GB826402A - Improvements in or relating to liquid fuel combustion chambers for gas turbine engines - Google Patents

Abstract

826,402. Gas turbine plant. COOPER, R. B. June 1, 1956 [March 1, 1955], No. 6030/55. Class 110 (3). [Also in Group XII] In an air-jacketed type of combustion chamber for a gas turbine engine, the flame tube comprises a plurality of coaxial perforated cylindrical sections 1, 2, 3, 4 spaced apart axially as at 8, and the flame tube is disposed within concentrically arranged casings 5, 10 which are disposed one within the other in spaced relation so as to provide annular passages 6, 11 through which air can flow to certain of the sections. Air swirling means 9, 12 are disposed in the annular passages and means are provided for cutting off or reducing the supply of air to one or more of the passages when the fuel supply is reduced. An axially-movable cylindrical sleeve 14 is disposed around the casing 5 and when in the outer position shown in Fig. 1 co-operates with a ring member 14a to close the air passage 11 from the air supply duct 13. When the baffle 14 is moved to the inner position shown in Fig. 2 air flows to both the inner and outer air passages 6, 11, and thence through the perforations and spaces 8 to the combustion space. The casings 5 and 10 are closed at their downstream ends by walls 5a, 10a. A small clearance 15 is provided between the ring 14a and sleeve 14 when in the closed position to allow a small quantity of air to pass to the flame tube sections 3 and 4. The flame tube sections 1, 2, 3 and 4 may be adjusted in the axial direction to determine the most suitable positions and then secured.