Abstract: The present disclosure relates to a combustor assembly for a gas turbine engine. The combustor assembly comprises a combustor liner, a combustor head, a cowl and a fastener. The combustor liner and the cowl define a cavity. The combustor liner has an integral lug that extends into the cavity from a wall of the combustor liner. The fastener extends into the combustor liner lug to fasten the combustor head to the combustor liner.

Abstract: There is disclosed a method of manufacturing a component. The method comprises melting and fusing powder in layers from a build plate to form the component and a disposable support structure, heat treating the component; and removing the support structure. Each layer of the support structure and the component are formed such that there is at least a 10-micron gap between them, to ensure that the component and the support structure are not fused together.

Abstract: Disclosed is an apparatus for the additive manufacture of a component comprising a substantially annular bed for supporting the component, a powder depositor, an energy beam source for emitting a beam of energy towards a beam target location, and control means for adjusting the beam target location. The apparatus is configured to provide rotation of the beam target location and/or the powder depositor relative to the bed, the relative rotation being about a rotational axis. Also disclosed are a method for additive manufacture, a gas turbine engine, and an aircraft.

Abstract: The present relates to combustor apparatus for a gas turbine engine comprising a bulkhead (34) an inner support ring (70) and an outer support ring (84) at end upstream end thereof. The bulkhead (34) has an inner surface (40), when in use is provided on an internal surface of a combustor (16) and exposed to combustion products and an outer surface (41) provided on an external surface of the combustor when in use; an inner mating feature to cooperate with the inner support ring (70); and an outer mating feature to cooperate with the outer support ring (84). In use, the inner and outer mating features prevent axial motion of the bulkhead relative to the inner (70) and outer (84) support rings.

Abstract: A combustion chamber comprising a plurality of circumferentially arranged cassette segments coupled to a combustor head at one end and a wall section at the other end, each cassette segment extending the full length of the combustion chamber, and wherein the combustor head has an annular tongue structure on a mating surface, the tongue structure engages with a groove portion present in each of the cassettes so that when assembled the groove portions in the each of the plurality of cassette segments forms a substantially continuous groove.

Abstract: An igniter seal arrangement for a combustion chamber. The combustion chamber has a wall having first surface and second surfaces. A boss projects from the first surface, and has a platform on its remote end. The platform has an inner surface spaced from the first surface of the wall to define a chamber between the first surface of the wall and the inner surface of the platform. The platform has an outer surface facing away from the first surface of the wall and an aperture extends through the wall from the outer surface of the platform of the boss to the second surface. First and second L-shape rails extend from the platform and a sealing member has a first edge and a second edge locatable between the outer surface of the platform and the first and second L-shape rails and the sealing member has an aperture to receive an igniter.

Abstract: The present relates to combustor apparatus for a gas turbine engine comprising a bulkhead (34) an inner support ring (70) and an outer support ring (84) at end upstream end thereof. The bulkhead (34) has an inner surface (40), when in use is provided on an internal surface of a combustor (16) and exposed to combustion products and an outer surface (41) provided on an external surface of the combustor when in use; an inner mating feature to cooperate with the inner support ring (70); and an outer mating feature to cooperate with the outer support ring (84). In use, the inner and outer mating features prevent axial motion of the bulkhead relative to the inner (70) and outer (84) support rings.

Abstract: An igniter seal arrangement for a combustion chamber. The combustion chamber has a wall having first surface and second surfaces. A boss projects from the first surface, and has a platform on its remote end. The platform has an inner surface spaced from the first surface of the wall to define a chamber between the first surface of the wall and the inner surface of the platform. The platform has an outer surface facing away from the first surface of the wall and an aperture extends through the wall from the outer surface of the platform of the boss to the second surface. First and second L-shape rails extend from the platform and a sealing member has a first edge and a second edge locatable between the outer surface of the platform and the first and second L-shape rails and the sealing member has an aperture to receive an igniter.

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear.

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT).

Abstract: A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear.