A tool for simultaneous local stress relief of each of a multiple of linear friction welds includes a columnar track defined along an axis, the columnar track having a helical slot; and a support structure engaged with the helical slot to translate and rotate a heat treat fixture portion along the axis.

A gas turbine engine includes a high pressure compressor disposed about a central longitudinal axis, a combustor, and a diffuser case. The diffuser case includes an outer ring providing a first platform and an inner ring providing a second platform. The first platform and the second platform are axially between the high pressure compressor and the combustor with respect to the central longitudinal axis. A plurality of circumferentially spaced struts extend radially from the first platform to the second platform and each include first and second circumferential sides. A plurality of heat shields are disposed on a leading edge defined at a forward end of a respective one of the plurality of struts.

A ceramic matrix composite (CMC) center body may be positioned around an austenitic nickel-chromium-based superalloy attachment ring. The attachment ring may be integrally formed with a turbine engine case. The attachment ring may have a greater coefficient of thermal expansion than the center body. A plurality of pins may be inserted through apertures in the center body and coupled to the attachment ring. The pins may slide within the apertures, allowing the attachment ring to expand without applying a load on the center body.

Turbine engine components are provided that have a repaired thermal barrier coating, along with their methods of formation and repair. The turbine engine component includes a thermal barrier coating on a first portion of a surface of a substrate; a repaired thermal barrier coating on a second portion of the surface of the substrate; and a ceramic coat on the outer bond coat. The thermal barrier coating includes an inner bonding layer and a first ceramic layer, with the inner bonding layer being positioned between the substrate and the first ceramic layer. The repaired thermal barrier coating generally includes an inner bond coat on the surface of the substrate and an outer bond coat on the inner bond coat. The inner bond coat is formed from a cobalt-containing material, while the outer bond coat is substantially free from cobalt.

An additively manufactured attritable engine includes a compressor section, a combustion section, a turbine section, and an engine case wall, which surrounds the compressor section, the combustion section, and the turbine section. The engine case wall includes a first cavity embedded in the engine case wall that defines an injector that is in fluid communication with the combustion section. The engine case wall includes at least one second cavity embedded within the engine case wall and defines at least one cooling channel that is in thermal communication through the engine case wall with the injector.

A bladed rotor comprising a rotor disk (12) presenting two front faces (14, 15) and an outer peripheral face (16), sockets (18) being provided in the outer peripheral face (16) and opening out into at least one of the front faces (14, 15). The rotor (10) comprising blades (30), each having a root (32) whereby the blade is fastened in a socket (18), an end face (31) of the root being substantially level with the front face (14) of the disk when the blade is fastened in the socket. A coating layer (40) is deposited on the disk (12) so as to cover both at least a portion of the front face (14) of the disk and at least a portion of the end face (31) of the root (32).

The present invention provides a Cr-rich cathodic arc coating, an article in turbine blade coated with the chromizing over cathodic arc coating, and a method to produce the coating thereof. The Cr-rich cathodic arc coating in the present invention comprises a cathodic arc coating and a diffusion coating deposited atop the cathodic arc coating to enforce hot corrosion resistance. The hardware coated with the chromizing over cathodic arc coating in the present invention is reinforced with superior-hot corrosion resistance. The present invention further provides a novel method for producing the chromizing over cathodic arc coating by re-sequencing coating deposition order. The method in the present invention is efficient and cost-reducing by eliminating some operations, e.g., DHT and peening, between the cathodic arc coating and the diffusion coating. The hot corrosion resistance in the present invention results from the high Cr content in the surface of the coating.

The present disclosure provides an assembly for a gas turbine engine. The assembly may comprise a tierod, a bearing mounting ring, and a joint coupling the tierod to the bearing mounting ring. The joint may be configured to increase a volume of a bearing compartment on an inner surface of the bearing mounting ring. A coefficient of thermal expansion of the bearing mounting ring may be substantially the same as the coefficient of thermal expansion of the tierod.

An airfoil has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.70-0.83 inch (17.8-21.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.34-0.45 inch (8.5-11.5 mm). The airfoil element includes at least three of a first mode with a frequency of 374815% Hz, a second mode with a frequency of 641615% Hz, a third mode with a frequency of 1441815% Hz, a fourth mode with a frequency of 1741715% Hz, a fifth mode with a frequency of 1932615% Hz and a sixth mode with a frequency of 2664815% Hz.

The present invention relates to a method for producing and/or repairing wear-stressed recesses or openings on components (22) of a turbomachine, especially of elements of a flow passage boundary, and also to corresponding components, wherein the method comprises: producing an at least two-layer molded repair part (15), one layer (2) of which is formed by an Ni-solder and a further layer (3) of which is formed from a mixture of an Ni-solder (4) and hard material particles (5) of hard alloys on a base of cobalt or nickel and which at least partially has an outer shape which is complementary to the inner shape of the recess (20) or opening which is to be repaired, inserting the molded repair part (15) into the recess (20) or opening and at least partially heat-treating the component (22) for soldering the molded repair part (15) onto the component.