Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.

Abstract: A device for determining a distance to a surface of a workpiece includes an arrangement for emitting an energy beam towards the surface. The device includes a contact member with a first surface configured to contact the surface of the workpiece and a second surface facing the energy beam emitting means. The energy beam emitting arrangement is arranged for directing the energy beam to the second surface of the contact member.

Abstract: An outlet nozzle for a jet engine has a gas intake and a gas outlet, at least one opening being provided through the nozzle boundary wall for the injection of a fluid into the nozzle in a direction perpendicular to one plane, for the purpose of controlling the direction of a gas flow from the jet engine so that vectoring occurs substantially tangentially in this plane. A first opening configuration is provided through the nozzle boundary wall on a first side of the nozzle center line and a second opening configuration is provided through the nozzle boundary wall on a second side of the nozzle center line. At least one of said first and second opening configurations has a substantial extension in the axial direction of the nozzle, in order to permit selective injection of the fluid through said opening configuration to a varying extent in the axial direction of the nozzle.

Abstract: An air propeller arrangement for propulsion of a fixed-wing aircraft includes a first air propeller that includes a first hub member and at least a first and a second propeller blade, the first and second blades being configured to contribute significantly to the propulsion and having a substantially equal length. Each of the blades has an inner, root end arranged at the first hub member and an outer, tip end positioned at a distance from the first hub member such that each blade extends in a radial direction from the first hub member. The first and second blades are interconnected at their outer ends. An aircraft provided with such an air propeller arrangement is also provided.

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.

Abstract: In a gas turbine engine at least one vanes is made of a composite material and an end part of the vane is fastened to the ring element by at least a first bracket member arranged in a corner region formed by the vane and a ring element. The first bracket member is fastened to the vane by a first fastening device arranged in association with a first hole extending through the vane. The first bracket member is fastened to the ring element by a second fastening device arranged in association with a second hole extending through the ring element. An opening is arranged in the ring element. A second bracket member at least partly has an angular cross section. The second, angled bracket member is arranged through the opening such as to be positioned on an opposite side of both the vane and the ring element in relation to the first bracket member. The second, angled bracket member is fastened to the first bracket member by the first and second fastening devices.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: The invention relates to an annular gas turbine housing component (15) comprising a plurality of circumferentially spaced first channels (16) for conveying a first gas flow in a first direction and a plurality of circumferentially spaced second channels (17) for conveying a second gas flow in a second direction across the first direction in a crossing position (18) of the first and second channels.

Abstract: 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.

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.

Abstract: 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.

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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.