In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component. The composite skin member can be a CMC material and is used to partially encapsulate the foam core. The gas turbine engine component can take the form of an airfoil member such as a blade or a vane, a combustor liner, etc. A first portion of the composite skin member includes a first surface extending past an edge of the component creating a step approximate an edge section. In another embodiment, composite skin members can be used to form a continuous shape for the edge section such that the foam core forms part of a gas path surface.

Transportable modular coating systems include a first transportable coating module comprising at least one first removable wall, a second transportable coating module comprising at least one second removable wall, wherein the first and second transportable coating modules are joinable when the first and second removable walls are removed, and a plurality of coating components fixed within the first and second transportable coating modules that combine to create a coating operation. The transportable coating module further includes a transportable control module that comprises a control system that operably connects to the plurality of coating components to operably control the coating operation.

Transportable modular coating systems include a first transportable coating module comprising at least one first removable wall, a second transportable coating module comprising at least one second removable wall, wherein the first and second transportable coating modules are joinable when the first and second removable walls are removed, and a plurality of coating components fixed within the first and second transportable coating modules that combine to create a coating operation. The transportable coating module further includes a transportable control module that comprises a control system that operably connects to the plurality of coating components to operably control the coating operation.

A gas turbine engine comprises an engine having a compressor section, and a turbine section. A firewall and accessory pumps are mounted on a downstream side of the firewall. The accessory pumps are driven by electric motors mounted on the firewall on an upstream side of the firewall.

A gas turbine engine comprises an engine having a compressor section, and a turbine section. A firewall and accessory pumps are mounted on a downstream side of the firewall. The accessory pumps are driven by electric motors mounted on the firewall on an upstream side of the firewall.

A sprayable thermal barrier coating powder mixture for a gas turbine engine includes: a dry composition having a low surface area ceramic powder having a median particle size distribution greater than 5 microns and less than 50 microns, and a high surface area ceramic powder having a median particle size distribution smaller than 5 microns, wherein the low surface area ceramic powder makes up at least 50% by weight of the dry composition of the sprayable thermal barrier coating powder mixture.

A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 μm).

A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 μm).

A power generation system comprising a liquid pump section (4) comprising a rotary liquid pump (7) with an impeller in which a working fluid is pressurised and which is driven by a drive shaft (8); an evaporator section comprising an evaporator (9) in which the in the rotary liquid pump (7) pressurised working fluid is at least partly evaporated by addition of heat from a heat source; an expander section (3) comprising a rotary expander (11) with an inlet port (16) and a rotary expander element in which the in the evaporator section at least partly evaporated working fluid is expanded; and a generator section (5) comprising a rotary power generator (13) with a rotor, whereby the expander section (3), the liquid pump section (4) and the generator section (5) are rotably connected in such a manner that relative rotational speed ratios between the rotary expander element of the rotary expander (11), the impeller of the rotary liquid pump (7) and the rotor of the rotary power generator (13) are mechanically upheld, characterised in that the drive shaft (8) which drives the impeller of the rotary liquid pump (7), is configured to be provided with a throttling device allowing a controlled portion (15) of the working fluid entering the rotary liquid pump (7) to pass from the liquid pump section (4) to the expander section (3) and/or the generator section (5).

A method of manufacturing a CMC structure includes infiltrating a porous substrate with a composite material and performing a first densification on the infiltrated porous substrate, forming a first densified porous substrate, wherein the first densification includes techniques selected from the group of techniques comprising photonic curing, photonic sintering, pulsed thermal heating, or combinations thereof.