Volvo Aero Corporation

Gknaerospace Sweden Ab

Hans Mårtensson

Martin Nilsson

Carlos Arroyo

Mattias Billson

Fredrik Wallin

Lars Ellbrant

Pieter Groth

A gas turbine engine comprises at least one radially extending bleed passage optionally in fluid communication with at least one generally circumferentially extending plenum. The passage has an upstream inlet in fluid communication with a bleed passage and an outlet for releasing air from the plenum. The upstream leading edge of the inlet or the downstream trailing edge of the inlet has a non-uniform profile.

Gas turbine air bleed arrangement with an inlet

A front centre body (FCB) structure for a geared turbofan engine comprises a plurality of vanes extending across the inlet duct to a low pressure compressor and integrates a heat exchanging arrangement to control the temperature of the gearbox of the turbofan engine.

Heat exchanger integration

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.

Strut and a gas turbine structure comprising the strut

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.

Bleed structure for a bleed passage in a gas turbine engine

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.

Blade for a flow machine

A wheel for a rotating flow machine, comprising a rotor () on which a plurality of blades () are arranged projecting radially from the rotor (), with each blade () having a root () attached to the rotor () and a blade top (). In addition, the wheel comprises a ring () arranged concentrically in relation to the rotor () outside the blade tops () in such a way that the ring () and the blades () overlap each other when the ring and the blades are viewed in a radial direction, which ring () is arranged to be caused to rotate by the blades () when the rotor () rotates. The extent () of the blades () in a radial direction and the internal dimension () of the ring () are matched to each other in such a way that there is a clearance (&#x394;) between each blade top () and the ring () in radial direction when the rotor () is not rotating.

Growing community of inventors

Trollhättan, Sweden

Hans Mårtensson