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There is a turbofan jet engine including an engine core. The engine core includes a fan and a compressor. The engine core includes a combustion chamber and a turbine functionally coupled to the compressor. The engine core includes a nozzle in fluid communication with the turbine. The turbofan jet en

There is a turbofan jet engine including an engine core. The engine core includes a fan and a compressor. The engine core includes a combustion chamber and a turbine functionally coupled to the compressor. The engine core includes a nozzle in fluid communication with the turbine. The turbofan jet engine includes a nacelle. The nacelle includes a forward extension proximate the fan and extending forward therefrom. The forward extension is funnel shaped to impart radial momentum to intake air during operation. The nacelle includes a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air. The vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. The vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan.

대표청구항 ▼

1. A turbofan jet engine comprising: a) an engine core including: a1) a fan having an intended rotation direction;a2) a compressor in fluid communication with the fan;a3) a combustion chamber in fluid communication with the compressor;a4) a turbine in fluid communication with the combustion chamber

1. A turbofan jet engine comprising: a) an engine core including: a1) a fan having an intended rotation direction;a2) a compressor in fluid communication with the fan;a3) a combustion chamber in fluid communication with the compressor;a4) a turbine in fluid communication with the combustion chamber and functionally coupled to the compressor; anda5) a nozzle in fluid communication with the turbine; andb) a nacelle including: b1) a forward extension proximate the fan and extending forward therefrom, and shaped to impart radial momentum to intake air during operation; andb2) a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air wherein the shape imparts angular momentum to intake air in the same direction as the intended rotation of the fan. 2. The engine of claim 1, wherein the forward extension is funnel shaped. 3. The engine of claim 1, wherein the vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. 4. The engine of claim 1, wherein the vortex device comprises a twisted fin extending across the forward extension. 5. The engine of claim 1, wherein the vortex device includes an air channel disposed through the forward extension and set at a rotational angle. 6. The engine of claim 1, wherein the vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan. 7. A turbofan jet engine nacelle, comprising: a) an engine core including: a1) a fan; a2) a compressor in fluid communication with the fan; a3) a combustion chamber in fluid communication with the compressor; a4) a turbine in fluid communication with the combustion chamber and functionally coupled to the compressor; and a5) a nozzle in fluid communication with the turbine; and b) a nacelle including a forward extension proximate the fan and extending forward therefrom, and shaped to impart radial momentum to intake air during operation wherein the shape imparts angular momentum to intake air in the same direction as the intended rotation of the fan. 8. The nacelle of claim 7 further comprising a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air. 9. The engine of claim 8, wherein the forward extension is funnel shaped. 10. The engine of claim 9, wherein the vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. 11. The engine of claim 10, wherein the vortex device comprises a twisted fin extending across the forward extension. 12. The engine of claim 11, wherein the vortex device includes an air channel disposed through the forward extension and set at a rotational angle. 13. The engine of claim 12, wherein the vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan. 14. A turbofan jet engine nacelle, comprising: a) an engine core including: a1) a fan; a2) a compressor in fluid communication with the fan; a3) a combustion chamber in fluid communication with the compressor; a4) a turbine in fluid communication with the combustion chamber and functionally coupled to the compressor; and a5) a nozzle in fluid communication with the turbine; and b) a nacelle including: b1) a forward extension proximate the fan and extending forward therefrom, and shaped to impart radial momentum to intake air during operation; and b2) a vortex device disposed inside the forward extension and shaped to impart angular momentum to intake air wherein the shape imparts angular momentum to intake air in the same direction as the intended rotation of the fan. 15. The engine of claim 14, wherein the forward extension is funnel shaped. 16. The engine of claim 15, wherein the vortex device includes a fixed blade extending from the interior of the forward extension and set at a rotational angle. 17. The engine of claim 16, wherein the vortex device comprises a twisted fin extending across the forward extension. 18. The engine of claim 17, wherein the vortex device includes an air channel disposed through the forward extension and set at a rotational angle. 19. The engine of claim 18, wherein the vortex device is shaped and positioned to direct intake air substantially perpendicular to the blades of the fan.