Assembly to stabilise flame development in a lean-burn gas turbine engine uses concentric array of turbolators downstream from turbine vanes

摘要

A gas turbine engine for e.g. aeronautical applications has a lean-fuel mixture burner chamber with an assembly which stabilises the flame pattern. The assembly consists of an outer pipe (1) with a concentric inner gas pipe (2) downstream from gas vanes, together forming an annular chamber (3). The chamber receives a mixture of cold air and atomised fuel which is surrendered to a burner chamber. Mixture flow through the annular chamber (3) is disrupted by a series of turbulators (4) in circular array. The turbulators extend a distance which is less than 30 per cent of the chamber radial height.