Abstract: A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated into a surface of the film. The thin film is capable of conforming to a surface of the cooled turbine component and is attached to the surface of the cooled turbine component via a braze material. A method for cooling a turbine component in a turbine engine is also provided.

Abstract: A weld filler is proposed which significantly improves the weldability of some nickel-based superalloys and includes the following constituents (in wt %): 11.2%-15.6% chromium (Cr), 9.6%-11.4% cobalt (Co) 2.4%-5.0%, molybdenum (Mo) 0.1%-3.3%, 4.4%-7.5% tungsten (W), 1.4%-2.6% tantalum (Ta), 3.0%-4.8% aluminum (Al), 0.4-1.0% titanium (Ti), 0.07%-0.08% carbon (C), 0.5%-1.4% hafnium (Hf), trace elements, and remainder nickel. A method is also provided. The method includes providing a nickel-based substrate to weld, applying a ductile weld filler having a closely matched coefficient of thermal expansion to a surface of the substrate, applying heat to melt the weld filler to form molten weld filler, welding the substrate with the weld filler at ambient temperature, and resolidifying the molten weld filler to form a solidified joint material.

Abstract: A cooled turbine component in a turbine engine is provided. The cooled turbine component includes a brazed in heat transfer feature, the brazed in heat transfer feature including a thin film including a heat transfer feature incorporated into a surface of the film. The thin film is capable of conforming to a surface of the cooled turbine component and is attached to the surface of the cooled turbine component via a braze material. A method for cooling a turbine component in a turbine engine is also provided.

Abstract: A static wear seal for an interface between two components is provided. The static wear seal includes a body portion including a receptacle configured to receive an insert portion. The insert portion is disposed within the receptacle. The receptacle is formed within the body portion at a surface of the body portion known to wear due to contact with a turbine component and includes a locking means such that the insert portion is retained within the receptacle. The insert portion is configured to receive wear due to contact with the turbine component. A transition seal assembly for a gas turbine engine including at least two seals wherein one of the two seals is a static wear seal is provided as well as a method to protect a wear surface of a static wear seal sealing an interface between the turbine components.

Abstract: A static wear seal for an interface between two components is provided. The static wear seal includes a body portion including a receptacle configured to receive an insert portion. The insert portion is disposed within the receptacle. The receptacle is formed within the body portion at a surface of the body portion known to wear due to contact with a turbine component and includes a locking means such that the insert portion is retained within the receptacle. The insert portion is configured to receive wear due to contact with the turbine component. A transition seal assembly for a gas turbine engine including at least two seals wherein one of the two seals is a static wear seal is provided as well as a method to protect a wear surface of a static wear seal sealing an interface between the turbine components.

Abstract: A method of welding including: applying a flux having at least a majority weight percent boron to a surface of a superalloy base material; forming a weldment on the surface wherein boron is melted onto the surface and is incorporated into a resulting weld pool and heat affected zone, and wherein incipient melted inter-dendritic material resulting from presence of the boron is available to flow into a crack formed during cooling of the weldment; and heat treating the weldment to diffuse a remaining concentration of the boron in the weldment and heat affected zone to a desired value.

Abstract: A stage (10) of stationary vanes (12) of a gas turbine engine, including: a plurality of stationary vanes disposed in an annular array (14); and an energy damping system (30) having a plurality of connection assemblies (32), each joining respective adjacent stationary vanes. A spring (34) is configured to circumferentially bias respective adjacent stationary vanes, and a damper (36) is configured to oppose relative circumferential movement between the respective adjacent stationary vanes. The connection of the overall assembly disclosed herein allows for the oscillating system to decrease its amplitude over the shortest time period no matter the conditions. This reduces wear compared to underdamped arrangements that do not decrease amplitude as quickly.

Abstract: A stage (10) of stationary vanes (12) of a gas turbine engine, including: a plurality of stationary vanes disposed in an annular array (14); and an energy damping system (30) having a plurality of connection assemblies (32), each joining respective adjacent stationary vanes. A spring (34) is configured to circumferentially bias respective adjacent stationary vanes, and a damper (36) is configured to oppose relative circumferential movement between the respective adjacent stationary vanes. The connection of the overall assembly disclosed herein allows for the oscillating system to decrease its amplitude over the shortest time period no matter the conditions. This reduces wear compared to underdamped arrangements that do not decrease amplitude as quickly.

Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.

Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.

Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion to which a row of vanes is affixed for providing structural support for the vanes in the engine section, and an aft hook extending from an aft side of the main body portion with reference to a direction of air flow through the engine section. The aft hook is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The support ring does not include a forward hook having a flange that extends axially from a forward or aft side of the forward hook with reference to the direction of air flow through the engine section.