A gaspath component includes a flowpath body. A cooling plenum is disposed within the flowpath body. The cooling plenum includes a first region configured to receive a cooling flow and a second region configured to expel the cooling flow from the flowpath body. A metering obstruction is positioned between the first region and the second region and is configured to meter a flow of coolant through the cooling plenum.

A gaspath component includes a flowpath body. A cooling plenum is disposed within the flowpath body. The cooling plenum includes a first region configured to receive a cooling flow and a second region configured to expel the cooling flow from the flowpath body. A metering obstruction is positioned between the first region and the second region and is configured to meter a flow of coolant through the cooling plenum.

A coupon for replacing a cutout in a hot gas path component of a turbomachine is provided. In one embodiment, the coupon includes a body having an outer surface; and a plurality of grinding depth indicators in the outer surface of the body. In another embodiment, the coupon includes a body having an edge periphery configured to mate with an edge periphery of the cutout, and at least a portion of the edge periphery of the body has a wall thickness greater than a wall thickness of an edge periphery of the cutout. The embodiments may be used together or separately.

A coupon for replacing a cutout in a hot gas path component of a turbomachine is provided. In one embodiment, the coupon includes a body having an outer surface; and a plurality of grinding depth indicators in the outer surface of the body. In another embodiment, the coupon includes a body having an edge periphery configured to mate with an edge periphery of the cutout, and at least a portion of the edge periphery of the body has a wall thickness greater than a wall thickness of an edge periphery of the cutout. The embodiments may be used together or separately.

A coupon for replacing a cutout in a hot gas path component of a turbomachine is provided. The coupon includes a body having an outer surface; a chamber within the body for receiving a flow of a coolant; and a passage extending from the chamber to the outer surface of the body. The passage includes an internal portion within a wall of the body having a first perpendicular, cross-sectional area and an exit portion at the outer surface of the body having a second perpendicular, cross-sectional area that is greater than the first perpendicular, cross-sectional area.

A coupon for replacing a cutout in a hot gas path component of a turbomachine is provided. The coupon includes a body having an outer surface; a chamber within the body for receiving a flow of a coolant; and a passage extending from the chamber to the outer surface of the body. The passage includes an internal portion within a wall of the body having a first perpendicular, cross-sectional area and an exit portion at the outer surface of the body having a second perpendicular, cross-sectional area that is greater than the first perpendicular, cross-sectional area.

A turbomachine blade system, in particular for a compressor or turbine stage of a gas turbine, which includes at least one blade, in particular a moving or guide blade, and at least one moving body for reducing the vibrations of this blade, at least one area of a guide for guiding the body and/or at least one area of a supporting structure for resiliently mounting the body and/or at least one area of the body being or becoming generatively manufactured together with at least one area of the blade, in particular of a vane and/or blade root and/or a shroud situated thereon.

A blade and gas turbine include a stationary blade main body provided internally with cavities, and an inner shroud linked to an end portion, in the longitudinal direction, of the stationary blade main body, and which is internally provided with an inner shroud cooling passage with which a first cavity is in fluid communication. The inner shroud is provided, in front edge corner portions, with a first chamfered portion intersecting a front surface, a side surface, and an upper surface, and first cooling holes in fluid communication with the inner shroud cooling passage are provided in the first chamfered portion.

A blade and gas turbine include a stationary blade main body provided internally with cavities, and an inner shroud linked to an end portion, in the longitudinal direction, of the stationary blade main body, and which is internally provided with an inner shroud cooling passage with which a first cavity is in fluid communication. The inner shroud is provided, in front edge corner portions, with a first chamfered portion intersecting a front surface, a side surface, and an upper surface, and first cooling holes in fluid communication with the inner shroud cooling passage are provided in the first chamfered portion.

A method for manufacturing a blade with a first portion and a second portion, the method includes forming the first portion that includes forming a model of the first portion from removable material, forming a first shell mould from the model of the first portion, and forming the single-crystal or columnar first portion m a first metal alloy in the first shell mould from a single-crystal seed, and forming the second portion in which the second portion is formed on the first portion, and in which the first portion and the second portion are made from different materials, the second portion being polycrystalline and formed from a second metal alloy. The blade includes a single-crystal or columnar first portion made from a first metal alloy and a polycrystalline second portion made from the second metal alloy different from the first metal alloy.