Title:
ガスタービンエンジンロータの先端隙間を制御するための方法及び装置
Document Type and Number:
Japanese Patent JP4569950
Kind Code:
B2
Abstract:
A compressor (40) for a gas turbine engine includes a rotor assembly (42) comprising a plurality of circumferentially-spaced apart rotor blades (50). Each of the blades extends radially outwardly from a radially inner rim (58) to a tip (60). Each rim defines a portion of a radially inner flowpath surface through the compressor. A casing (80) extends circumferentially around the rotor assembly. The casing includes at least a first ring (41) and a second ring (82). The first ring includes a radially inner surface defining a portion of a radially outer flowpath surface through the compressor. The first ring inner surface is spaced radially outwardly from the plurality of rotor blade tips. The said second ring is coupled to the first ring by a fastener assembly (86). The first ring radially inner surface facilitates substantially insulating the fastener assembly from the compressor flowpath.
More Like This:
| WO/2021/230442 | HAIR DRYER |
Inventors:
Steven Michelle Taylor
Christina Marie Spencer
Dragos Nikolae Ricou
Christina Marie Spencer
Dragos Nikolae Ricou
Application Number:
JP2004137239A
Publication Date:
October 27, 2010
Filing Date:
May 06, 2004
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F04D29/32; F01D1/02; F01D11/14; F01D25/24; F02C3/04; F02C6/12; F04D29/52; F04D29/58; F04D29/64
Domestic Patent References:
| JP9510761U | ||||
| JP8035401A | ||||
| JP61147303U | ||||
| JP50155819A | ||||
| JP10266896A |
Attorney, Agent or Firm:
Arakawa Satoshi
Hirokazu Ogura
Nobukazu Ito
Toshihisa Kurokawa
Hirokazu Ogura
Nobukazu Ito
Toshihisa Kurokawa