There is described an airfoil combination for aircraft turbofan, designed to save fuel in aircraft operation, which is composed by two wings (5) and two supports (6) articulated or not, for each of the wings (5). These two wings (5) are located inside the turbofan, internally to the outer fairing (3
There is described an airfoil combination for aircraft turbofan, designed to save fuel in aircraft operation, which is composed by two wings (5) and two supports (6) articulated or not, for each of the wings (5). These two wings (5) are located inside the turbofan, internally to the outer fairing (3) of the turbofan and externally to the other components of the turbofan. In one of the embodiments, the two wings may have high-lifting devices, such as flaps. The two wings use the “blown” air at great speed by the fan (1) to generate a pre-determined lifting effect pursuant to the flight phases and the operating regimes of the turbofans to compensate totally or partially the weight of the turbofan itself, reducing the lift effort to be generated by the aircraft wings. As the lift force generated by a wing is directly proportional to the square root of the air speed which passes over its surfaces, the lift effect obtained as described above is proportionally very high in relation to the area of the wings (5) that are the subject matter of the present invention.
대표청구항▼
1. An airfoil combination for a turbofan, the turbofan comprising: a fan,a stator,an outer fairing receiving the fan and the stator therein, andan inner fairing,the airfoil combination comprising at least two cambered wings disposed inside the turbofan such that each cambered wing is positioned outs
1. An airfoil combination for a turbofan, the turbofan comprising: a fan,a stator,an outer fairing receiving the fan and the stator therein, andan inner fairing,the airfoil combination comprising at least two cambered wings disposed inside the turbofan such that each cambered wing is positioned outside the inner fairing and inside the outer fairing, each cambered wing including an upper wing surface that is more convex than a lower wing surface and positioned within the turbofan so as to generate a pre-determined lift when a fluid is passed thereover. 2. The airfoil combination for a turbofan according to claim 1, wherein each of the cambered wings is provided with at least two articulated supports disposed internally to the external fairing of the turbofan. 3. The airfoil combination for a turbofan according to claim 2, wherein an attack angle of each cambered wing is modifiable relative to a direction of a fluid passed thereover via a servomechanism. 4. The airfoil combination for a turbofan according to claim 1, wherein each of the cambered wings is provided with at least two non-articulated supports provided internally to the outer fairing of the turbofan. 5. The airfoil combination for a turbofan according to claim 1, wherein each of the cambered wings has at least two articulated supports that allow an attack angle of each cambered wing to be modified relative to a direction of a fluid passed thereover. 6. The airfoil combination for a turbofan according to claim 5, wherein the attack angle of each cambered wing is modifiable via a servomechanism. 7. An airfoil combination for a turbofan, the turbofan comprising: a fan,a stator,an inner fairing, andan outer fairing receiving the fan and the stator therein,the airfoil combination comprising at least two cambered wings each including an upper wing surface that is more convex than a lower wing surface and positioned within the turbofan so as to generate a pre-determined lift when a fluid is passed thereover, each of the cambered wings further including a movable flap such that an angle of each flap relative to its respective cambered wing is movable so as to modify lift that is generated when a fluid is passed thereover. 8. The airfoil combination for a turbofan according to claim 7, wherein each of the cambered wings is provided with at least two articulated supports disposed internally to the external fairing of the turbofan. 9. The airfoil combination for a turbofan according to claim 7, wherein each of the cambered wings is provided with at least two non-articulated supports disposed internally to the external fairing of the turbofan. 10. The airfoil combination for a turbofan, according to claim 7, wherein each of the cambered wings has at least two articulated supports that allow an attack angle of each cambered wing to be modified relative to a direction of a fluid passed thereover. 11. The airfoil combination for a turbofan according to claim 10, wherein the attack angle of each cambered wing is modifiable via a servomechanism. 12. The airfoil combination for a turbofan according to claim 7, wherein the angle of each flap is modifiable via a servomechanism.
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이 특허에 인용된 특허 (4)
McConnell Charles H. (Seattle WA), Engine installation for aircraft.
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