Doosan Enerbility Co., Ltd.

Doosan Enerbnity Co., Ltd.

Wade Beaumont

Joerg Krueckels

Willy H Hoffmann

Igor Tsypkaykin

Stefan Emanuel Martin

Simon Hauswirth

Richard Jones

Vincent Galoul

Yunchang Jang

Stafan Emanuel Martin

A blade for turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction between a root end and a tip end and including an inner void extending from the root end in the radial direction, a root body integrally formed with the airfoil body, extending from the root end of the air foil body to a bottom end in the radial direction, and including a receiving slot extending from the bottom end in the radial direction and opening into the inner void of the air foil body, and an insert positioned in the receiving slot of the root body and including a plurality of through holes extending in the radial direction to form a fluid connection to the inner void of the air foil body.

Blade for a turbo machine, blade assembly, gas turbine, and method for manufacturing a blade for a turbo machine

A blade for a turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction and including a suction side surface and a pressure side surface opposite to the suction side surface with respect to a circumferential direction extending across the radial direction, and a snubber structure including a first snubber element protruding in the circumferential direction from the suction side surface of the airfoil body and a second snubber element protruding in the circumferential direction from the pressure side surface of the airfoil body, wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius, the first radius being smaller than the second radius.

Blade for a turbo machine, blade assembly, and turbine

The present invention presents a ring assemblydisposed radially outwardly of an array of circumferentially arranged bladesof a gas turbine engine rotor R. The ring assemblyincludes ring segmentsdisposed circumferentially one adjacent to another and having a first circumferential endand a second circumferential endcircumferentially spaced apart from each other. The first endof a ring segmentand the second endof an adjacent ring segmentof the plurality of ring segmentsare arranged facing each other. An integrally formed projecting seal partis formed at the first end. An integrally formed receiving seal partis formed at the second endfacing the first end. The receiving seal partreceives the projecting seal partto form a mating connection between the ring segmentand the adjacent ring segment. A gas turbine engine including the ring assemblyis also provided. Furthermore, a method of manufacturing the ring segmentof the ring assemblyis also provided.

Gas turbine ring assembly comprising ring segments having integrated interconnecting seal

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Baden, Switzerland

Wade Beaumont