초록 ▼

A flow path splitter duct is provided. The flow path splitter duct includes a main hub, a first outlet hub and a second outlet hub. The main hub has a plurality of inlet ports each being separated by at least one wall. The first outlet hub has a plurality of first duct outlet ports, each of the fir

A flow path splitter duct is provided. The flow path splitter duct includes a main hub, a first outlet hub and a second outlet hub. The main hub has a plurality of inlet ports each being separated by at least one wall. The first outlet hub has a plurality of first duct outlet ports, each of the first duct outlet ports are in fluid communication with only one of the corresponding plurality of inlet ports. The second outlet hub has a plurality of second duct outlet ports, each of the second duct outlet ports are in fluid communication with only one of the corresponding plurality of inlet ports, wherein engine exhaust gas that enters one of the plurality of inlet ports is simultaneously diverted to only one of the first duct outlet ports and to only one of the second duct outlet ports. A vertical takeoff and landing aircraft is also provided that includes the flow path splitter duct. A method of using the same is also provided.

대표청구항 ▼

What is claimed is: 1. A vertical takeoff and landing aircraft comprising: an aircraft fuselage; a plurality of engines; at least one hub assembly mechanically coupled to said fuselage having a plurality of transport ducts, each transport duct for selectively receiving engine exhaust gas from one o

What is claimed is: 1. A vertical takeoff and landing aircraft comprising: an aircraft fuselage; a plurality of engines; at least one hub assembly mechanically coupled to said fuselage having a plurality of transport ducts, each transport duct for selectively receiving engine exhaust gas from one or more of said plurality of engines, said hub assembly being rotated by at least one of said engines; a flow path splitter duct; and a tandem rotor/wing coupled to said flow path splitter duct for each of said hub assemblies being mechanically coupled thereto, said tandem rotor/wing having a plurality of primary flow ducts correspondingly receiving engine exhaust gas from said plurality of transport ducts and passing engine exhaust gas to a select plurality of rotor/wing nozzles; wherein said flow path splitter duct comprises: a main hub having a plurality of inlet ports each being separated by at least one wall, a first outlet hub having a plurality of first duct outlet ports, each of the first duct outlet ports in fluid communication with only one of the corresponding plurality of inlet ports, and a second outlet hub having a plurality of second duct outlet ports, each of the second duct outlet ports in fluid communication with only one of the corresponding plurality of inlet ports, wherein engine exhaust gas entering one of the plurality of inlet ports is simultaneously diverted to only one of the first duct outlet ports and to only one of the second duct outlet ports, and wherein each of said inlet ports is individually in fluid communication with one of each of said plurality of transport ducts, and wherein each of said outlet ports are in fluid communication with one of each of said plurality of primary flow ducts. 2. The aircraft of claim 1 wherein said tandem rotor/wing includes a first blade and a second blade; said first blade having four nozzles, of which two nozzles are ducted to a first primary flow duct and the other two nozzles are ducted to a second primary flow duct; and said second blade having four nozzles, of which two nozzles are ducted to said first primary flow duct and the other two nozzles are ducted to said second primary flow duct, wherein said first primary flow duct receives engine exhaust gas via a first transport duct from one of said engines and said second primary flow duct receives engine exhaust gas via a second transport duct from another of said engines. 3. The aircraft of claim 2 wherein said first primary flow duct is coupled to said outer two nozzles of said first blade and said outer two nozzles of said second blade. 4. The aircraft of claim 2 wherein said first primary flow duct is coupled to said outer two nozzles of said first blade and said inner two nozzles of said second blade. 5. The aircraft of claim 1 wherein said plurality of second duct outlet ports or said plurality of first duct outlet ports is symmetrically offset vertically about said outlet hub. 6. The aircraft of claim 1 wherein said main hub is perpendicular to said first outlet hub, wherein said first outlet hub is parallel to but in the opposite direction from said second outlet hub, and wherein at least one of said plurality of inlet ports are D shaped and at least one of said plurality of duct outlet ports is kidney shaped. 7. A method of propelling and lifting an aircraft in a 1-engine out situation comprising: providing an aircraft fuselage; providing a plurality of engines; providing at least one hub assembly mechanically coupled to said fuselage having a plurality of transport ducts, each transport duct for selectively receiving engine exhaust gas from one or more of said plurality of engines, said hub assembly being rotated by at least one of said engines; providing a flow path splitter duct; providing a tandem rotor/wing coupled to said flow path splitter duct for each of said hub assemblies being mechanically coupled thereto, said tandem rotor/wing having a plurality of primary flow ducts correspondingly receiving engine exhaust gas from said plurality of transport ducts and passing engine exhaust gas to a select plurality of rotor/wing nozzles; and directing the engine exhaust gas from less than said plurality of engines to a selected set of nozzles through a selected set of transport ducts and primary flow ducts when less than said plurality of engines are operating. 8. A method of claim 7 wherein the plurality of engines comprises three and wherein said tandem rotor/wing includes a first blade and a second blade; said first blade having four nozzles, of which two nozzles are ducted to a first primary flow duct and the other two nozzles are ducted to a second and third primary flow ducts, respectively; and said second blade having four nozzles, of which two nozzles are ducted to said first primary flow duct and the other two nozzles are ducted to said second and said third primary flow ducts, respectively, wherein said first primary flow duct receives engine exhaust gas via a first transport duct from said first engine and said second primary flow duct receives engine exhaust gas via a second transport duct from said second engine, when said third engine is non-operable.