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 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.

A vane intended to be mounted in a supply fluid pattern, includes a blade delimited in a lateral direction by an outer surface, the blade housing a data routing channel and having a groove leading to the outer surface and which communicates with the data routing channel, and data collecting means for collecting data on one of the outer surface of the blade and the vicinity thereof, the data collecting means being connected, through the groove, to the data routing channel, or extending there through. The data collecting means include one of an inserted tube and a cable, and the groove is formed in one of the outer surface opposite that whereto the inserted tube and the cable leads, and the blade that includes an orifice passing therethrough the outer surface.

The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank (10), manufacturing a housing element (14), producing an assembly opening (12) corresponding to the housing element (14) in the housing blank (10), arranging the housing element (14) in the assembly opening (12), and joining the housing element (14) to the housing blank (10) by means of a welding method. In addition, the invention relates to a turbomachine housing.

A system and method for performing laser induced breakdown spectroscopy during laser ablation of a coating, such as a TBC coating, deposited on a surface of a component, particularly to enable obtained spectrometry signals of the ablated coating to be used to monitor and control the laser ablation removal process in real-time. The system includes a laser energy source and a scan head interconnected with the laser energy source to receive a laser beam therefrom and then direct the laser beam onto the surface of the coated component. Collection optics collect radiation emitted from a laser-induced plasma generated by the laser beam at the surface of the coated component. The system is further equipped to spectrally analyze the radiation and generate a feedback signal for control and optimization of one or more operational parameters of the laser energy source in real-time.

A method of treatment includes laser-hardening a portion of a component and texturing a treated surface of the portion with a hydrophobic surface texture. In some embodiments, the method includes polishing the treated surface after laser-hardening the portion and prior to texturing the treated surface. A component includes a component body having a portion that is laser-hardened. The treated surface is hydrophobic with a hydrophobic surface texture. In some embodiments, the component is a turbine component. In some embodiments, the portion is a leading edge. A turbine system includes a turbine shaft and a turbine component attached to the turbine shaft. The turbine component includes a component body having a leading edge. The leading edge is laser-hardened and the treated surface of the leading edge is hydrophobic with a hydrophobic surface texture.

Methods provided for remotely stopping a crack in a component of a gas turbine engine are provided, along with methods of remotely cleaning a surface area of a component of a gas turbine engine. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; and drilling a hole into the base of the defect. An integrated repair interface is also provided.

A system for forming a cooling hole in an airfoil includes a liquid-jet guided laser. The liquid-jet guided laser generates a laser beam confined within a fluid column. The fluid column/laser beam is directed at an outer surface of the airfoil. The system also includes a purge medium supply that is fluidly coupled to an aperture of the airfoil. The purge medium supply provides a purge medium into an inner cavity of the airfoil. The purge medium flow is oriented to flow in a flow direction that is substantially parallel to an inner surface of the cavity. A cooling hole is formed in the airfoil and extends through the outer surface and penetrates the inner surface of the cavity. A centerline of the cooling hole forms an acute angle with respect to the purge medium flow direction. The system described herein provides a method for manufacturing an airfoil.

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 system and method for automated laser ablation includes an end effector for performing laser ablation at a location with restricted access. The systems and methods of the present disclosure specifically provide for a miniature laser end effector which may be inserted through a port or bore in order to ablate the surface of an internal component of a complex assembly. In several embodiments of the present subject matter, the end effector is mounted on a machine and coupled to a laser system.