Abstract:
The present invention provides a turbofan engine including leading edge erosion protection for composite stator vanes contained therein. The composite stator vanes are defined by a leading edge, a trailing edge, a concave surface and a convex surface. The vanes are generally formed of a graphite fiber and an aramid fiber braided preform that is laminated with an epoxy matrix resin or other high temperature matrix resin. A wire mesh screen is embedded during a molding process into an outermost surface of the leading edge of the epoxy matrix resin. A tapering erosion protection layer comprised of an erosion protective material is applied to the wire mesh screen at the leading edge of the composite stator vane an aids in protecting the leading edge of the stator vane from debris and contaminants, including operational fluids, dust, and sand that may be carried in an air stream passing therethrough the turbofan engine, as well as an erosive operational environment.
Abstract:
A gas turbine part comprises a superalloy metal substrate, a bonding underlayer formed on the substrate and comprising an intermetallic compound of aluminum, nickel, and platinum, and a ceramic outer layer anchored on the alumina film formed on the bonding underlayer. The bonding underlayer essentially comprises an Ni—Pt—Al ternary system constituted by an aluminum-enriched α-NiPt type structure, in particular an Ni—Pt—Al ternary system having a composition NizPtyAlx in which z, y, and x are such that 0.05≦z≦0.40, 0.30≦y≦0.60, and 0.15≦x≦0.40.
Abstract:
An erosion resistant protective structure for a turbine engine component comprises a shape memory alloy. The shape memory alloy includes nickel-titanium based alloys, indium-titanium based alloys, nickel-aluminum based alloys, nickel-gallium based alloys, copper based alloys, gold-cadmium based alloys, iron-platinum based alloys, iron-palladium based alloys, silver-cadmium based alloys, indium-cadmium based alloys, manganese-copper based alloys, ruthenium-niobium based alloys, ruthenium-tantalum based alloys, titanium based alloys, iron-based alloys, or combinations comprising at least one of the foregoing alloys. Also, disclosed herein are methods for forming the shape memory alloy onto turbine component.
Abstract:
The present invention provides a turbofan engine including leading edge erosion protection for composite stator vanes contained therein. The composite stator vanes are defined by a leading edge, a trailing edge, a concave surface and a convex surface. The vanes are generally formed of a graphite fiber and an aramid fiber braided preform that is laminated with an epoxy matrix resin or other high temperature matrix resin. A wire mesh screen is embedded during a molding process into an outermost surface of the leading edge of the epoxy matrix resin. A tapering erosion protection layer comprised of an erosion protective material is applied to the wire mesh screen at the leading edge of the composite stator vane an aids in protecting the leading edge of the stator vane from debris and contaminants, including operational fluids, dust, and sand that may be carried in an air stream passing therethrough the turbofan engine, as well as an erosive operational environment.
Abstract:
A rotating blade body is provided that can restrain vibrations of rotating blades effectively. The rotating blade body comprises a rotor disc, a plurality of rotating blades being assembled so as to extend from the outer circumference of the rotor disc in a radial pattern, and sealing pins extending along the direction of the rotating shaft in the gaps between the platforms of the rotating blades being adjacent in a circumferential direction. The sealing pins have a through-hole made therein, penetrating axially from one end surface to the other end surface.
Abstract:
The present invention relates to a method of repairing a Ni-based alloy part having an undercoat layer and a topcoat layer stacked on a Ni-based alloy base when the topcoat layer is damaged, comprising the steps of removing a peeled-off portion of the damaged topcoat layer and a denatured portion of the undercoat layer corresponding to the peeled-off portion, forming another undercoat layer by applying spraying to an opening portion of the undercoat layer in the atmosphere at a spray particle speed of 300 m/s or more and a base-material temperature of 300° C. or less, and forming another topcoat layer in the peeled-off portion of the topcoat layer
Abstract:
In a fluid transfer device (10) that includes a housing (12), a rotor (16) rotatably mounted in the housing (12) and having a bore (24) and at least one piston (30) slidingly mounted in the bore (24), a port plate (42) that includes a body portion (44) mountable in the housing (12) and formed from a first material and a wear layer (56) formed of a second material, different from the first material, attached to the body portion (44) and adapted to contact the rotor (16). Also a fluid transfer device (10) including such a port plate (42).
Abstract:
A rotor (10) for a thermal machine, in particular a steam or gas turbine, includes a plurality of rotor disks (12, 13, 14) which are arranged one behind the other in the rotor axis (11) and are welded to one another, at least one first rotor disk (13), which is arranged in a section of the rotor (10) which is subject to particularly high thermal loads, including a nickel-base alloy which is able to withstand high temperatures and is welded to at least one second, adjacent rotor disk (12, 14), which includes a steel which is able to withstand high temperatures. In a rotor (10) of this type, accurate testing of the welded joints located in the high-temperature region is achieved by nondestructive testing by virtue of the fact that a first rotor ring (15, 16) of a steel which is able to withstand high temperatures is inserted between the first and second rotor disks (13 and 12, 14), which first rotor ring (15, 16) on one side is welded to the second rotor disk (12, 14) and on the other side is joined to the first rotor disk (13) via an encircling weld seam (21, 21′, 26).
Abstract:
Vapour turbine operating with geothermal vapours containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of sealing laminas made of a nickel alloy containing a quantity of nickel ranging from 54% to 58% by weight to avoid the washing of the geothermal vapours, maintaining a high useful life of the series of sealing laminas and vapour turbine.
Abstract:
An overlay coating for articles used in hostile thermal environments. The coating has a predominantly gamma prime-phase nickel aluminide (Ni3Al) composition suitable for use as an environmental coating and as a bond coat for a thermal barrier coating. The coating has a composition of, by weight, at least 6% to about 15% aluminum, about 2% to about 5% chromium, optionally one or more reactive elements in individual or combined amounts of up to 4%, optionally up to 2% silicon, optionally up to 60% of at least one platinum group metal, and the balance essentially nickel. A thermal-insulating ceramic layer may be deposited on the coating.
Abstract translation:用于敌对热环境中的物品的覆盖涂层。 该涂层主要具有适合用作环境涂层和用作热障涂层的粘合涂层的γ初始相铝酸镍(Ni 3 Al 3 Al)组合物。 该涂层具有按重量计至少6%至约15%的铝,约2%至约5%的铬,任选的一种或多种反应性元素的组合物,其个体或组合量可达4%,任选至多2 %硅,任选至多60%的至少一种铂族金属,余量基本上为镍。 绝热陶瓷层可以沉积在涂层上。