A turbine ring sector made of ceramic matrix composite material has a portion forming an annular base with an inner face for defining the inner face of a turbine ring when the ring sector is mounted on a ring support structure and an outer face from which there extends an attachment portion for attaching the ring sector to the ring support structure, the ring sector further including inter-sector faces, each for facing a neighboring ring sector when the ring sector is mounted on the ring support structure; wherein the inter-sector faces are coated in an environmental barrier that is doped with an electrically-conductive compound and that presents at least one slot.

Engineered groove features (EGFs) are formed within thermal barrier coatings (TBCs) of turbine engine components. The EGFs are advantageously aligned with likely stress zones within the TBC or randomly aligned in a convenient two-dimensional or polygonal planform pattern on the TBC surface and into the TBC layer. The EGFs localize thermal stress- or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. Propagation of a crack is arrested when it reaches an EGF, so that it does not cross over the groove to otherwise undamaged zones of the TBC layer. In some embodiments, the EGFs are combined with engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC.

A process for forming a component is provided. The process includes providing a cooling channel flow definition at least partially about a core comprising a ceramic matrix composite material. A metal material is cast about the core and the cooling channel flow definition to form an outer metal shell. In addition, a cooling channel is formed from the cooling channel flow definition in the component.

An article has a metallic substrate having a plurality of recesses. A first coating is at least at the recesses and has: a splatted layer; and a columnar layer atop the splatted layer. A second coating is away from the recesses and has: a columnar layer atop the substrate without an intervening splatted layer.

An object is to provide a sheet-metal turbine housing reinforced by a readily-manufacturable structure, the sheet-metal turbine housing also having a small thickness and improved containment performance. A sheet-metal turbine housing includes: a scroll part forming an exhaust gas channel of a scroll shape in a turbocharger for driving a turbine with exhaust gas of an engine, the scroll part comprising sheet metal; and at least one rib portion of a protrusion shape formed on an outer wall surface of the scroll part at a radially outer side of an inlet edge of a turbine blade along a circumferential direction of the scroll part, the at least one rib portion protruding either outward or inward, or both, and including a bend and bend-back structure formed on the sheet metal forming the scroll part.

A system according to various embodiments can include: a coating system configured to apply a thermal coating material to a component, the component having a plurality of cooling holes; an airflow system coupled with the coating system, the airflow system configured to force air through the component; and a control system coupled with the airflow system and the coating system, the control system configured to: detect coating instructions for the coating system, the coating instructions instructing the coating system to apply the thermal coating material to a subset of the plurality of cooling holes; and instruct the airflow system to force air through the subset of the plurality of cooling holes during application of the thermal coating material to the component in response to detecting the coating instructions.

Core assemblies for manufacturing airfoils and airfoils made therefrom having an aft flowing serpentine hybrid skin core positioned relative to a plurality of core bodies and configured to define at least one serpentine cavity within the manufactured airfoil. The aft flowing serpentine hybrid skin core extends from a root region toward a tip region in a radial direction of the manufactured airfoil and the plurality of core bodies are positioned about the aft flowing serpentine hybrid skin core to form a shielding structure to thermally shield the aft flowing serpentine hybrid skin core in the manufactured airfoil.

Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180 F. (638 C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.

Embodiments of the present disclosure are directed to an article and methods of forming the article. The article includes a thermal barrier coating disposed on a substrate. The thermal barrier coating includes a thermal barrier material and partially filled surface-connected columnar voids. The partially filled surface-connected columnar voids are interspersed with the thermal barrier material in the thermal barrier coating. At least some of the partially filled surface-connected columnar voids include a calcium-magnesium-aluminum-silicon-oxide (CMAS)-reactive material disposed within, such that the CMAS-reactive material is physically separated from the substrate by a columnar cavity having an aspect ratio greater than 3.

The present invention relates to a process of storing energy through the conversion of thermal energy and subsequent power generation by means of a gas turbine set with compressor (1), expander (6) and power generator (8), with at least one (3) and with a second (4) low-temperature reservoir, and a high-temperature reservoir (5) with bulk material as the heat storage medium (11),
characterized in that, the electric energy is stored in the form of high-temperature heat above the turbine outlet temperature TOT in a thermal reservoir (5),
that during the power generation phase a compressed gas from the compressor (1) is heated in a low-temperature reservoir (3, 4) to a temperature near the turbine outlet temperature TOT and subsequently heated in a high-temperature reservoir (5) with stored heat from electric power to a temperature level of at least the turbine inlet temperature TIT, and that the ratio between the bed height in flow direction and the mean particle diameter of the bulk material (11) in the high-temperature reservoir (5) is at least 10, preferably at least 100, more preferably at least 250, even more preferably at least 500 and especially preferably at least 1000,
in addition, a means in which this process can be used.