Abstract:
An array of tile assemblies is fixedly connected to a common waterwall panel to form a refractory liner for an incinerator. Each tile assembly includes a unitary, clip-type, metallic anchor, which is directly welded to the waterwall panel, and a solid refractory tile slidably connected to the anchor through a dovetail locking mechanism. The rear surface of the refractory tile includes a longitudinal rib from which projects a dovetail pin configured to receive the anchor. The longitudinal rib increases the overall thickness of the refractory tile through the region of interconnection with the anchor. In this manner, the anchor is suitably protected by the refractory tile from intense heat which may otherwise cause mechanical failure in the locking mechanism. Additionally, the solid construction of refractory tile both limits the presence of air gaps within the tile assembly and reduces the likelihood of tile fragmentation or cracking.
Abstract:
A refractory ceramic component (10) for a gas turbine engine (100) is employed that is more cost effective than typical components used in the gas turbine engine (100). The refractory ceramic component (10) may include a refractory ceramic liner (12) that is easily replaceable. The refractory ceramic liner (12) may be a unitary construction or made of numerous bricks (15) that are interlocked. The ceramic used is a refractory oxide material.
Abstract:
Eine Vorrichtung zur Einspeisung von Luft in den Feuerraum eines Verbrennungsofens umfasst einen längsgestreckten, mit einer feuerfesten Schutzverkleidung (12) versehenen und zwei Enden aufweisenden Balken (10), durch dessen Inneres mindestens ein Luftverteilrohr (19, 20) verlauft. Längs des Balkens (10) sind mit dem mindestens einen Luftverteilrohr (19, 20) kommunizierend verbundene Luftauslasse ( 17. 18) angeordnet. Der Balken (10) weist Luftleitmittel auf, die in einem oberen Bereich des Balkens (10) zumindest in der Nahe seiner beiden Enden angeordnet sind zur Erzeugung von über je einen Oberflächenbereich (25) des Balkens ( 10) abwärts streichenden Luftschleiern. Durch diese Luftschleier wird die Ablagerung von Schlacke und/oder Flugasche auf dem Balken verhindert.
Abstract:
The invention relates to a metal element (12) for anchoring an anti-erosion coating that is intended to be fastened alone in an isolated manner to a metal wall or assembled with other identical anchoring elements. The anchoring element (12) has an edge (12a) for fastening to said metal wall and an anchoring body firmly attached to the fastening edge (12a) and having an upper edge (12b) that is away from the fastening edge and intended to be covered by a composite material of concrete type. A section of this upper edge (12b), which is not intended to be juxtaposed and assembled with an upper edge of an identical anchoring element, is provided with a delimiting tab (16) in order to delimit a height of composite material that must cover the upper edge (12b) of said anchoring element, said delimiting tab (16) having a delimiting edge (18) that is a predetermined distance away from a plane defined by the upper edge (12b) of the anchoring element.
Abstract:
A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.
Abstract:
An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell and a heat shield. The heat shield includes a base and a plurality of panel rails. The panel rails are connected to the base and extend vertically to the shell. The panel rails include first and second rails. A vertical height of the first rail at a first location is less than a vertical height of the second rail at a second location.
Abstract:
A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.
Abstract:
A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.
Abstract:
A liner panel for use in a combustor of a gas turbine engine includes a substrate with a hot side and a cold side; a bond coat on at least one of the hot side and the cold side of the substrate; and a convective feature on the cold side of the substrate of a material different than a material of the substrate. A wall assembly for use in a combustor of a gas turbine engine includes a shell with a multiple of impingement flow passages; and a liner panel mounted to the shell, where the panel includes a convective feature which faces the shell. A method of cooling a liner panel for a combustor section of a gas turbine engine includes directing an impingement flow towards a convective feature of a liner panel; and directing an effusion flow though the liner panel.
Abstract:
The present invention relates to an insert unit for improving the burning efficiency of gas burners, which contains a burner stone (1) that can be connected to the gas burner, where the burner stone (1) has a flow channel (2), and the burner stone (1) is made of a material containing silicon. The characteristic feature of the invention is that the burner stone (1) is made of a silicon carbide based material with an open porosity of at least 10%, and at least a part of the external delimiting surface (la) of the burner stone (1) and/or at least a part of the internal delimiting surface (1b) of the burner stone (1) is coated with a catalyst layer (3).