Title:
3つの回転体を備えるガスタービンエンジン
Document Type and Number:
Japanese Patent JP2014515460
Kind Code:
A
Abstract:
A gas turbine engine for propelling an aircraft, including a low pressure rotary body including low pressure turbine rotor blades, an intermediate rotary body including intermediate turbine rotor blades, a high pressure rotary body including high pressure turbine rotor blades, an air flow flowing through the engine from upstream to downstream. The at least one intermediate turbine rotor blade is followed directly downstream by a low pressure turbine rotor blade so as to straighten air flow deflected by the intermediate turbine rotor blade.
More Like This:
| WO/2019/016302 | DISC TURBINE WITH STATIC DISTRIBUTOR |
| WO/2011/033204 | TURBINE ENGINE WITH CONTRA-ROTATING NON-DUCTED PROPELLERS |
| JP2014231767 | VARIOUS ENERGY RESERVATION CYCLE COMBINED ENGINE |
Inventors:
Cyan, Philip
Muban, Lamine
Muban, Lamine
Application Number:
JP2014513239A
Publication Date:
June 30, 2014
Filing Date:
May 31, 2012
Export Citation:
Assignee:
SNECMA
International Classes:
F01D1/26; F01D5/06; F01D9/02; F02C3/067; F02C7/00; F02K3/06; F02K3/072
Attorney, Agent or Firm:
Kawaguchi International Patent Office