Blade for a turbo machine
AssigneeSiemens Aktiengesellschaft
InventorAnthony Davis
Life of this patent
Estimating the term…
Abstract
A blade for a turbomachine, for example a gas turbine, is provided. The blade is arranged on a turbine rotor of the gas turbine. The blade includes a root portion having two narrow sides and two broad sides, a cooling air supply passage in the root portion, and a cooling air bleed which is arranged in the root portion and is in fluid connection with the cooling air supply passage. The cooling air bleed includes a nozzle on one of the narrow sides of the root portion, wherein the nozzle is formed by a hole and wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade.
Claims15
1-13. (canceled)
Blade for a turbomachine, comprising:
- a root portion with two narrow sides and two broad sides;
- a cooling air supply passage in the root portion;
- and
- a cooling air bleed arranged in the root portion and in fluid connection with the cooling air supply passage;
- wherein the cooling air bleed comprises a nozzle on one of the narrow sides of the root portion, and wherein the nozzle is formed by a hole,
- wherein the blade further comprises an upper blade platform and a lower blade platform,
- wherein the upper blade platform and the lower blade platform are embodied as parts of a labyrinth-sealing when assembled in the turbomachine, and
- wherein the nozzle is arranged between the upper blade platform and the lower blade platform, and
- wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade.
Dependencies are inferred from the claim text.