A control system for a gas turbine includes a controller. The controller includes a processor configured to receive a plurality of signals from sensors disposed in the gas turbine engine system, wherein the gas turbine system engine comprises a compressor section fluidly coupled to a gas turbine section. The processor is additionally configured to derive a vanadium content in a gas turbine engine fuel based on at least one of the plurality of signals. The processor is also configured to determine if a control curve should be adjusted based on the vanadium content in the gas turbine engine fuel, and if it is determined that the control curve should be adjusted, then deriving an adjustment to the control curve based on the vanadium content, and applying the adjustment to the control curve to derive an adjusted control curve.

An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.

A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets. A sacrificial structure for forming internal cooling passages within a blade outer air seal and a method of cooling an interface between a blade outer air seal and a rotating blade array is also disclosed.

Airfoil assemblies for gas turbine engines are described. The airfoil assemblies include an airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, the airfoil body extending in a radial direction between a first end and a second end, wherein the airfoil defines an internal cavity bounded by interior surfaces of the airfoil body, the airfoil body formed from a high-temperature-material material and a metallic insert member installed within the internal cavity. One or more radially extending ribs are arranged on an exterior surface of the metallic insert member and defining one or more radially extending passages between the exterior surface of the metallic insert member and the interior surface of the airfoil body.

In accordance with one aspect of the present exemplary embodiment, a molten metal pump comprising a refractory material body defining an elongated chamber is provided. The chamber is configured to receive a shaft and impeller assembly. The chamber includes an open top through which the shaft passes and a bottom inlet. The impeller is located in or adjacent the inlet. The body further defines an elongated passage adjacent to the chamber. An opening provides fluid communication between the elongated passage and the elongated chamber. The elongated passage is in fluid communication with a discharge channel configured to direct molten metal at least substantially perpendicular to an elongated axis of the elongated chamber.

Coating systems are provided for positioning on a surface of a substrate, along with the resulting coated components and methods of their formation. The coating system may include a layer having a compound of the formula: A.sub.1bB.sub.bZ.sub.1dD.sub.dMO.sub.6 where: A is Al, Ga, In, Sc, Y, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Fe, Cr, Co, Mn, Bi, or a mixture thereof; b is 0 to about 0.5; Z is Hf, Ti, or a mixture thereof; D is Zr, Ce, Ge, Si, or a mixture thereof; d is 0 to about 0.5; and M is Ta, Nb, or a mixture thereof.

A steam valve includes a housing defining a steam inlet and steam outlet in fluid communication with a valve cavity, and an annular valve seat disposed within the valve cavity. A control valve is configured to selectively engage the valve seat. The steam valve further includes a stop valve configured to selectively engage the valve seat. The steam valve includes a pressure seal head configured to receive the stop valve. The pressure seal head includes an elongated body having a bore extending longitudinally through the body; and a nose piece extending from an end of the elongated body. The nose piece has at least a tapered end portion and a bore extending longitudinally therethrough. The bore of the nose piece is longitudinally with the bore of the elongated body. The nose piece is formed of a first material which has greater erosion properties than a second material forming the elongated body.

An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.

A gas turbine component includes a substrate and a corrosion resistant layer coupled to the substrate. The corrosion resistant layer includes zirconium silicate and is configured to protect the substrate from exposure to a vanadium corrodent.

A fan containment arrangement for a gas turbine engine comprises: a fan containment casing; and a fan track liner radially within the fan containment casing and extending radially inwardly from the fan containment casing to a gas-washed surface delimiting a gas path for a fan. The fan track liner comprises an impact resistant layer formed from titanium or titanium alloy. No greater than about 20% of the radial thickness of the fan track liner is formed from titanium or titanium alloy. The fan track liner comprises first and second cellular impact structures separated from one another by a first septum layer, the first cellular impact structure being the impact resistant layer formed from titanium or titanium alloy, or the impact resistant layer formed from titanium or titanium alloy is a septum layer, separating the first and second cellular impact structures. (FIG. 5)