A turbine component is configured to be cooled by structured porosity cooling. The component includes: a wall; a contiguous porous layer that is part of the wall; a first zone defined in the porous layer such that it has a first structured porosity, and a second zone defined in the layer such that it has a second structured porosity. The first structured porosity is different from the second structured porosity.

A coated article, comprising an article having at least one surface having disposed thereupon an oxidation resistant coating comprising at least two constituents to form a composition, a first constituent comprising at least one thermal expansion component comprising at least about 10% by volume to up to about 99% by volume of the composition, a second constituent comprising at least one oxygen scavenger comprising at least about 1% by volume to up to about 90% by volume of the composition.

A device for masking the inner periphery of a disc of a turbine engine generally includes a lower element, an upper element, and an elastic annular seal. The lower element, the upper element, and the elastic annular seal are coaxial, the elastic annular seal arranged longitudinally between the lower element and the upper element. The seal generally includes a lower annular part bearing radially and internally against the lower element, and an upper annular part bearing radially and internally against the upper element. The lower part and the upper part are connected to one another by an annular central part forming a return element. The elastic annular seal is configured to bear longitudinally, radially, and externally against each longitudinal end of said inner periphery of the disc to mask said inner periphery, and a clamping system capable of clamping the seal between the lower element and the upper element.

An apparatus and method for an engine component having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a plurality of circumferentially spaced airfoils rotatable about a centerline defining an axial direction, each airfoil comprising an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip along a span-wise direction to define a span length; wherein each of the airfoils have an unguided turning angle to stagger angle ratio defined with respect to a percentage of the span length.

The present disclosure provides a method of multi-objective and multi-dimensional online joint monitoring for a nuclear turbine. The method includes: obtaining first temperature monitoring data of the nuclear turbine by performing online thermal monitoring on a rotor, a valve cage and a cylinder of the nuclear turbine under quick starting-up; obtaining second temperature monitoring data of tightness of a flange association plane of the cylinder of the nuclear turbine by performing online thermal monitoring on the tightness of the flange association plane; obtaining operation monitoring data of a shafting vibration of a rotor and bearing system of the nuclear turbine by performing online safety monitoring on the shafting vibration of the rotor and bearing system; and optimizing operation and maintenance control of the nuclear turbine according to at least one type of monitoring data among the first temperature monitoring data, the second temperature monitoring data and the operation monitoring data.

A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arranged on a side (162) of a respective platform. Groove (160) is defined by a radially-outward surface (168) at an underside of the platform and a surface (170) extending with a tangential component (T) toward radially-outward surface (168). A seal and damper member (152) is disposed in groove (160), where the body of seal and damper member has adjoining surfaces (190, 188) configured to respectively engage, in response to a camming action, with the surfaces (168, 170) that define the axially-extending groove. The camming action being effective to produce an interference fit of the seal and damper member (152) with the side of the respective platform (162) and an opposed side (163) of an adjacent platform.

Disclosed are systems and methods to bore or tunnel through various geologies in an autonomous or substantially autonomous manner including one or more non-contact boring elements that direct energy at the bore face to remove material from the bore face through fracture, spallation, and removal of the material. Systems can automatically execute methods to control a set of boring parameters that affect the flux of energy directed at the bore face. Systems can further automatically execute the methods to: monitor, direct, maintain, and/or adjust a set of boring controls, including for example a standoff distance between the system and the bore face, a temperature of exhaust gases directed at the bore face, a removal rate of material from the bore face, and/or a thermal or topological characterization of the bore face during boring operations.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

The austenitic heat resistant steel of the embodiment contains: 24 to 50% by mass of Ni, 5 to 13% by mass of Cr, 0.1 to 12% by mass of Co, 0.1 to 5% by mass of Nb, 0.1 to 0.5% by mass of V, 1.90 to 2.35% by mass of Ti, 0.01 to 0.30% by mass of Al, 0.001 to 0.01% by mass of B, 0.001 to 0.1% by mass of C, and the balance being Fe and inevitable impurities.

An intershaft seal assembly for use between an inner shaft and an outer shaft rotatable within a turbine engine is presented. The seal assembly includes a sealing ring, an inner ring, and a pair of end rings. The sealing ring further includes a plurality of asymmetric ring segments whereby each asymmetric ring segment further includes a vertical flange and a pair of horizontal flanges extending from the vertical flange in a non-symmetric arrangement. The non-symmetric seal geometry provides an axial force balance thereby reducing wear and increasing seal life. The sealing ring is disposed about the inner ring. The inner ring includes a plurality of ridges that engage the asymmetric ring segments so as to prevent rotation of the asymmetric ring segments with respect to the inner shaft. The end rings are disposed about the sealing ring and the inner ring. The horizontal flanges separately contact the end rings so that the vertical flange extends from and between the end rings in the direction of the outer shaft. A non-contact seal is formed between an outer sealing surface along the vertical flange and an inner sealing surface along the outer shaft.