A method to form a hole in a ceramic matrix composite component may be provided. A monolithic rod may be inserted into a porous ceramic preform. The ceramic preform may be formed into a ceramic matrix composite body that includes the monolithic rod. A portion of the monolithic rod may be removed, leaving a remaining portion in the ceramic matrix composite body. The remaining portion may include walls that define the opening in the ceramic matrix composite body. Alternatively or in addition, a ceramic matrix composite component may be provided. The ceramic matrix composite component may comprise a ceramic matrix composite body that includes a portion of a monolithic rod. The portion of the monolithic rod forms a lining around a hole passing partly or entirely through a length of the monolithic rod.

A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration; and attenuating the component to a desired frequency by forming a plurality of openings in the external metallic shell.

An apparatus includes an electrode assembly comprising a carriage having a plurality of electrode holders, the electrode holders being respectively configured to detachably receive a plurality of electrodes, the electrodes include a plurality of first electrodes and a plurality of second electrodes. The first electrodes are configured for rough machining a workpiece by electric discharging or wire electric discharging to remove material from the workpiece, the second electrodes are configured for finish machining the rough machined workpiece by electric discharging to remove material from the rough machined workpiece.

A method for modifying an aperture in a component, a system for modifying flow through a component, and a turbine component are disclosed. The method includes providing a substrate having at least one aperture having an electrically-conductive surface, providing a deposition device including an ESD torch, the ESD torch including an aperture penetrating electrode including a conductive material, inserting the aperture penetrating electrode at least partially into the aperture, and generating an arc between the aperture penetrating electrode and the electrically-conductive surface to deposit electrode material within the aperture. The system includes the ESD torch removably supported in an electrode holder. The turbine component includes at least one aperture having an electrospark deposited material along an electrically-conductive surface, the electrospark deposited material providing modified fluid flow through the turbine component.

An electrical discharge machining method includes selectively immersing only a portion of a workpiece in an electrical discharge machining liquid such that a machining object portion included in the portion of the workpiece is opposed to an electrode immersed in the electrical discharge machining liquid and applying an electrical discharge machining to the machining object portion by applying a voltage between the electrode and the workpiece in a state where the portion of the workpiece is selectively immersed in the electrical discharge machining liquid.

A stator vane shiplap assembly is provided. The stator vane shiplap assembly may comprise a plurality of stator clusters, coupled together to form an annular shape. Each stator cluster may comprise a shiplap stator shroud and a plurality of stator vanes. The shiplap stator shroud may comprise a female end and a male end, with each end comprising a complimentary forward shiplap surface and outward shiplap surface. In response to a coupling of adjacent shiplap stator shrouds, the female forward shiplap surface and the female outward shiplap surface may form a compound shiplap seal joint with the male forward shiplap surface and the male outward shiplap surface. A feather seal may also be introduced between the coupling of adjacent shiplap stator shrouds.

A method for producing a rotary disk/blisk for a high-pressure compressor or a high-speed turbine and to a corresponding geared turbofan engine. The method involves providing a Ni base alloy comprising, in % by weight, 15.5-16.5 Cr, 14.0-15.5 Co, 4.75-5.25 Ti, 2.75-3.25 Mo. 2.25-2.75 Al, 1.00-1.50 W, as well as optionally 0.0250-0.0500 Zr, 0.0100-0.0200 B, 0.0100-0.0200 C, remainder Ni. The base alloy is shaped by forging to obtain a preform of the disk/blisk, the final contour thereof being produced by electrical discharge machining or electrochemical machining.

The invention relates to a method for producing a mistuning component. The method comprises the following steps: a) producing a container (34) having at least one chamber (36); b) producing a lid (32, 32′); c) inserting at least one impulse element into the chamber (36); d) joining the lid (32, 32′) and the container (36), wherein joining is carried out by soldering/brazing.

An apparatus and method relating to a film hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film hole.

A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface and a plurality of holes, each hole including a central axis having vector components defined by a common vector.