AFTERBURNER COMMIXING LINING VENT CHANNELS Russian patent published in 2009 - IPC F02K3/10 

FIELD: engines and pumps.

SUBSTANCE: aircraft gas turbine engine comprises a diffuser arranged ahead of the afterburner and confined by a tubular wall referred to as a flows commixing lining fitted inside the casing. There is an annular channel arranged between the casing and tubular wall intended for secondary cold flow passage. The front upstream fuel injectors arranged at the diffuser inlet. Right behind the rear injectors, flame holders are fitted. The tubular wall of flows features a bicurvature between the radial plane accommodating the front fuel injectors and the radial plane accommodating the front fuel injectors, and a radial plane located behind the flame holders, the said bicurvature being narrowed downstream to decelerate primary gas flow F1 behind the front fuel injectors. An annular scoop air intake is arranged around the diffuser tubular wall upstream front section to intake inlet air in the said annular channel. The tubular wall is furnished with channels distributed along the circumference between scoop upstream intake end and diffuser to enter the diffuser inside. Note that the aforesaid channels pass and come out tangentially to the diffuser inner wall surface located between the upstream injectors and flame holders.

EFFECT: higher efficiency of tubular wall cooling.

5 cl, 2 dwg