Title:
EXHAUST NOZZLE FOR SUPERSONIC AIRCRAFT
Document Type and Number:
Japanese Patent JP3246153
Kind Code:
B2
Abstract:
PURPOSE: To provide an exhaust nozzle for supersonic aircraft which is provided with a mixer of lobe type with high mixing efficiency in a storable manner, and capable of smooth shifting from the noise-reduced mode at the take-off to the supersonic cruising mode through the subsonic mode, and also capable of smooth shifting in a short time from the noise-reduced mode to the reverse mode at the landing.
CONSTITUTION: A two-dimensional exhaust nozzle of constant sectional shape is provided with a lobe type mixer M which is developed in a linear manner. The air is introduced by first flaps A in the noise-reduce mode, the air is mixed with the high speed gas flow from a core engine 16 by the mixer M to reduce the speed of the jet flow, and the introduction of the air is stopped in the supersonic cruising mode. The mixer M is stored outside the high speed gas flow, and the respective flaps A-D are arranged in an optimum manner for the supersonic cruising mode.
Inventors:
Masahiko Yamamoto
Tadaaki Watanabe
Koji Tokunaga
Takeshi Kashiwagi
Tadaaki Watanabe
Koji Tokunaga
Takeshi Kashiwagi
Application Number:
JP492294A
Publication Date:
January 15, 2002
Filing Date:
January 21, 1994
Export Citation:
Assignee:
Ishikawajima Harima Heavy Industries Co., Ltd.
International Classes:
F02K1/08; F02K1/12; F02K1/46; F02K1/62; (IPC1-7): F02K1/46; F02K1/08; F02K1/12; F02K1/62
Domestic Patent References:
| JP5720539A | ||||
| JP63235651A |
Other References:
【文献】米国特許5154052(US,A)
【文献】米国特許3614037(US,A)
【文献】米国特許3587973(US,A)
【文献】米国特許3614037(US,A)
【文献】米国特許3587973(US,A)
Attorney, Agent or Firm:
Minoru Hotta (2 outside)