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Title:
【発明の名称】ガスタービン冷却動翼
Document Type and Number:
Japanese Patent JP3337393
Kind Code:
B2
Abstract:
In gas turbine cooled moving blade, cooling air passage is made shortest and temperature elevation and pressure drop of cooling air are suppressed. Cooling air passage (16) is bored in turbine cylinder wall (15) below stationary blade (11) of first stage. The cooling air passage (16) connects at one end (16a) to turbine cylinder and at the other end (16b) to space (13) and is directed to air inflow hole (6) provided in shank portion (4) of lower portion of platform (2) of moving blade (1). Cooling air is jetted from the cooling air passage (16) toward the air inflow hole (6) so as to flow into the shank portion (4) and then into the moving blade (1) for cooling thereof. Axis (17) of the cooling air passage (16) is directed with deviation in rotational circumferential direction by angle determined by jetted velocity of the cooling air jetted from the cooling air passage(16) and rotational velocity of the moving blade (1) from position of the air inflow hole when the moving blade (1) stands still in row with the stationary blade (11) in rotor axial direction. Thus, the cooling air can be jetted in optimal direction with shortest distance and temperature elevation and pressure drop of the cooling air can be suppressed to minimum.

Inventors:
Yasuyoshi Tomita
Hiroki Fukuno
Honest Aoki
Kiyoshi Suenaga
Application Number:
JP10592897A
Publication Date:
October 21, 2002
Filing Date:
April 23, 1997
Export Citation:
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Assignee:
MITSUBISHI HEAVY INDUSTRIES,LTD.
International Classes:
F01D5/08; F01D5/18; F01D25/12; F02C7/12; F02C7/18; (IPC1-7): F01D5/08; F01D5/18
Domestic Patent References:
JP8177526A
JP5710704A
JP4986706A
JP5079610A
Attorney, Agent or Firm:
Arata Ishikawa