초록 ▼

A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and co

A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the 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 connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.

대표청구항 ▼

What is claimed is: 1. 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 there

What is claimed is: 1. 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. 2. The system of claim 1, wherein the first tube of each of the fluid injector assemblies has a diameter of about 1 inch to about 4 inches. 3. The system of claim 1, wherein each of the fluid injector assemblies further comprises: a second tube for providing a secondary fluid flow, wherein the first tube extends within the second tube, and wherein the second tube is connected to the outlet. 4. The system of claim 1, wherein the fuel valve of each fluid injector assembly comprises a solenoid valve. 5. The system of claim 1, wherein each of the injector assemblies is configured to provide detonation of a mixture of air from the secondary air valve and fuel from the fuel valve when ignited by the igniter. 6. The system of claim 1, wherein each of the injector assemblies is configured to provide fast deflagration combustion of a mixture of air from the secondary air valve and fuel from the fuel valve when ignited by the igniter. 7. The system of claim 1, wherein the outlet tube has a plurality of openings for permitting fluid to pass to the exhaust nozzle. 8. A fluid flow system in a gas turbine engine, the system comprising: a fixed-geometry exhaust nozzle physically defining a throat area and a divergent section; a primary air supply valve for selectively supplying air from an air source; a fluid injector assembly positioned at the exhaust nozzle and connected in fluid communication with the primary air supply valve, wherein the fluid injector assembly comprises: a first tube; a passive air check valve positioned substantially within the first tube and in fluid communication with the primary air supply valve; a fuel valve extending within the first tube and located downstream of the air valve; an igniter extending into the first tube located downstream of the fuel valve; an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle, wherein the injector assembly is configured to provide fast deflagration combustion of a mixture of air from the passive air check air valve and fuel from the fuel valve when ignited by the igniter. 9. The system of claim 8, wherein the first tube of the fluid injector assembly has a diameter of about 1 inch to about 4 inches. 10. The system of claim 8, wherein the fluid injector assembly further comprises: a second tube for providing a secondary fluid flow, wherein the first tube extends within the second tube, and wherein the second tube is connected to the outlet. 11. The system of claim 8, wherein the fuel valve of the fluid injector assembly comprises a solenoid valve. 12. The system of claim 8, wherein the outlet tube has a plurality of openings for permitting fluid to pass to the exhaust nozzle. 13. A fluid flow system in a gas turbine engine, the system comprising: an exhaust nozzle defining a throat area and a divergent section; a plurality of fluid injector assemblies positioned at the exhaust nozzle, wherein each fluid injector assembly comprises: an air valve for controllably providing fan bleed air from the gas turbine engine; a fluid chamber, wherein the air valve provides an air outlet into the fluid chamber; a passive air check valve positioned substantially within the fluid chamber and in fluid communication with the air valve; a fuel valve, wherein the fuel valve provides a fuel outlet within the fluid chamber; an igniter extending into the fluid chamber for igniting fuel and air mixtures to produce combustion that raises pressure; an outlet tube in fluid communication with the fluid chamber and connected in fluid communication with the exhaust nozzle, wherein the outlet tube of each fluidic injection assembly has a plurality of bifurcation openings for permitting fluid to pass to the exhaust nozzle. 14. The system of claim 13, wherein the fuel valve of the fluid injector assembly comprises a solenoid valve. 15. The system of claim 13, wherein each injector assembly is configured to provide detonation of a mixture of air from the secondary air valve and fuel from the fuel valve when ignited by the igniter. 16. The system of claim 13, wherein each injector assembly is configured to provide fast deflagration combustion of a mixture of air from the air valve and fuel from the fuel valve when ignited by the igniter. 17. The system of claim 13, wherein at least one of the plurality of fluid injector assemblies is configured to produce a pressure rise of at least about 4 times the pressure of the fan bleed air utilized and up to about 8 times the pressure of the fan bleed air utilized. 18. The system of claim 1, wherein the outlet is configured as a slot shaped nozzle defining a substantially rectangular opening. 19. The system of claim 18, wherein the first tube has a substantially cylindrical shape. 20. The system of claim 8, wherein the first tube has a substantially cylindrical shape, and wherein the outlet is configured as a slot shaped nozzle defining a substantially rectangular opening.