An article and method of forming an article are provided. The article includes a side wall at least partially defining an inner region and an outer region of the article, the side wall having a first end and a second end, an end wall formed proximal to the first end of the side wall, the end wall defining a tip portion of the article, and a cooling channel formed in the side wall, within the tip portion. The method of forming an article includes positioning a first sheet of material having a channel formed therein over a first end of a body, positioning at least one additional sheet of material over the first sheet of material, and securing the first sheet of material and the at least one additional sheet of material to the body to form a tip portion including a cooling channel formed therein.

Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.

Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.

A seal assembly for a gas turbine engine defining a central axis extending along an axial direction and including a rotating shaft extending at least partially along the axial direction. The seal assembly includes a first component coupled to a fixed structure or drivingly coupled to the rotating shaft. The seal assembly further includes a rotating component drivingly coupled to the rotating shaft of the gas turbine engine. Additionally, the first component and rotating component define an annular gap therebetween. The seal assembly also includes one or more flanges extending from the stationary component, the rotating component, or both. The flange(s) include a base and an external surface extending into the annular gap from the base to a tip. Additionally, the flange(s) defines an inlet port on the external surface fluidly coupled to an outlet port at the tip. As such, the flange(s) forms a seal within the annular gap.

A supply system of a sealing system of a turbomachine, wherein the sealing system which are suppliable with a seal gas. The supply system comprises, for each sealing sub-system, four seal gas lines: a first seal gas supply line, via which process gas extracted from the turbomachine is suppliable as first seal gas to the respective sealing sub-system. A second seal gas supply line, via which second seal gas is suppliable to the respective sealing sub-system. A seal gas discharge line, via which the first seal gas and the second seal gas are dischargeable from the respective sealing sub-systems. A safety discharge line, which is closed during the normal operation and open in the event of a fault, to discharge at least one part of the first seal gas and of the second seal gas from the respective sealing sub-system via the same in the event of a fault.

A supply system of a sealing system of a turbomachine, wherein the sealing system which are suppliable with a seal gas. The supply system comprises, for each sealing sub-system, four seal gas lines: a first seal gas supply line, via which process gas extracted from the turbomachine is suppliable as first seal gas to the respective sealing sub-system. A second seal gas supply line, via which second seal gas is suppliable to the respective sealing sub-system. A seal gas discharge line, via which the first seal gas and the second seal gas are dischargeable from the respective sealing sub-systems. A safety discharge line, which is closed during the normal operation and open in the event of a fault, to discharge at least one part of the first seal gas and of the second seal gas from the respective sealing sub-system via the same in the event of a fault.

A stator vane (3) for a turbine (50c) of a turbomachine (50), the stator vane having a stator vane airfoil (3c), an inner shroud (3a) and an outer shroud (3b), the inner shroud (3a) and the outer shroud (3b) bounding an annular space (2), in which working gas (51) is conveyed during operation, radially with respect to a longitudinal axis (52) of the turbomachine (50), and the stator vane airfoil (3c) having a stator vane airfoil channel (3d) extending through its interior between a radially inner inlet (6) and a radially outer outlet (7). A characteristic features is that the inlet (6) is disposed in such a manner that a gas (8) flowing through the stator vane airfoil channel (3d) during operation is at least partially formed of the working gas (51) conveyed in the annular space (2), and thus the working gas is redistributed from radially inward to radially outward.

A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.

A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.

Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.