Title:
ハイブリッドウォーム形ガスタービンエンジン
Document Type and Number:
Japanese Patent JP5227069
Kind Code:
B2
Abstract:
A gas turbine engine (100) has components including a compressor (6), a combustor (7), and a turbine (9). At least one component is radially bladed having at least one row (206) of radially extending rotatable blades (208) and at least another is a worm component (210) having an inner body (12) disposed within an outer body (14). The inner and outer bodies have offset inner (16) and outer axes (18), intermeshed inner (17) and outer (27) helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine (100) has components in serial downstream flow relationship including a fan (108), a low pressure compressor (8), a high pressure compressor (6), a combustor (7), a high pressure turbine (9), and a low pressure turbine (120). At least one of the components is radially bladed and at least one of the components is a worm component (210).
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Inventors:
Kurt David Mallow
Laurin George Giffin
Oradapo Faklu
Laurin George Giffin
Oradapo Faklu
Application Number:
JP2008109697A
Publication Date:
July 03, 2013
Filing Date:
April 21, 2008
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F02C3/055; F04C18/107
Foreign References:
| US20040208740 | ||||
| US2553548 |
Attorney, Agent or Firm:
Arakawa Satoshi
Hirokazu Ogura
Toshihisa Kurokawa
Hirokazu Ogura
Toshihisa Kurokawa