Title:
タービンにおける回転部品を冷却するための装置及び方法
Document Type and Number:
Japanese Patent JP4602518
Kind Code:
B2
Abstract:
A cooling system for turbomachinery includes a compressor bleed air passageway (42) for supplying bleed cooling air to a plurality of circumferentially spaced, generally axially extending passages (44) in communication with a cavity (38) within the inner barrel (39) in which the flanges (34, 36) of the turbine and compressor rotors are secured to one another. The exit ends of the passages have swirl devices (50) for turning the flow from the general axial direction to a tangential direction corresponding to the direction of rotation of the combined rotors. A leakage seal (48) is provided between the rotor and the stationary component to provide a pressure drop across a plenum and cavity to increase the velocity of air flowing into the cavity. Consequently, cooling air is supplied the cavity at a tangential velocity approaching the rotor velocity with reduced windage and lower temperature, thereby improving the performance of the turbomachinery.
Inventors:
Mark Stuart Scoder
Jeffrey John Buckywicks
Jeffrey John Buckywicks
Application Number:
JP2000161310A
Publication Date:
December 22, 2010
Filing Date:
May 31, 2000
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F02C7/18; F01D5/08; F01D25/12
Domestic Patent References:
| JP4224234A | ||||
| JP7009194B2 | ||||
| JP61155630A | ||||
| JP57002428A | ||||
| JP55131531A |
Foreign References:
| US3565545 | ||||
| US3602605 | ||||
| US3826084 |
Attorney, Agent or Firm:
Arakawa Satoshi