US 8,506,251 B2Granted

Gas turbine blade, manufacturing method therefor, and gas turbine using turbine blade

AssigneeMitsubishi Heavy Industries, Ltd.

InventorsSatoshi Hada, Takahiko Imada, Tomofumi Shintani, Katsutoshi Ooe, Norifumi Hirata, Hiroshi Asano

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Abstract

Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade.

Claims4

Dependent claims

A gas turbine blade in which cooling channels are formed inside the turbine blade, and the turbine blade is cooled by causing cooling air to circulate through the cooling channels, wherein

the cooling channels comprise:
a plurality of straight channel-like base-side elongated holes that extend in a longitudinal direction at a base side of the turbine blade,
a plurality of straight channel-like tip-side elongated holes that extend in a longitudinal direction at a tip side of the turbine blade, and
a plurality of communicating hollow portions that are interposed at connection portions between the base-side elongated holes and the tip-side elongated holes to individually allow the two types of elongated holes to communicate with each other, and that have larger cross-sectional areas than the channel cross-sectional areas of the two types of elongated holes,
wherein the communicating hollow portions are formed so as to match the position of a platform portion of the turbine blade, and
wherein, among the plurality of the communicating hollow portions, the communicating hollow portions that are adjacent to each other are set at different heights.

3 more elements

Dependencies are inferred from the claim text.

Facts

Application: 13/093,437Filed 25 Apr 2011 · continuation in part
Priority: JP 2010-0466873 Mar 2010
Published: US 2011/0217180 A18 Sep 2011
Granted: 13 Aug 2013
Term ends: Not estimatedThe source records don’t support an estimate.

Classification13 codes

F01D 5/187
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: convection cooling
B23H 9/10
Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects: working turbine…
B23P 15/02
Making specific metal objects by operations not covered by a single other subclass or a group in this subclass: turbine or like blades from one piece
F01D 5/18
Form or construction: hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades