Gknaerospace Sweden Ab

Volvo Aero Corporation

Roger Sjöqvist

Jan Nilsson

David Russberg

Hakan Jakobsson

Dan Gustafsson

Jan Svensson

Eva Dahl

Sten Johansson

Håkan Jakobsson

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.

Supporting structure for a gas turbine engine

The invention concerns a gas turbine engine component () comprising an outer ring (), an inner ring (), a plurality of circumferentially spaced elements () extending between the inner ring () and the outer ring (), wherein an annular load transfer structure () extends circumferentially along an inner side of the inner ring () and also inwards in a radial direction of the component (). The first portion (), at least along a part of the circumference, is inclined in the radial direction in relation to a second portion (), wherein the two inclined portions () are connected in a connection zone () between the inclined portions (), and wherein a radial and/or axial position of the connection zone () varies along the circumference such that the radial/axial position of the connection zone in a location that circumferentially corresponds to a first element (), i.e. in a first circumferential location (A), is radially and/or axially different from the radial/axial position of the connection zone () in-between the first element () and an adjacent second element (), i.e. in a second circumferential location (B).

Gas turbine engine component

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.

A bearing support structure is provided for installation in a gas turbine engine between radially inner first and second bearings adapted to rotatably support a first and a second rotor, respectively, and a radially outer engine frame. The support structure includes a first annular plate-shaped part and an arrangement for supporting the first bearing at one end thereof and a second annular plate-shaped part and an arrangement for supporting the second bearing at one end thereof. The first and second plate-shaped parts are joined together forming a one-piece unit for installation in the gas turbine engine.

Bearing support structure and a gas turbine engine comprising the bearing support structure

A turbine including a rotor () that is driven by gas and that has a housing () enclosing the rotor. The turbine includes a component () suspended from the housing () that is arranged inside the housing () and at least partially beside the rotor () with respect to the direction () of the gas flow in order to impede any fragments which may come loose from the rotor from penetrating the housing in radial direction.

Growing community of inventors

Trollhättan, Sweden

Roger Sjöqvist