Control mechanism for injector diaphragms

Claim 1

In a turbojet engine having a chamber casing, an annular combustion chamber located within the chamber casing and defined by inner and outer walls about a longitudinal axis of symmetry with a plurality of air-fuel injectors arranged in an annular array at a forward end of the combustion chamber with their axes generally parallel to the longitudinal axis, each air-fuel injector equipped with an outer swirler defining openings to introduce a first air fraction into the injection system to form a combustible air-fuel mixture and a rotatable diaphragm to control the swirler openings, the improvements comprising: (a) a generally annular fairing member having a curved cross-section so as to divide an air flow into a first portion which flows into the air-fuel injectors and a second portion which passes over the outer wall of the combustion chamber; (b) mounting means to rotatably attach the annular member to the outer wall of the combustion chamber such that the annular member is located adjacent to the outer wall inside the chamber casing, and is capable of rotational movement about the longitudinal axis of symmetry; (c) drive means operatively connected to the annular member to move the annular member in either direction about the longitudinal axis of symmetry; and, (d) connecting means connecting the annular member with each of the rotatable diaphragms such that rotational movement of the annular member causes substantially simultaneous rotational movement of the diaphragms.