Patents Assigned to GKN AEROSPACE SWEDEN AB
  • Patent number: 9003812
    Abstract: 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: Grant
    Filed: May 8, 2009
    Date of Patent: April 14, 2015
    Assignee: GKN Aerospace Sweden AB
    Inventor: Roger Sjöqvist
  • Publication number: 20150093287
    Abstract: A a titanium alloy can be applied on a substrate by one of melting, welding, and depositing said titanium alloy on said substrate and solidifying said deposited or molten titanium alloy. Further, 0.01-0.4 weight % Boron can be added to said titanium alloy before or during said melting, welding or depositing said titanium alloy on said substrate.
    Type: Application
    Filed: May 16, 2012
    Publication date: April 2, 2015
    Applicant: GKN Aerospace Sweden AB
    Inventors: Robert Pederson, Frank Skystedt
  • Patent number: 8992139
    Abstract: 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.
    Type: Grant
    Filed: May 26, 2009
    Date of Patent: March 31, 2015
    Assignee: GKN Aerospace Sweden AB
    Inventors: Anders Wretland, Tore Hagward
  • Publication number: 20150033759
    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: Application
    Filed: December 22, 2011
    Publication date: February 5, 2015
    Applicant: GKN Aerospace Sweden AB
    Inventor: Roger Sjöqvist
  • Publication number: 20150007570
    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: Application
    Filed: December 20, 2011
    Publication date: January 8, 2015
    Applicant: GKN Aerospace Sweden AB
    Inventors: Lars-Olof Hellgren, Olof Lewin, Kent Holmedahl
  • Publication number: 20140373556
    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: Application
    Filed: December 23, 2011
    Publication date: December 25, 2014
    Applicant: GKN AEROSPACE SWEDEN AB
    Inventors: Egon Aronsson, Per Widstrom, Elinor Magnusson, Johan Thoreus, Christian Lundh
  • Publication number: 20140341730
    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: Application
    Filed: December 8, 2011
    Publication date: November 20, 2014
    Applicant: GKN Aerospace Sweden AB
    Inventor: Fredrik Kullenberg
  • Publication number: 20140294579
    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: Application
    Filed: March 14, 2011
    Publication date: October 2, 2014
    Applicant: GKN AEROSPACE SWEDEN AB
    Inventors: Niklas Jansson, Robert Reimers
  • Publication number: 20140190180
    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: Application
    Filed: May 16, 2011
    Publication date: July 10, 2014
    Applicant: GKN AEROSPACE SWEDEN AB
    Inventors: Harald Söderlund, Andreas Borg