Title:
ガスタービン・サブアセンブリ
Document Type and Number:
Japanese Patent JP3977482
Kind Code:
B2
Abstract:
The gas turbine subassembly includes the stator, the rotor, and the annular brush seal which is attached to the stator and whose free end is in line-to-line contact with the first circumferential portion of the rotor's outside surface during a first rotation/load state (such as a full-speed/full-load state of a power-plant gas-turbine rotor). A longitudinally-adjoining second circumferential portion (such as a groove) has a smaller diameter than that of the first circumferential portion. The rotor and stator together undergo a predetermined differential thermal movement when the rotor transitions to a second rotation/load state (such as a turning-gear/no-load state). During such movement, the free end of the brush seal moves radially inward and longitudinally across the second portion, preferably without any contact.
Inventors:
Christopher Edward Wolfe
Ottoman Same Dink
Ottoman Same Dink
Application Number:
JP10546297A
Publication Date:
September 19, 2007
Filing Date:
April 23, 1997
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F01D11/00; F02C7/28
Domestic Patent References:
| JP7217452A |
Attorney, Agent or Firm:
Kenichi Matsumoto