Improvements in combustion chambers for aero-thermodynamic ducts and gas turbine engines

摘要

638,109. Generating combustion products under pressure. LEDUC, R. Dec. 12, 1947, No. 32790. Convention date, Sept. 6, 1946. [Class 51 (i)] A combustion chamber for an aero-thermodynamic duct or gas turbine comprises co-axially disposed annular walls defining a flame chamber containing a burner and the entry of which has a complete ring of radially- or axially-disposed inclined guide vanes comprising groups of alternately opposite-handed vanes, a continuous annular space for the passage of cooling air being disposed around the annular walls. A number of co-axial flame chambers each fitted with a burner and ring of inlet guide vanes may be provided. In Fig. 1, the annular walls 4SP1/SP, 42 ... are of convergent-divergent form and the flame chambers are formed between the convergent trailing part of one annular wall and the divergent leading part of the succeeding wall. Fuel is supplied to the ring manifolds 6 which carry circumferentially-spaced burners, and the radially-disposed guide vanes 5 produce vortical flow. The annular walls are supported by faired brackets 2 from the external wall 1. The exhaust of an auxiliary gas turbine 3a provides a core of hot gases. The guide-vanes 5 may be axiallydisposed. In Fig. 5, theannular walls 8a, 9a form an annular flame chamber 7 and the rearward ends of the walls are pleated to form radial partitions 14 which divide the air flowing through the annular passages 8, 9 and the combustion products from the flame chamber 7 into radial strata. The inlet of the flame chamber 7 may also be sub-divided by partitions 12a into auxiliary flame chambers 7a, 7b and 12. Rings of radial guide-vanes 10a, 10b of alternating groups of opposite-handed vanes, are provided. The leading flame chamber in both embodiments may be arranged to act as a pilot flame chamber.