A combustor assembly for a gas turbine engine is includes a liner and a combustor dome formed of a ceramic matrix composite material. The combustor dome and liner together define at least in part a combustion chamber. The combustor dome extends along a circumferential direction and defines one or more openings, the combustor dome is configured to receive one or more fuel-air injector hardware assemblies in or through the one or more openings.

A Ni-based alloy comprises nitrides, of which an estimated largest size is an area-equivalent diameter of 12 m to 25 m, the estimated largest size of the nitrides being determined by calculating an area-equivalent diameter D which is defined as D=A.sup.1/2 in relation to an area A of a nitride with a largest size among nitrides present in a measurement field of view area S.sub.0 of an observation of the Ni-based alloy, repeatedly performing this operation for n times corresponding to a measurement field of view number n to acquire n pieces of data of the area-equivalent diameter D, arranging the pieces of data of area-equivalent diameter D in ascending order into D.sub.1, D.sub.2, . . . D.sub.n to calculate a standardized variable y.sub.j, plotting the area-equivalent diameter D and the standardized variable y.sub.j on X and Y axes of an X-Y coordinate system, respectively, to obtain a regression line y.sub.j=aD+b (wherein a and b are constants) to calculating y.sub.j where a cross-sectional area to be predicted S is 100 mm.sup.2, and substituting the obtained value of y.sub.j into the regression line to obtain the estimated largest size of the nitrides.

A method of manufacturing a ceramic matrix composite component may include introducing a gaseous precursor into an inlet portion of a chamber that houses a porous preform and introducing a gaseous mitigation agent into an outlet portion of the chamber that is downstream of the inlet portion of the chamber. The gaseous precursor may include methyltrichlorosilane (MTS) and the gaseous mitigation agent may include hydrogen gas. The introduction of the gaseous precursor may result in densification of the porous preform(s) and the introduction of the gaseous mitigation agent may shift the reaction equilibrium to disfavor the formation of harmful and/or pyrophoric byproduct deposits, which can accumulate in an exhaust conduit 340 of the system.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A burner port block assembly having a refractory block with a central passageway therethrough and a ceramic extension piece disposed at least partially in the central passageway of the refractory block. The extension piece has a distal end, a proximal end, and a sidewall that defines a central passageway extending between the distal end and the proximal end. The central passageway of the refractory block is provided with a first engagement structure and the sidewall of the extension piece is provided with a second engagement structure. Engagement of the first engagement structure with the second engagement structure connects the extension piece to the refractory block. The burner port block assembly may further include at least one ceramic fiber board having a hole therethrough disposed at the distal end of the refractory block and/or a gasket positioned between the refractory block and the extension piece.

A sintered refractory product having the form of a block and consisting of a granulate formed by all the grains having a size larger than 100 m, referred to as coarse grains, and a matrix binding the coarse grains and consisting of the grains having a size smaller than or equal to 100 m, the granulate representing between 45% and 90% by mass of the product, the product having a composition such that, in a mass percentage based on the oxides: Al.sub.2O.sub.3>80%, SiO.sub.2<15%, Na.sub.2O<0.15%, Fe.sub.2O.sub.3<0.05%, CaO<0.1%, the other oxides forming the remainder up to 100%, and the Na.sub.2O content in the matrix being greater than 0.010%, in a mass percentage based on the mass of the product.

Methods for preparing slotted ceramic coatings and the resulting components comprising the same are provided. The methods and products include the incorporation of a coating system comprising a ceramic coating with cooling holes disposed throughout the ceramic coating and slots defined in the thermal barrier coating and disposed in relation to the cooling holes. The resulting ceramic coating has improved resistance to CMAS infiltration and improved compliance resulting in an increased life of the coated component.

A combustor may include a nonmetallic combustor body configured to hold a combustion reaction. The combustor may include and one or more electrodes disposed outside the nonmetallic combustor body and configured to apply electrical energy to the combustion reaction. The combustor may include a power supply operatively coupled to the one or more electrodes.

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO.sub.2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO.sub.2 circulating fluid. Fuel derived CO.sub.2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

A small stove assorted with smokeless combustion of combustible solids/semisolids, a stove core and a shape of briquette are to ensure that a cylindrical briquette stack is quickly ignited in a smokeless state. A section A stove core inner ring and a flame concentrator are made of a selected high-whiteness aluminum silicate fiber with superior thermal insulation/resistance effects, and are processed for, e.g., blocking the micropores inner circumferential surface, and a stove core outer ring is made of cheaper foam glass, foam ceramic or calcium silicate modules. An underlying briquette with a concave top is designed to enable an easy, convenient and fast alignment of vent holes. The overall cross-sectional area of the vent holes is expanded by 30%-50% as compared with the area of the anthracite briquettes with the same diameter, and the inner ring vent holes are mainly expanded.