The invention regards a gas turbine engine control system and a method for limiting turbine overspeed in case of a shaft failure. The control system includes: an overspeed protection system that activates an activation member in case a shaft failure is detected; a fuel limiting mechanism coupled with the activation member, wherein the fuel limiting mechanism is configured to limit the fuel supply to the gas turbine engine combustor if the activation member is activated; a variable stator vane mechanism which is configured to adjust variable stator vanes of a compressor of the gas turbine engine in their rotational position, the variable stator vanes having a closed position which blocks air flow through the compressor. A connecting fuel line connecting the fuel limiting mechanism and the variable stator vane mechanism is provided, wherein upon activation of the activation member the fuel limiting mechanism pressurizes the connecting fuel line, thereby activating the variable stator vane mechanism to move at least one row of the variable stator vanes into the closed position.

A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly.

A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly.

A gas expander includes a scroll casing, an impeller accommodated in the scroll casing and rotationally driven to a first side in a circumferential direction around a central axis by the gas flowing while expanding from an outside to an inside in a radial direction, a diffuser disposed on a first side in an axial direction with respect to the scroll casing and forming a flow path of the gas discharged from the impeller to the first side in the axial direction and swirling to the first side in the circumferential direction, and a vortex preventer provided in the diffuser, in which the vortex preventer includes a profile rectifying blade portion, which is curved or inclined to a second side in the circumferential direction from the first side toward a second side in the axial direction, at least in a portion of the second side in the axial direction.

An acoustic liner that may be for a turbofan engine may comprise a first sidewall, a second sidewall, wherein the first sidewall and the second sidewall define a plurality of cells disposed therebetween, and a pre-cut septum ribbon comprising a plurality of permeable septum coupled together via a plurality of connecting members, with each one of the plurality of permeable septum being generally in a respective one of the plurality of cells.

A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.

A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.

Example apparatus, systems, and articles of manufacture to control deflection mismatch are disclosed herein. Further examples and combinations thereof include: A deflection limiter comprising an inner shroud segment to support a stator structure, the inner shroud segment including a first end face and a first outer upper portion, the first end face positioned radially inward and aft relative to the first outer upper portion, and an outer shroud segment to support the inner shroud segment, the outer shroud segment including a second end face and a second outer upper portion, the second end face positioned aft relative to the first end face and the second outer upper portion positioned aft relative to the first outer upper portion of the inner shroud segment, the second end face coupled to the first end face of the inner shroud segment and the second outer upper portion coupled to the first outer upper portion.

Example apparatus, systems, and articles of manufacture to control deflection mismatch are disclosed herein. Further examples and combinations thereof include: A deflection limiter comprising an inner shroud segment to support a stator structure, the inner shroud segment including a first end face and a first outer upper portion, the first end face positioned radially inward and aft relative to the first outer upper portion, and an outer shroud segment to support the inner shroud segment, the outer shroud segment including a second end face and a second outer upper portion, the second end face positioned aft relative to the first end face and the second outer upper portion positioned aft relative to the first outer upper portion of the inner shroud segment, the second end face coupled to the first end face of the inner shroud segment and the second outer upper portion coupled to the first outer upper portion.

An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.