A combustor liner panel attachment assembly. The assembly includes a first liner extending from a first end to a second end, and circumferentially to partially define a combustion zone. The assembly also includes a second liner disposed circumferentially adjacent to the first liner. The assembly further includes a radial support having a shoulder in contact with a radially inner surface of each of the first liner and the second liner to radially retain the first liner and the second liner, the radial support allowing the first liner and the second liner to thermally grow axially.

This invention relates to a refractory lining of a tube wall (2) for an incinerator including at least four refractory tiles (3) of ceramic material which are arranged next to and above one another, wherein the tiles at their rear side, which is facing the tube wall (2), are provided with a vertical insertion channel (10) for mounting the tiles upon the holders (7) of the tube wall, wherein a free space (11) is formed between the tiles (3) and the tube wall (2), which space is filled with a curable pouring compound, and wherein a spacer (20) is provided adjacent to four mutually adjoining edges (12) of the at least four refractory tiles (3). Alternative embodiments are characterized by the use of a head bolt, and/or wedge element (50) and/or a flip-element (60).

Embodiments of the disclosure relate to articles, coated chamber components and methods of coating chamber components with a low volatile coating. The low volatile coating can include a rare earth metal-containing layer that coats all surfaces of a component (e.g., a high temperature heater).

A heat shield assembly of a combustion chamber has a supporting structure and heat shield elements arranged on the supporting structure. For fastening, the supporting structure has spring devices fastened therein, into each of which a fastening bolt can be screwed. In order to realize the pre-installation and the later removal of the spring elements contained in the spring device, at a holding sleeve, a contact plate is removably fastened in the holding sleeve on the side facing the heat shield element and a stationary securing plate is arranged on the opposite side.

A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. A mounting assembly attaches the forward end of the liner to the annular dome. The mounting assembly includes a pin extending through the slot and the forward end of the annular dome. The mounting assembly also includes a grommet positioned in an opening in the forward end of the liner. The grommet is also positioned around the pin to protect the liner during operation of the gas turbine engine.

Example apparatus and methods providing for the improved chemical conversion of the combustible components of a gaseous medium are disclosed. In some examples, the apparatus includes a guiding body that guides the flow of the gaseous medium within a reaction chamber of the apparatus. In some examples, the guiding body of the disclosed apparatus is configured to stabilize a residence period of the gaseous medium in the reaction chamber. In some examples, the guiding body results in a flow path of the gaseous medium within the reaction chamber being optimized and/or maximized, and/or results in a short circuit flow of the gaseous medium in the reaction chamber being suppressed. In some disclosed examples, the guiding body causes at least a portion of the flow path of the gaseous medium within the reaction chamber to take the form of a cyclone flow.

A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. Additionally, a heat shield is provided. The heat shield includes an end also received within the slot defined by the annular dome. A mounting assembly attaches the forward end of the liner and the end of the heat shield to the annular dome, such that the forward end of the liner and the end of the heat shield are co-mounted within the slot defined by the annular dome.

A combustor device for a gas turbines engines includes first and a second tubular members telescopically fitted in axially sliding manner to one another with interposition of annular centering and sealing which include at least a centering annular shoulder and a sealing ring arranged coaxial to one another. The sealing ring is axially spaced apart from the centering annular shoulder so that an axial distance between the centering annular shoulder and the sealing ring is greater than a maximum axial movement allowed between the first and said second tubular members.

A process for producing an anti-erosion coating on an inner or outer metal wall of a chamber of a fluid catalytic cracking unit, comprising: (i) the shaping of a honeycomb metal anchoring structure, said anchoring structure being formed from a plurality of strips connected in pairs by joining assembly portions of these strips so as to form a plurality of cells between two adjacent strips, (ii) the fastening of said anchoring structure by welding to said metal wall, so that each cell of the anchoring structure is welded to the wall of the chamber at least at the junctions between the contiguous assembly portions of two adjacent strips, and (iii) the insertion of a composite material into the cells from the metal wall and at least up to the upper longitudinal edge of each strip.

A material which exhibits auxetic characteristics and control of thermal expansion characteristics while experiencing significant stress reduction is disclosed. The material has a repeating pattern of void structures along both lateral symmetry lines and longitudinal symmetry lines.