Abstract:
A component for use in a gas turbine engine includes a first section, a second section, and a functionally graded section. The first section is made of a metal material. The second section is made of a ceramic material and/or a ceramic matrix composite material. The functionally graded section is disposed between the first section and the second section.
Abstract:
A solid freeform manufacturing system includes a manufacturing chamber containing a powder based additive manufacturing device. The manufacturing chamber is connected to an environmental control chamber. The environmental control chamber contains environmental control devices including fans, filters, and an inert gas source. An interconnection between the environmental control chamber and manufacturing chamber allows an inert, contaminant free manufacturing environment.
Abstract:
A hybrid airfoil (142) for a gas turbine engine comprises a leading edge portion (148), a trailing edge portion (150) and an intermediate portion (151) between said leading edge portion (148) and said trailing edge portion (150). The leading edge portion (148) is made of a first material, the trailing edge portion (150) is made of a second material, and the intermediate portion (151) is made of a third material. At least two of said first material, said second material and said third material are different materials. A a portion (115) between said leading edge portion and said intermediate portion includes a pocket (127) that receives a non-metallic portion (102A). A connection interface is established between said leading edge portion (148) and said non-metallic portion (102A).
Abstract:
According to one embodiment of this disclosure, a coating includes a plurality of elongated reinforcing materials 56. The coating includes a bond coat 58 in which a first portion of a first elongated reinforcing material is embedded. The coating further includes a ceramic coat 70 adjacent the bond coat in which a second portion of the first elongated reinforcing material is embedded.
Abstract:
A additive manufacturing system (20) includes a containment housing (22) operable to form a containment chamber (34) with a low pressure operating atmosphere and an additive manufacturing build housing (24) within said containment housing (22).
Abstract:
A ceramic turbine component is formed by a process including mixing a ceramic powder with an inorganic binder powder. The powder mixture is then formed into a turbine component that is subsequently densified by transient liquid phase sintering. In an embodiment, the turbine component may be formed by an additive manufacturing process such as selective laser sintering.
Abstract:
An additive manufacturing system comprises a build chamber, a powder bed additive manufacturing device disposed in the build chamber, and a powder contamination detection system. The powder contamination detection system is in communication with an atmosphere in the build chamber.