Abstract:
A method for casting comprising: providing a seed (84), the seed characterized by: an arcuate form and a crystalline orientation progressively varying along an arc of the form; providing molten material (123; 360'); and cooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material.
Abstract:
A combustor assembly includes a support structure (29) and at least one combustor liner panel (30) selectively attached to the support structure (29). The combustor liner panel (30) includes an uncooled ceramic portion (40), a cooled ceramic portion (42) and a support (44) that receives the cooled ceramic portion (42).
Abstract:
A gas turbine engine (10) includes an engine casing (11) concentrically disposed around the following: a low pressure compressor; a turbine (26,28); and a high pressure compressor (22) having at least one bleed tube (42) and at least one joint (44,46) proximate to the engine casing (11); and at least one flame prevention device (50) adapted to cover at least a portion of at least one gas turbine engine component (42).
Abstract:
A coating system includes a first work piece (26A), a work piece support (18) for holding the first work piece, a plasma-based coating delivery apparatus (14) configured to apply a coating material to the first work piece in a plasma-based vapor stream, and a first electron gun (20A) configured to direct a first electron beam at the first work piece while the plasma-based coating delivery apparatus applies the coating to the first work piece for heating the first work piece being coated, wherein the first electron gun is configured to direct the first electron beam at a region of the first work piece facing away from the plasma-based coating delivery apparatus.
Abstract:
A method for forming a thermal barrier coating on a combustor panel or a fuel nozzle comprises the steps of: providing a component selected from the group consisting of a combustor panel, a bulkhead heat shield, and a fuel nozzle; optionally depositing a first layer of a metallic alloy onto the component; and depositing a ceramic composition layer using an electron beam physical vapor deposition technique. If the component is formed from a yttrium or other active element doped single crystal superalloy, the first layer may be omitted and the ceramic composition layer may be deposited directly onto a surface of the component.
Abstract:
A thermal barrier coating system for use on a turbine engine component which reduces sand related distress is provided. The coating system comprises at least one first layer of a stabilized material selected from the group consisting of zirconia, hafnia, and titania and at least one second layer containing at least one of oxyapatite and garnet. Where the coating system comprises multiple first layers and multiple second layers, the layers are formed or deposited in an alternating manner.
Abstract:
An apparatus for non-line of sight coating of a part (12) includes a housing (14), a vapor source (20), at least one nozzle (24), and a vacuum pumping system (16). The vapor source (20) produces a vapor cloud (30) into the housing (14) and toward the part (12). The nozzle (24) provides a gas flow to interact with the vapor cloud (30). The vacuum pumping system (16) maintains a pressure within the housing (14).