| 摘要 |
The present invention provides gas turbine reheat combustion apparatus for aircraft propulsion. The apparatus includes means for producing a flame stabilization zone in a stream of combustion supporting gas flowing in a duct, said stabilization zone having a recirculatory flow region therein, an injector for introducing a fluid comprising an inert diluent such as, for example, nitrogen, into the recirculatory flow region, and means for supplying the fluid to the injector.
|
