Patent ID: 7775460

Claim:
A fluid flow system in use with a gas turbine engine, the system comprising: an exhaust nozzle defining a physical throat area and divergent section; a primary air supply valve; a distribution manifold connected to the primary air supply valve and in fluid communication therewith; a plurality of fluid injector assemblies positioned at the exhaust nozzle and in fluid communication with the distribution manifold, wherein each fluid injector assembly comprises: a first tube; a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold wherein the secondary air valve comprises a passive air check valve; a fuel valve positioned at least partially within the first tube and located downstream of the secondary air valve; an igniter extending into the first tube downstream of the fuel valve; and an outlet in fluid communication with the first tube and in fluid communication with the exhaust nozzle, wherein the outlet has a geometry that changes a shape of fluid flow exiting the first tube, wherein at least one of the plurality of fluid injector assemblies is configured to produce a pressure rise between approximately four to approximately eight times the pressure of supplied air utilized for combustion of a fuel/air mixture in the at least one of the plurality of fluid injector assemblies.