has been performed. A as turbine engine component fat by the method is also provided. | 05-17-2012 |
| 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 |
| 20120093642 | STRUT AND A GAS TURBINE STRUCTURE COMPRISING THE STRUT - 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. | 04-19-2012 |
| 20120063861 | HOLDER FOR A CUTTING TOOL, A CUTTING TOOL AND A CUTTING INSERT - A holder for a cutting tool includes a body having a first channel for receiving a stem portion of the cutting tool. The body has a second channel intersecting with the first channel. The holder further includes a plunger to be inserted in the second channel, the plunger having a third channel the cross section of which at least partly overlaps with the cross section of the first channel when the plunger is inserted into the body so as to enable the stem of the cutting tool to extend into the third channel when the stem is inserted in the first channel. The holder further includes a mechanism for locking the stem against movement relative to the body by means of the plunger. A cutting tool for use in such a holder and a cutting insert are also provided. | 03-15-2012 |
| 20110308674 | METHOD, ALLOY AND COMPONENT - A method for heat treating a nickel base alloy includes the steps of: a. heating a nickel base alloy to at least its delta (δ) 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 (δ) phase, and b. cooling the nickel base alloy to a temperature below the gamma prime (ν) precipitation temperature at a rate sufficient to precipitate the alloy's chromium carbide and gamma prime (ν) in a serrated grain boundary. | 12-22-2011 |
| 20110299980 | GAS TURBINE ENGINE AND A GAS TURBINE ENGINE COMPONENT - A gas turbine engine component providing a gas flow passage is provided, which gas flow passage surrounds an inner passage surface, an outer passage surface forming an outer delimitation of said gas flow passage. In an aspect, the trace of the inner passage surface in a cross-section perpendicular to a central axis of the component presents at least one substantially straight portion. In another aspect, where a plurality of circumferentially spaced blades extends between the inner and outer passage surfaces, two portions of the trace, in a cross-section perpendicular to a central axis of the component, of the outer passage surface between two adjacent blades are substantially straight and oriented in an angle in relation to each other so as to form a concavity in the gas flow passage. | 12-08-2011 |
| 20110299917 | COMPONENT AND A GAS TURBINE ENGINE COMPRISING THE COMPONENT - 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. Further, the fastening device is adapted to allow the first member to move relative to the fastening element in a second load condition such that the first part of the bushing arrangement can be brought into contact with the fastening element for establishing a second load transmission path between the first member and the second member via the fastening element. | 12-08-2011 |
| 20110283711 | GAS TURBINE COMPONENT AND A GAS TURBINE ENGINE COMPRISING THE COMPONENT - A gas turbine component includes an element having a relatively weak region with regard to stress loads in operation, the component including at least one elongated stiffening structure which extends on at least one side of the weak region, and the elongated stiffening structure is connected to the element in a load-transmitting manner and adapted to form a load path in its extension direction. | 11-24-2011 |
| 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 |
| 20110164969 | METHOD FOR PRODUCING A VANE, SUCH A VANE AND A STATOR COMPONENT COMPRISING THE VANE - 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. | 07-07-2011 |
| 20110005192 | COOLING SYSTEM FOR AN AIRCRAFT, AIRCRAFT COMPRISING THE COOLING SYSTEM AND COOLING METHOD - A cooling system for an aircraft includes a cooling circuit for transporting a coolant, with the cooling circuit running to a component in the aircraft that is heated up during flying in order to take up heat from the heated-up component via the coolant. The cooling circuit runs to a jet engine for propulsion of the aircraft in order to release heat to a flow of gas in the jet engine via the coolant. | 01-13-2011 |
| 20110002778 | GAS TURBINE HOUSING COMPONENT - 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. | 01-06-2011 |
| 20110000223 | GAS TURBINE COMPONENT AND A METHOD FOR PRODUCING A GAS TURBINE COMPONENT - A gas turbine component includes an inner ring, an outer ring, and a plurality of circumferentially spaced struts which are rigidly connected to the inner ring and the outer ring forming a load-carrying structure. The component includes at least one fairing connected to two adjacent struts defining a gas channel between the struts and the fairing. | 01-06-2011 |
| 20100314467 | THERMAL SPRAYING METHOD AND DEVICE - A thermal spraying device includes an arrangement for generating a flame and an arrangement for injecting a powder into the flame, the flame-generating means including an end piece out of an outlet of which the flame is directed towards a substrate subjected to spraying, and the powder-injection arrangement includes a frame element that projects in the flame ejection direction from the end piece, that at least partly surrounds a flame zone extending from the end piece, and that presents an inner circumference that is larger than the inner circumference of the outlet, and at least one powder port for the introduction of a powder to the flame being arranged on the inner periphery of the frame element at a distance from the outlet of the end piece as seen in the flame ejection direction. There is provided at least one gas injection opening in the frame element, the gas injection opening being located between the outlet of the end piece and the at least one powder port as seen in the flame ejection direction. | 12-16-2010 |
| 20100314466 | THERMAL SPRAYING METHOD AND DEVICE - A thermal spraying device includes an arrangement for generating a flame and an arrangement for injecting a powder into the flame, the flame-generating means including an end piece out of an outlet of which the flame is directed towards a substrate subjected to spraying, and the powder-injection arrangement includes a frame element that projects in the flame ejection direction from the end piece, that at least partly surrounds a flame zone extending from the end piece, and that presents an inner circumference that is larger than the inner circumference of the outlet, and at least one powder port for the introduction of a powder to the flame being arranged on the inner periphery of the frame element at a distance from the outlet of the end piece as seen in the flame ejection direction. There is provided at least one gas injection opening in the frame element, the gas injection opening being located between the outlet of the end piece and the at least one powder port as seen in the flame ejection direction. | 12-16-2010 |
| 20100301617 | GAS TURBINE ENGINE - 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. | 12-02-2010 |
| 20100300067 | COMPONENT CONFIGURED FOR BEING SUBJECTED TO HIGH THERMAL LOAD DURING OPERATION - A component configured for being subjected to a high thermal load during operation includes a wall structure with a tubular shape, wherein the wall structure includes a plurality of cooling channels for handling a coolant flow. The wall structure is divided in a plurality of sectors in a circumferential direction of the wall structure. Each sector includes at least two cooling channels and the wall structure is configured to prevent coolant flow communication between the cooling channels in adjacent sectors. | 12-02-2010 |
| 20100278641 | LINER FOR A TURBINE SECTION, A TURBINE SECTION, A GAS TURBINE ENGINE AND AN AEROPLANE PROVIDED THEREWITH - 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. | 11-04-2010 |
| 20100199633 | BLEED STRUCTURE FOR A BLEED PASSAGE IN A GAS TURBINE ENGINE - 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. | 08-12-2010 |
| 20100192351 | METHOD FOR PRODUCING AN ANNULAR WALL STRUCTURE - A method is provided for producing an annular wall structure, the method including the steps of feeding an elongated sheet in its longitudinal direction, plastically deforming a flat surface of the sheet so that a set recess pattern is formed in the elongated sheet during the feeding, and joining edges of a deformed individual sheet and/or edges. | 08-05-2010 |
| 20100180575 | ENGINE WALL STRUCTURE AND A METHOD OF PRODUCING AN ENGINE WALL STRUCTURE - An engine wall structure includes an inner wall to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The webs are mainly formed by a first material and the inner wall is mainly formed by a second material of other composition and other heat conductivity than the first material. | 07-22-2010 |
| 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 |
| 20100154423 | SYSTEM FOR MIXING GAS FLOWS IN A GAS TURBINE ENGINE, GAS TURBINE ENGINE AND AN AIRCRAFT ENGINE - A system is provided for mixing gas flows in a gas turbine engine. The system includes an annular wall structure which internally delimits a channel for a first gas flow. The wall structure includes a plurality of first wall portions. At least one of the first wall portions is movably arranged in a radial direction between a first position and a second position for mixing an external gas flow with the first gas flow. | 06-24-2010 |
| 20100146980 | MASKING ARRANGEMENT FOR A GAS TURBINE ENGINE - A masking arrangement for a gas turbine engine includes a plurality of annular elements arranged overlapping one another when these are viewed in an axial direction so as to mask at least a substantial portion of any interior hot and rotating gas turbine engine part at an aft end of the gas turbine engine from rear view when the masking arrangement is applied downstream the interior part in the gas turbine engine. | 06-17-2010 |
| 20100132367 | DEVICE FOR MOVING A PLURALITY OF HATCHES IN A GAS TURBINE ENGINE - A device is provided for moving a plurality of hatches, spaced at intervals from one another in a circumferential direction of a gas turbine engine, between a first position and a second position, wherein each of the hatches is arranged to keep an opening in a wall in a closed position, when in the first position, and to keep the opening in an open position, when in the second position. At least one of the hatches is provided with two connecting members which are mutually separated in the circumferential direction of the device, and the device includes a linkage for the movement, the linkage being connected to the hatch at the two mutually separated connecting members. | 06-03-2010 |
| 20100116792 | METHOD OF JOINING PIECES OF METAL MATERIAL AND A WELDING DEVICE - A welding device includes at least one beam-reflecting side element arranged so as to reflect at least a part of a high energy density beam towards a region in which a weld joint is to be generated in a piece of material, wherein the beam-reflecting side element protrudes from a surface of said piece of material. | 05-13-2010 |
| 20100111685 | GAS TURBINE ENGINE COMPONENT, A TURBOJET ENGINE PROVIDED THEREWITH, AND AN AIRCRAFT PROVIDED THEREWITH - 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. | 05-06-2010 |
| 20100058586 | METHOD OF MANUFACTURING A WALL STRUCTURE AND A MACHINING TOOL - 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. | 03-11-2010 |
| 20100037589 | COMPONENT CONFIGURED FOR BEING SUBJECTED TO HIGH THERMAL LOAD DURING OPERATION - 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. | 02-18-2010 |
| 20090211224 | OUTLET DEVICE FOR A JET ENGINE AND A CRAFT COMPRISING SUCH AN OUTLET DEVICE - An outlet device for a jet engine comprises a number of fixed ducts, each with a gas intake and a gas outlet for conducting a gas from the jet engine, at least two of the outlets of said gas ducts open in different directions, and a gas distribution arrangement is arranged at the gas intakes for selective distribution of the gas to the ducts. | 08-27-2009 |
| 20090202353 | WHEEL FOR A ROTATING FLOW MACHINE - A wheel for a rotating flow machine, comprising a rotor ( | 08-13-2009 |
| 20090202338 | BLADE FOR A FLOW MACHINE - In a blade intended to be exposed to a gas flow at high speed during operation of a flow machine comprising the blade, the blade includes a front end designed to face towards the incoming gas flow and a rear end. The front end is provided with a concave area that is such that during operation a stagnation point for the incoming gas flow arises at a distance in front of an outer blade surface that defines the concave area and such that the outer blade surface is thereby at least partially protected from the incoming gas flow. | 08-13-2009 |
| 20090114766 | ANNULAR TORSIONAL RIGID STATIC COMPONENT FOR AN AIRCRAFT ENGINE - In an annular torsional rigid static component for an aircraft engine, the component includes at least one arrangement for mounting the engine to an aircraft. The mounting arrangement comprises a body formed in a composite material. | 05-07-2009 |
| 20090028699 | STATIC GAS TURBINE COMPONENT AND METHOD FOR REPAIRING SUCH A COMPONENT - A static gas turbine component includes an inner and an outer annular support member and a plurality of circumferentially spaced radial struts arranged between the support members for transmitting structural loads. Each of a plurality of the struts includes a load carrying core rigidly fixed to both the inner and the outer support member forming a unitary carcass with the support members, an impact resistant shell surrounding the core, and an energy absorbing material arranged between the core and the shell. | 01-29-2009 |
| 20080276596 | Engine Wall Structure and a Method of Producing an Engine Wall Structure - An engine wall structure includes an inner wall to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The webs are mainly formed by a first material and the inner wall is mainly formed by a second material of other composition and other heat conductivity than the first material. | 11-13-2008 |
| 20080260482 | Method and Device for Controlling a Tool with Ultrasonic Waves - 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. | 10-23-2008 |
| 20080245054 | Cooling System for an Aircraft, Aircraft Comprising the Cooling System and Cooling Method - A cooling system for an aircraft includes a cooling circuit for transporting a coolant, with the cooling circuit running to a component in the aircraft that is heated up during flying in order to take up heat from the heated-up component via the coolant. The cooling circuit runs to a jet engine for propulsion of the aircraft in order to release heat to a flow of gas in the jet engine via the coolant. | 10-09-2008 |
| 20080236138 | Arrangement for Propelling an Aircraft, Aircraft and Outlet Nozzle for a Jet Engine - The invention relates to an arrangement for propelling an aircraft comprising a jet engine and an outlet nozzle arranged downstream of the jet engine. The jet engine is of a type which generates an internal core flow and an external fan flow. A part of the outlet nozzle has an internal surface which defines a gas duct for the fan flow. The aforementioned part of the outlet nozzle includes a wall structure that is arranged at a distance from the internal surface such that it separates the gas duct for the fan flow from an internal gas duct for the core flow. | 10-02-2008 |
| 20080216315 | Method of Producing an Engine Wall Structure - A method is provided for producing an engine wall structure that includes an inner wall, to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The engine wall structure is produced by wire-electro discharge machining the duct out of a solid sheet forming the entire engine wall structure including the inner wall, the outer wall and the webs. | 09-11-2008 |
| 20080213088 | Stator for a Jet Engine, a Jet Engine Comprising Such a Stator, and an Aircraft Comprising the Jet Engine - 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. | 09-04-2008 |
| 20080206719 | Method For Training A Person While Operating A Vehicle - 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. | 08-28-2008 |
