A combustor includes a nozzle, a burner cylinder surrounding the outer circumference of the nozzle, and an outside flow path cylinder surrounding the outer circumference of a downstream end portion of the burner cylinder. A purge air flow path through which air flows is formed between the inner circumferential side of the outside flow path cylinder and the outer circumferential side of the burner cylinder. A tapered surface is formed in the downstream end portion of the burner cylinder such that the plate thickness of a burner cylinder-forming plate that forms the burner cylinder gradually thins toward the downstream side.

A gas turbine combustion chamber with a double-wall embodiment, having an outer cold combustion chamber wall and an inner hot combustion chamber wall which form an intermediate space, with impingement cooling holes in the outer combustion chamber wall, effusion cooling holes in the inner combustion chamber wall, outer mixing holes in the outer combustion chamber wall, and inner mixing holes in the inner combustion chamber wall. Respectively, one tubular mixing element connects the outer mixing hole and the inner mixing hole, wherein the mixing element includes an inflow opening in its area which is arranged inside the intermediate space. The outer mixing hole has a smaller diameter than the inner mixing hole, and the throughflow surface area of the effusion holes that are adjoining the mixing element is reduced by the difference in surface area between the outer mixing hole and the inner mixing hole.

A method of fabricating a combustor thermal shield comprising a combustor panel, a cooling feature, and an attachment feature, the combustor thermal shield to be used in a gas turbine engine combustor, includes shaping a sheet of material used to form the combustor panel. The method also includes additively manufacturing the cooling feature onto the sheet of material forming the combustor panel. The method also includes attaching the attachment feature to the sheet of material forming the combustor panel. The method also includes curving the sheet of material forming the combustor panel to achieve a curve profile according to a design of the gas turbine engine combustor.

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield having an annular shape. A first groove may be formed circumferentially along an inner surface of the heat shield. A support lock may have a second groove extending radially inward from a distal surface of the support lock. A retention ring may be configured to fit within the first groove of the heat shield and the second groove of the support lock.

The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall, to which combustion chamber tiles are fastened by means of bolts, where in the bolt fastening area in the combustion chamber wall at least one impingement cooling hole is provided, the center axis of which is inclined to the center axis of the bolt and intersects a transition area between the bolt and the combustion chamber tile.

A rotating machine component, particularly a gas turbine combustion component, having at least one part built from a porous material with a plurality of pores, wherein at least a subset of the plurality of pores is at least partly filled with a gas with a composition different from air and/or with a powder, wherein the porous material is a laser sintered or laser melted material in which void local regions form the plurality of pores. The component counter-acts vibrations. A rotating machine or gas turbine engine may have such a component.

A cooled gas turbine engine component includes a wall having a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface. Each aperture includes an inlet portion, a collection chamber, a metering portion, a U-shaped bend portion and a diffusing portion arranged in flow series from the inlet to the outlet. The inlet portion of each aperture is arranged substantially perpendicularly to a surface of the collection chamber. The metering portion of each aperture is arranged to extend longitudinally from a first lateral side of the collection chamber and the diffusing portion of each aperture is arranged at an angle to the second surface. Each outlet has a quadrilateral shape in the second surface of the wall and each outlet is displaced laterally from the metering portion.

A sound attenuator includes part of a plate forming a combustion liner and an acoustic cover defining, in conjunction with this part of the plate, a space on the outer circumferential side of the combustion liner. A restrictor that reduces a gas flow path is provided inside the combustion liner. At least one through-hole penetrating from inside the combustion liner to the space is defined in the part of the plate. At least one of the through-holes in the sound attenuator is present within a region spanning from a position of a minimum restrictor diameter of the restrictor to positions, on an upstream side and a downstream side, at a distance equivalent to a minimum restrictor radius.

Provided is a combustor that has an efficient cooling structure. Also provided is a gas turbine engine that is provided with the combustor. A combustor that is for a gas turbine and that is provided with a combustion liner and with a fuel injection part that is provided to one end of the combustion liner so as to pass through the combustion liner. The combustion liner is provided with an inner liner that forms a combustion chamber inside the combustion liner, with a coolant flow path that is an annular space that is formed outside the inner liner, and with a coolant supply means that supplies hydrogen gas to the coolant flow path. In this combustor, the inner liner that is the combustion chamber is cooled by the hydrogen gas that flows in the coolant flow path.

A method of forming a sprayed coating includes preparing a spray target member having a surface on which openings of first ends of holes are formed, preparing a plurality of masking pins each of which comprises metal, and inserting each of the masking pins into a corresponding one of the holes so that each of the masking pins partially protrudes from the surface. The method also includes applying an adhesive agent for fixing the masking pins to the respective holes, to at least one of the holes or the masking pins, forming a ceramic layer by spraying on the surface of the spraying target member, the ceramic layer comprising a ceramic material, while the masking pins are fixed to the respective holes via the adhesive agent, and removing the masking pins from the holes after the spraying step.