A blade member on a surface of which a groove structure is formed, wherein the groove structure includes a plurality of first groove structures, a plurality of second groove structures, and a third groove structure, the plurality of first groove structures are formed to extend in a first direction, the plurality of second groove structures are formed to extend in a second direction that is different from the first direction, the third groove structure extends along a third direction that is different from the first and second directions, and is formed between one first groove structure and one second groove structure.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate and a locating feature at an exterior surface of the substrate. An outer coating is applied over the substrate. The outer coating covers the locating feature. At least a portion of the preform component and the outer coating are scanned with an imaging system to provide scan data indicative of a location of the locating feature. A cooling aperture is formed in the substrate and the outer coating based on the scan data.

Methods and systems for characterizing holes in a combustor liner of a gas turbine engine, and associated repair methods are provided. One method comprises receiving first measured data of the combustor liner in an uncoated state. The method includes determining a first location and a first orientation of a first hole and a first location and a first orientation of a second hole in the combustor liner using the first measured data. The method includes receiving second measured data of the combustor liner in a coated state where the second hole is at least partially obstructed by a coating and the first hole is substantially unobstructed by the coating. The method includes inferring a second location of the second hole of the combustor liner in the coated state using a known spacing between the first location of the first hole and the first location of the second hole. The characterization of the holes may be used to re-drill the obstructed second hole.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.

Systems and methods include a blade monitoring system. The blade monitoring system includes a processor. The processor is configured to receive a sensor signal from a sensor configured to observe a blade of the turbomachinery. The processor is also configured to derive a measurement based on a marking disposed on the blade of the turbomachinery, wherein the marking comprises a discrete feature; and to display the measurement to an operator of the turbomachinery

A pump bearing holder has a carrier portion configured to carry a static set of magnets of a pump magnetic bearing and a support portion extending outwardly of the carrier portion to connect with a pump casing such that the pump bearing holder spans an inlet provided in the pump housing. The support portion defines a plurality of internal through-passages that, in use, allow a gas flowing through the inlet to flow through the support portion.

Disclosed techniques include creating a pressure differential within an interior of a dual-wall component relative to pressure at an exterior of the dual-wall component, fabricating a hole in a first wall of the dual-wall component, while fabricating the hole in the first wall of the dual-wall component, acoustically monitoring the hole fabrication, while acoustically monitoring the hole fabrication, detecting breakthrough of the first wall of the dual-wall component based on an acoustic signal due to gas passing through the fabricated hole, and based on the acoustic signal, ceasing the fabrication of the hole.

Systems and methods are disclosed herein for repairing components. A material layer may be deposited on a surface of a component. The material layer may cover a cooling hole. A pulsed heat source may heat the component and the material layer. An infrared camera may take a series of images of the component. A location of the cooling hole may be identified based on thermal properties of the component. A removal tool may remove a portion of the material layer in order to expose the cooling hole.

A method for manufacturing a component having a defined geometry includes: a) defining a pre-component geometry including interim shape elements and additional, sacrificial elements for supporting interim elements; b) on a base plate, depositing multiple layers of a powder including a material from which the pre-component will be manufactured; c) sintering the powder to form the pre-component to the defined geometry; d) removing at least some of the sacrificial elements from the pre-component; e) subjecting the remaining pre-component from step d) to a HIP step; and f) removing remaining sacrificial elements from the pre-component product of step e) to provide a component to the defined component geometry. In the definition of the pre-component geometry, the interim elements differ from the corresponding final shape elements in the defined component geometry such that during the HIP step, the interim shape elements adjust to form final shape elements in the defined component geometry.