Ducted-fan turbine engine for military application, has annular flow straightening chamber that is delimited at its downstream by conical ring, and piercing that is formed in leading wall and supplies cooling air to chamber

摘要

The engine has an annular flow straightening chamber (23) that is delimited at its downstream by a conical ring (16). A piercing (21) supplies cooling air to the chamber, and is formed in a leading wall (22) between the chamber and downstream end of an annular passage (6). A distribution compartment (30) is connected to and surrounds the chamber.