Title:
A convergent diver Gent nozzle for turbine engines
Document Type and Number:
Japanese Patent JP6082960
Kind Code:
B2
Abstract:
A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.
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Inventors:
Leco, Mathieu
Bertussi, Jean
Gaiyo, Mathieu
Bertussi, Jean
Gaiyo, Mathieu
Application Number:
JP2014545330A
Publication Date:
February 22, 2017
Filing Date:
December 04, 2012
Export Citation:
Assignee:
Saffron Aircraft Engines
International Classes:
F02K3/02; F02C7/00
Domestic Patent References:
| JP49111014A | ||||
| JP10103153A | ||||
| JP200530397A | ||||
| JP8189419A | ||||
| JP6190306A |
Foreign References:
| US20040006969 | ||||
| EP1607610A1 |
Attorney, Agent or Firm:
Kawaguchi International Patent Office
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