A seal assembly includes a seal arc segment defining first and second seal supports. A carriage defines first and second support members with the first support member supporting the seal arc segment in a first ramped interface and the second support member supporting the seal arc segment in a second ramped interface such that the seal arc segment is circumferentially moveable with respect to the carriage. The seal assembly includes an anti-rotation interface in which the seal arc segment and the carriage are engaged. The anti-rotation interface restricts circumferential movement of the seal arc segment.

A method comprises discharging from a metal vaporization device a vapor of a metal or a metal precursor to a chemical vapor infiltration device where the chemical vapor infiltration device is in fluid communication with the metal vaporization device. The chemical vapor infiltration device contains a preform containing ceramic fibers. The preform is infiltrated with a metallic coating or a coating of a metallic precursor along with a ceramic precursor coating. The metallic coating and/or the metallic precursor coating and the ceramic precursor coating are applied sequentially or simultaneously.

The present disclosure relates to turbine blades adapted for use in gas turbine engines. In particular, this disclosure is directed to turbine blades that include components made from ceramic matrix composite materials and that incorporate abradable materials.

An embodiment of a system for measuring fuel ignition within a torch igniter for a combustor in a gas turbine engine includes a housing surrounding and defining a combustion chamber, a first glow plug received through the housing, and control circuitry. An innermost end of the first glow plug extends into the combustion chamber while an outermost end opposite the innermost end extends away from the combustion chamber. The control circuitry is connected to the outermost end of the glow plug and is configured to measure a temperature of the innermost end of the glow plug based on electrical resistance of the glow plug. The control circuitry is further configured to determine an operational parameter of the torch igniter based on the temperature.

The invention relates to an axial turbine with a rotating casing and stationary shaft, sections for the assembly thereof, and materials for the manufacture thereof.

A boundary layer turbine (BLT) engine has a housing formed by an outer cylinder a first and a second faceplate, a turbine shaft through the faceplates, a stack of alternating disks and spacers with central holes joined to the turbine shaft leaving an outer combustion zone, an air inlet through the first faceplate, an exhaust port through the second faceplate, a fuel port through the outer cylinder, and an ignition device communicating with the combustion zone. The disks and spacers have openings forming separate intake and exhaust channels parallel to the turbine shaft, one channel channeling air from the air inlet port to spaces between disks, and the other channel channeling exhaust from the combustion zone through the exhaust channel to the exhaust port. Fuel is injected into the combustion zone, the air fuel mixture is ignited, and exhaust products impart torque to the turbine shaft by boundary layer friction.

A seal assembly includes a carbon seal that has a sealing surface. A seal seat has a sealing surface and is positioned for rotation relative to the carbon seal. A diamond-like carbon coating at least partially forms the sealing surface on the seal seat.

An airfoil includes an airfoil section that has a ceramic airfoil wall that defines a suction side and a pressure side. There is an interior cavity in the airfoil section. A rib spans across the interior cavity and connects the suction side and the pressure side. The rib has a thermal conductance element that is configured to conduct heat away from the suction side and the pressure side.

A method of pressure sintering an environmental barrier coating on a surface of a ceramic substrate to form an article is provided. The method includes the steps of etching the surface of the ceramic substrate to texture the surface, disposing an environmental barrier coating on the etched surface of the ceramic substrate. The environmental barrier coating includes a rare earth silicate, and pressure sintering the environmental barrier coating on the etched surface of the ceramic substrate in an inert or nitrogen atmosphere such that at least a portion of the environmental barrier coating is disposed in the texture of the surface of the ceramic substrate thereby forming the article.

A coated component, along with method of forming the same, is provided. The coated component may include a substrate having a surface, a silicon-based bond coating on the surface of the substrate, and an EBC on the silicon-based bond coating. The silicon-based bond coating may include a silicon-phase contained within a refractory phase. The silicon-phase, when melted, is contained within the refractory phase and between the surface of the substrate and an inner surface of the environmental barrier coating. Such a coated component may be, in particular embodiments, a turbine component.