초록 ▼

A spinner mounting at least one propeller hub and having a blade platform for each hub formed on the spinner body formed from a thermal insulating material capable of withstanding exhaust gasses. The platform is formed in a shape that presents an aerodynamic surface in the direction of travel of the

A spinner mounting at least one propeller hub and having a blade platform for each hub formed on the spinner body formed from a thermal insulating material capable of withstanding exhaust gasses. The platform is formed in a shape that presents an aerodynamic surface in the direction of travel of the system, preferably at a predetermined effective blade angle so as to act in concert with the blade and the gas path to minimize drag or to optimize thrust. The system may include two sets of propeller blades, and each includes a spinner and blade platform.

대표청구항 ▼

1. A spinner device for an open rotor propeller system having a propeller hub mounting a propeller blade using a rotor blade spar, comprising: an aerodynamically shaped spinner body covering the hub of at least one propeller having an aerodynamic blade shape, the spinner being formed from a solid th

1. A spinner device for an open rotor propeller system having a propeller hub mounting a propeller blade using a rotor blade spar, comprising: an aerodynamically shaped spinner body covering the hub of at least one propeller having an aerodynamic blade shape, the spinner being formed from a solid thermal insulating material;a blade platform for each propeller, the platform extending radially out from the spinner body proximate the propeller hub and having an opening for the rotor blade spar to mount the blade on the hub, the platform extending radially out at least as far as an exhaust gas stream having a gas path, whereby the platform thermally isolates the hub and spar from exhaust gasses. 2. The device of claim 1, wherein the platform is formed from a thermal insulating material capable of withstanding the exhaust gasses at temperatures of approximately 900° F. (482° C.). 3. The device of claim 1, wherein platform is formed in a shape that presents an aerodynamic surface in the direction of travel of the system. 4. The device of claim 3, wherein the shape compliments the blade shape at a predetermined effective blade angle so as to act in concert with the blade and the gas path. 5. The device of claim 3, wherein the shape and blade angle are set to minimize drag, optimize thrust, or apply rotational forces on the platform to further rotate the propeller. 6. The device of claim 1, wherein the open rotor propeller system includes two rotors supporting two sets of propeller blades, and each set of propeller blades includes a spinner and blade platform. 7. The device of claim 6, wherein both platforms are formed in a shape that presents an aerodynamic surface in the direction of travel of the system to compliment the blade shape at a predetermined effective blade angle so as to act in concert with the blade and the gas path. 8. The device of claim 7, wherein the shape and blade angle are set to minimize drag, optimize thrust, or apply rotational forces on the platform to further rotate the propeller. 9. In an open rotor propeller system having a spinner mounting at least one propeller hub, spar and blades having an aerodynamic blade shape, and an engine for driving the at least one propeller hub and producing exhaust gas, the improvement comprising: a blade platform device extending radially out from the spinner at the propeller hub and having an opening for the rotor blade spar to mount the blade on the hub, the platform being formed from a material for thermally isolating the hub and spar from the exhaust gas, the platform extending radially out at least as far as the exhaust gas stream having a gas path. 10. The device of claim 9, wherein the platform is formed from a thermal insulating material capable of withstanding the exhaust gasses at temperatures of approximately 900° F. (482° C.). 11. The device of claim 9, wherein the platform is formed in a shape that presents an aerodynamic surface in the direction of travel of the system. 12. The device of claim 11, wherein the shape compliments the blade shape at a predetermined effective blade angle so as to act in concert with the blade and the gas path. 13. The device of claim 12, wherein the shape and blade angle are set to minimize drag, optimize thrust, or apply rotational forces on the platform to further rotate the propeller. 14. The device of claim 9, wherein the open rotor propeller system includes two rotors supporting two sets of propeller blades, and each set of propeller blades includes a spinner and blade platform. 15. The device of claim 14, wherein both platforms are formed in a shape that presents an aerodynamic surface in the direction of travel of the system to compliment the blade shape at a predetermined effective blade angle so as to act in concert with the blade and the gas path. 16. The device of claim 15, wherein the shape and blade angle are set to minimize drag, optimize thrust, or apply rotational forces on the platform to further rotate the propeller. 17. An open rotor propeller system, comprising: at least one propeller hub, spar and blades having an aerodynamic blade shape;an engine for driving the at least one propeller hub and producing exhaust gas; anda blade platform device on the spinner the platform extending radially out from the propeller hubs and having an opening for the rotor blade spar to mount the blade on the hub, the platform being formed from a material for thermally isolating the hub and spar from the exhaust gas, the platform extending radially out at least as far as the exhaust gas stream gas flow path. 18. The system of claim 17, wherein the platform is formed from a thermal insulating material capable of withstanding the exhaust gasses at temperatures of approximately 900° F. (482° C.). 19. The system of claim 17, wherein the platform is formed in a shape that presents an aerodynamic surface in the direction of travel of the system, wherein the shape compliments the blade shape at a predetermined effective blade angle so as to act in concert with the blade and the gas path. 20. The system of claim 19, wherein the shape and blade angle are set to minimize drag, optimize thrust, or apply rotational forces on the platform to further rotate the propeller.