A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The bulkhead includes a plurality of impingement cooling rings. Each impingement cooling ring of the plurality of impingement cooling rings includes a plurality of impingement cooling holes extending through the bulkhead. The combustor further includes a heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel. The heat shield panel further includes a radial portion between a perimeter and an opening, with respect to an opening center axis, which is free of penetrations. The plurality of impingement cooling holes of each of the plurality of impingement cooling rings are directed toward the radial portion of the heat shield panel.

Combustor panels of gas turbine engines and gas turbine engines are described. The combustor panels include a hot side configured to be exposed to combustion within a gas turbine engine, a cold side opposite the hot side of the combustor panel, the cold side configured to receive cooling flow thereon, and a peak-valley gridded pattern formed on the cold side, the peak-valley gridded pattern comprising a plurality of recessed cells arranged in a grid pattern, with each recessed cell having a peak, angled sidewalls, and an effusion hole located at a bottom of the angled sidewalls.

A gas turbine engine component includes a first surface and a second surface. The component further includes a dilution hole defined by the first surface and the second surface. The component further includes a first effusion hole and a second effusion hole each having an inlet defined by the second surface and an outlet defined by the first surface such that the outlet of the first effusion hole is located nearer to the dilution hole than the outlet of the second effusion hole.

A gas turbine engine component includes a hot side surface that is configured for exposure to a hot gas flow path, a second surface that is opposite the hot side surface and not exposed to the hot gas flow path, and an effusion cooling aperture positioned along the hot side surface. The effusion cooling aperture includes a recessed portion including a void area beginning at the hot side surface and extending inwardly therefrom, a forward surface, an entirety of which is angled at 90 degrees or greater than 90 degrees with respect to the hot side surface, defining a forward end of the recessed portion, an inward surface, angled with respect to the hot side surface, and connecting the forward surface to the hot side surface, and an overhang portion connected with the hot side surface and extending aftward from the forward surface and over the void area.

A turbine component has a plurality of cooling passages each extending through a body of a structure between opposite hot and cold surfaces of the structure. According to one embodiment, at least one of the cooling passages includes a plurality of upstream paths defining respective inlet openings on the cold surface and merging into a number of downstream paths defining respective outlet openings on the hot surface.

The present disclosure relates to apparatuses and methods that are useful for one or more aspects of a power production plant. More particularly, the disclosure relates to combustor apparatuses and methods for a combustor adapted to utilize different fuel mixtures derived from gasification of a solid fuel. Combustion of the different fuel mixtures within the combustor can be facilitated by arranging elements of the combustor controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel mixtures.

An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.

A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

Provided are a combustor nozzle, a gas turbine combustor, a gas turbine, a cover ring, and a combustor nozzle manufacturing method. The combustor nozzle includes: a nozzle body provided with a fuel flow passage; a cover ring that is disposed on an outer side of the nozzle body so as to form air flow passages that allow air to jet out toward a front side; and fuel injection nozzles that are provided in a leading end part of the nozzle body at predetermined intervals in a circumferential direction and extend through the cover ring so as to be able to inject fuel from the fuel flow passage toward the front side. The cover ring has an outer circumferential surface cover that covers an outer circumferential surface of the nozzle body, a leading end surface cover that covers a leading end surface of the nozzle body, and a plurality of inclined flow passages that extend through the leading end surface cover in a thickness direction and are inclined in a predetermined direction relative to a direction of a central axis.

A combustor panel having a plurality of cooling flow paths formed between the outer surface and the inner surface of the combustor panel. The cooling flow paths have inlets that open at the outer surface and introduce a cooling medium into their interior, and outlets that open at the inner surface and discharge the cooling medium flowing through their interior. Among the plurality of cooling flow paths, each of plurality of cooling flow paths extending from a position along the edge of an aperture of the combustor panel forms an aperture-vicinity flow path. Among the plurality of aperture-vicinity flow paths, each of the aperture-vicinity flow paths for which the inlet is formed closer to the aperture than the outlet forms an aperture-side inlet flow path. The number of the aperture-side inlet flow paths is greater than one-half of the all of the aperture-vicinity flow paths.