A method of determining a remaining life in a component and a rotatable machine system are provided. The rotatable machine system includes a plurality of valves coupled in flow communication with a rotatable machine of the rotatable machine system, a plurality of sensors configured to receive operating parameters associated with the rotatable machine and the plurality of valves, and an online valve lifetime counter (OVLIC), including a processor communicatively coupled to the plurality of sensors. The OVLIC is configured to determine a trend of differential temperature across a body of a valve of the plurality of valves, convert the trend of differential temperature to a stress induced into the valve over time, and determine life remaining in the valve based on a total damage of the valve wherein the total damage is a function of creep damage and fatigue damage to the valve.

A flange of a blade root platform is separated from an adjacent edge of the blade by a groove that prevents direct transmission of forces created by the bolted attachment of the platform flange to the adjacent part of the blade and reduces stress concentrations.

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

A method of manufacturing an airfoil includes creating a plurality of cavities separated by a plurality of internal ribs in an airfoil forging. At least one hole is drilled in at least one of the plurality of internal ribs with a waterjet drilling tool. At least one hole extends perpendicularly to a wall of the rib.

A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

A component for a gas turbine engine includes a surface adjacent a flow of hot gases. A plurality of cavities is in a portion of the surface. The plurality of cavities have a first group of cavities with a first cross-section and a second group of cavities with a second cross-section different from the first cross-section. The first and second groups of cavities are arranged such that there is no straight line across the portion of the surface that does not intersect one of the plurality of cavities. A thermal barrier coating is over the surface and fills each of the plurality of cavities.

A device includes two components which are rotationally fixedly operatively connected to one another. One component engages certain regions radially around the other component in an axial direction. Between the components, there is a substantially ring-shaped structural unit by which the rotationally fixed connection is produced. The structural unit includes two elements which extend in a circumferential direction radially between the components. Via the structural unit, there is an interference fit between the radially outer component and the structural unit and between the radially inner component and the structural unit over the entire operating range of the device. The elements bear against one another in the region of their end sides facing toward one another. The coefficient of thermal expansion or the coefficients of thermal expansion of the elements is or are greater than the coefficient of thermal expansion or the coefficients of thermal expansion of the components.

A component for a gas turbine engine includes a surface adjacent a flow of hot gases. A plurality of cavities is in a portion of the surface. The plurality of cavities have a first group of cavities with a first cross-section and a second group of cavities with a second cross-section different from the first cross-section. The first and second groups of cavities are arranged such that there is no straight line across the portion of the surface that does not intersect one of the plurality of cavities. A thermal barrier coating is over the surface and fills each of the plurality of cavities.

A shroud (22) comprises shroud bodies (22) fixed to blade tips of blades (18) mounted to a rotor body to extend in a radial direction, the shroud bodies (22) being disposed adjacent to one another in a circumferential direction, wherein each of the shroud bodies (22) includes a circumferential end surface (27, 28) that includes an abutting end surface where adjacent shroud bodies (22) abut, and an opposing surface (34) where adjacent shroud bodies (22) face one another with a clearance (32) therebetween, the opposing surface (34) being contiguous with the abutting end surface; and an outer surface (24) that includes a radially outward protruding protrusion (40) formed to extend along the opposing surface (34).