Patents Assigned to GKN AEROSPACE SWEDEN AB
  • Patent number: 10318664
    Abstract: A first set of data is received relating to the operation of a first mechanical part. A plurality of steady state conditions for the first set of operational data is determined. A load history is determined for the first mechanical part based on the plurality of determined steady states and the first set of operational data. One of a plurality of predefined life consumption calculation models is selected based on a type of the first mechanical part and a position of a critical area at the first mechanical part. A level of life consumption for the critical area of the first mechanical part is determined based on the selected life consumption calculation model and the determined load history.
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: June 11, 2019
    Assignee: GKN Aerospace Sweden AB
    Inventors: Magnus Andersson, Fredrik Wanman, Peter Svensson
  • Patent number: 10294816
    Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.
    Type: Grant
    Filed: November 13, 2014
    Date of Patent: May 21, 2019
    Assignees: United Technologies Corporation, GKN Aerospace Sweden AB
    Inventors: Daryl B. Mountz, Theodore W. Kapustka, Glenn Levasseur, Marcus Borg, Joakim Berglund, Anders Svahn, Johan Ockborn, Bengt Pettersson
  • Patent number: 10280790
    Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.
    Type: Grant
    Filed: November 13, 2014
    Date of Patent: May 7, 2019
    Assignees: United Technologies Corporation, GKN Aerospace Sweden AB
    Inventors: Daryl B. Mountz, Theodore W. Kapustka, Glenn Levasseur, Marcus Borg, Joakim Berglund, Anders Svahn, Johan Ockborn, Bengt Pettersson
  • Patent number: 10073007
    Abstract: A reliability range is determined for a parameter of a component in a machine subjected to life reducing loads during operation, comprising the steps of: acquiring, for each of a plurality of load sessions, at least one parameter value for said component; generating a distribution pattern containing said parameter values for the plurality of load sessions; assigning a reliability range for the distribution pattern, wherein parameter values outside said reliability range are considered as being unrealistic; analyzing the parameter values outside the reliability range to determine which of said parameter values outside the reliability range are confirmed to be unrealistic; and adjusting the reliability range if a ratio between the confirmed unrealistic parameter values and the considered unrealistic parameter values is outside a further range being predetermined for the ratio.
    Type: Grant
    Filed: September 12, 2012
    Date of Patent: September 11, 2018
    Assignee: GKN Aerospace Sweden AB
    Inventors: Magnus Andersson, Henrik Eckervald
  • Patent number: 10036276
    Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.
    Type: Grant
    Filed: June 14, 2013
    Date of Patent: July 31, 2018
    Assignees: United Technologies Corporation, GKN Aerospace Sweden AB
    Inventors: Daryl B. Mountz, Theodore W. Kapustka, Glenn Levasseur, Marcus Borg, Joakim Berglund, Anders Svahn, Johan Ockborn, Bengt Pettersson
  • Patent number: 10025893
    Abstract: A life consumption of a component in a machine may be predicted. Load data may be received from a load session of the machine. A plurality of parameter sets may be accessed, each associated with a critical point of the component, which point is considered to have critical life consumption. For each critical point, life consumption may be calculated using a life consumption calculation model receiving the load data and the parameter sets as input. By selecting a plurality of critical points on the component, a more complete view is presented of how the different parts of the component are affected by the load session.
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: July 17, 2018
    Assignee: GKN Aerospace Sweden AB
    Inventors: Magnus Andersson, Anders Larsson
  • Patent number: 10012108
    Abstract: The invention concerns a gas turbine engine component (37) comprising an outer ring structure (10), an inner ring structure (20) and a plurality of circumferentially spaced radial elements (15) for transferring loads between the inner ring structure (20) and the outer ring structure (10), wherein the outer ring structure (10) comprises a circular ring member (11) for withstanding an internal pressure during operation of the gas turbine engine. The invention is characterized in that the outer ring structure (10) comprises a first set of circumferentially distributed and substantially straight reinforcement ribs (16) for achieving radial stiffness, wherein the reinforcement ribs (16) form sides in a polygonal shape and wherein each of said reinforcement ribs (16) extends between two adjacent radial elements (15). The invention also concerns a gas turbine engine (1) comprising a component (37) of the above type.
    Type: Grant
    Filed: December 23, 2011
    Date of Patent: July 3, 2018
    Assignee: GKN Aerospace Sweden AB
    Inventors: Henrik Amnell, Lennart Brottgardh, David Russberg, Patrik Svantesson
  • Patent number: 9951692
    Abstract: The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26).
    Type: Grant
    Filed: December 23, 2011
    Date of Patent: April 24, 2018
    Assignee: GKN Aerospace Sweden AB
    Inventors: Egon Aronsson, Per Widstrom, Elinor Magnusson, Johan Tholérus, Christian Lundh
  • Patent number: 9946232
    Abstract: A set of load data for a selected point in time and resulting from the machine operation is received. The load data is provided from a first database comprising predefined machine conditions associated to different sets of load data for the machine. One of the predefined machine conditions that is most representative of the received set of load data is selected.
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: April 17, 2018
    Assignee: GKN Aerospace Sweden AB
    Inventors: Mikael Nilsson, Daniel Norder
  • Patent number: 9865175
    Abstract: 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: Grant
    Filed: September 4, 2014
    Date of Patent: January 9, 2018
    Assignee: GKN Aerospace Sweden AB
    Inventors: Thomas Johnsson, Anders Lundbladh, Dan Ring, Olof Hannius
  • Patent number: 9822652
    Abstract: 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: Grant
    Filed: July 3, 2012
    Date of Patent: November 21, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventors: Roger Sjoqvist, Hakan Jakobsson, Dan Gustafsson
  • Patent number: 9816439
    Abstract: A gas turbine structure includes a first housing and a second housing, one of the first and second housings being located around the other of the first and second housings such that a core flow passage is obtained between the first and second housings. The gas turbine structure further includes an elongate structural member extending in a structural member direction from the first housing to the second housing and the gas turbine structure further includes a fairing circumferentially enclosing at least a portion of the structural member.
    Type: Grant
    Filed: May 16, 2011
    Date of Patent: November 14, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventors: Harald Söderlund, Andreas Borg
  • Patent number: 9803551
    Abstract: The invention concerns a method for manufacturing of a gas turbine engine component (37) comprising an outer ring structure (42, 47), an inner ring structure (41), and a plurality of circumferentially spaced elements (46, 46a, 46b) extending between the inner ring structure (41) and the outer ring structure (42), wherein a primary gas channel for axial gas flow is defined between the elements (46, 46a, 46b), and wherein the component (37) has an inlet side for gas entrance and an outlet side for gas outflow. The invention is characterized in that the method comprises the step of machining a one-piece metal blank as to form a one-piece part (47) comprising: a portion (46b) of each of said elements (46), wherein said portion (46b) relates to a portion of an extension length of the elements (46) between said ring structures (41, 42); and a ring-shaped member (42) that connects said element portions (46b) and that is intended to form part of one of the ring structures.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: October 31, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventors: Lars-Olof Hellgren, Olof Lewin, Kent Holmedahl
  • Patent number: 9797312
    Abstract: A supporting structure for a gas turbine engine includes an inner ring, an outer ring, and a plurality of circumferentially spaced, load carrying radial elements connecting the inner and outer rings. The radial elements have an airfoil shape with a leading edge directed towards the inlet side of the supporting structure, a trailing edge directed towards the outlet side of the supporting structure, and two opposite sides connecting the leading edge and the trailing edge. At least one of the radial elements includes a gas passage arrangement configured to lead a separate bleeding gas flow from the supporting structure. The gas passage arrangement includes a radially extending gas channel arranged inside the radial element and at least one opening in communication with the gas channel. The at least one opening is arranged at one of the two opposite sides of the radial element.
    Type: Grant
    Filed: May 2, 2012
    Date of Patent: October 24, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventors: Goran Johnsson, Rickard Samuelsson
  • Patent number: 9765648
    Abstract: 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 a primary gas channel for axial gas flow is defined between the elements (22), wherein the component (27) has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure (23) positioned internally of the inner ring (20) for transferring loads between said elements (22) and a bearing structure (24) for a turbine shaft (11) positioned centrally in the component (27), wherein the annular load transfer structure (23) extends circumferentially along at least a part of an inner side of the inner ring (20) and inwards in a radial direction of the component (27), wherein the annular load transfer structure (23) has a first portion (23a) and a second portion (23b), and wherein the first portion (23a) is located closer to the inner ring (20) t
    Type: Grant
    Filed: December 8, 2011
    Date of Patent: September 19, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventor: Fredrik Kullenberg
  • Patent number: 9689312
    Abstract: 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: Grant
    Filed: December 22, 2011
    Date of Patent: June 27, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventor: Roger Sjöqvist
  • Patent number: 9670789
    Abstract: A composite guide vane for a gas turbine structure is adapted to extend in a guide vane direction from a first housing towards a second housing of the gas turbine structure. The guide vane includes a guide vane length in the guide vane direction and the guide vane includes a first attachment portion with at least one first opening for attachment of the guide vane to the first housing. The first opening extends in a first opening direction which forms an angle with the guide vane direction. The guide vane includes a cover portion including a first material and a core portion which is at least partially enclosed by the cover portion.
    Type: Grant
    Filed: March 14, 2011
    Date of Patent: June 6, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventors: Niklas Jansson, Robert Reimers
  • Patent number: 9435215
    Abstract: A gas turbine structure includes a guide vane. The gas turbine structure (further includes a first housing and a second housing and the guide vane extends from the first housing to the second housing. The guide vane includes a leading edge and a trailing edge and the guide vane extends from the leading edge to the trailing edge along a mean camber line. The guide vane includes a first attachment structure, a first fastening arrangement and a second fastening arrangement. Moreover, the first attachment structure includes a stiffening member extending over at least a portion of a circumference of the first housing. Furthermore, the stiffening member includes a stiffening member center point as measured along the mean camber line.
    Type: Grant
    Filed: March 14, 2011
    Date of Patent: September 6, 2016
    Assignee: GKN Aerospace Sweden AB
    Inventors: Niklas Jansson, Robert Reimers
  • Patent number: 9228446
    Abstract: A gas turbine engine component includes a ring element and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. At least one of the vanes is made of a composite material. The at least one composite vane is fastened to the ring element. The component further includes first and second wall portions that are fixed in relation to the ring element and arranged on opposite sides of the composite vane. At least a first hole extends through the first wall portion, the composite vane and the second wall portion. The first hole is adapted to receive a first insertion member. The component is arranged such as to, with regard to the first hole, provide a tight fit for the first insertion member in the first wall portion as well as in the composite vane and to provide a loose fit with a radial play in the second wall portion.
    Type: Grant
    Filed: October 27, 2009
    Date of Patent: January 5, 2016
    Assignee: GKN Aerospace Sweden AB
    Inventors: Rickard Samuelsson, Robert Reimers
  • Publication number: 20150227659
    Abstract: A life consumption of a component in a machine may be predicted. Load data may be received from a load session of said machine. A plurality of parameter sets may be accessed, each associated with a critical point of said component, which point is considered to have critical life consumption. For each critical point, life consumption may be calculated using a life consumption calculation model receiving said load data and said parameter sets as input. By selecting a plurality of critical points on the component, a more complete view is presented of how the different parts of the component are affected by the load session.
    Type: Application
    Filed: June 19, 2012
    Publication date: August 13, 2015
    Applicant: GKN Aerospace Sweden AB
    Inventors: Magnus Andersson, Anders Larsson