Title:
【発明の名称】ガスタービンジェットエンジン
Document Type and Number:
Japanese Patent JP2815206
Kind Code:
B2
Abstract:
A gas turbine jet engine is disclosed with a fan delivering into a bypass duct to generate mainly propulsion thrust, and with a thrust reversing device having flaps which for reverse thrust operation pivot into the fan air stream and cooperate with an axially extended extreme section of the outer wall of the bypass duct to uncover delection ports arranged at breakthroughs in the outer wall. The extreme section of the outer wall and the thrust reverser flaps are linked one with the other for relative movement between them such that in a first phase of actuation relative to a fixed extreme nozzle section, the extreme section provides an additional fan nozzle area which communicates with the inlet flow areas formed by the flaps relative to the bypass duct.
Inventors:
Helmut-Arund Guidel
Heinrich Enderle
Alois Laura
Heinrich Enderle
Alois Laura
Application Number:
JP33094089A
Publication Date:
October 27, 1998
Filing Date:
December 19, 1989
Export Citation:
Assignee:
Mt motoren-und turbinen-union munich gmbb etch
International Classes:
F02K1/72; F02K1/70; (IPC1-7): F02K1/70
Domestic Patent References:
| JP55137344A |
Attorney, Agent or Firm:
Ishido