Abstract: A hub-side leading edge part of a fan first-stage rotating blade 10 for taking an air thereinto more extends in a forward direction of an engine than a tip-side leading edge part and a mid-span leading edge part. The hub side of the fan first-stage rotating blade 10 is integrally connected as one with the tip side and the mid span while having a longer chord length than those of the tip side and the mid span. A radius at a root of the hub-side leading edge part is set in a boss ratio of 0 to 0.4.

Abstract: A leading edge part of a fan rotating blade for taking air thereinto is provided with a vertical hub portion positioned on the hub side so as to be substantially perpendicular to a fan rotary shaft, a backward mid-span portion inclined toward the downstream side from the hub side to the mid-span portion, and a forward inclined tip portion inclined toward the upstream side from the mid-span side to the tip portion.

Abstract: [Object] An object of the invention is to provide a fan rotating blade for a turbofan engine capable of increasing a bypass ratio by increasing an intake air flow rate without enlarging a diameter of a fan and an inner diameter of a casing and of realizing a decrease in weight of an engine as well as a decrease in fuel consumption and noise. [Means for Solving the Problems] A leading edge part 11 of a fan rotating blade 10 for taking air thereinto is provided with a vertical hub portion 12 positioned on the hub side so as to be substantially perpendicular to a fan rotary shaft, a backward mid-span portion 13 inclined toward the downstream side from the hub side to the mid-span portion, and a forward inclined tip portion 14 inclined toward the upstream side from the mid-span side to the tip portion.

Abstract: A turbofan engine of the invention is provided with a fan first-stage moving blade for taking an air therein, and a spinner rotationally driving the fan first-stage moving blade, the spinner has a spiral blade extending spirally to an outer side in a radial direction, sucking the air from a front face of the spinner and supplying the air to the fan first-stage moving blade. Further, the fan first-stage moving blade and the spinner are integrally coupled, and the spiral blade and the fan first-stage moving blade are formed such that blade surfaces are smoothly connected.

Abstract: A turbofan engine has a fan on a front side thereof and a turbine driving the fan. The turbofan engine includes a disk rotationally driven by the turbine, a spinner detachably mounted at a front side of the disk, a spiral blade integrally mounted on a surface of the spinner, and a rear moving blade detachably mounted on an outer circumferential surface of the disk. The spiral blade and the rear moving blade form a first-stage moving blade of the fan.

Abstract: A hub-side leading edge part of a fan first-stage rotating blade 10 for taking an air thereinto more extends in a forward direction of an engine than a tip-side leading edge part and a mid-span leading edge part. The hub side of the fan first-stage rotating blade 10 is integrally connected as one with the tip side and the mid span while having a longer chord length than those of the tip side and the mid span. A radius at a root of the hub-side leading edge part is set in a boss ratio of 0 to 0.4.

Abstract: A turbofan engine of the invention is provided with a fan first-stage moving blade for taking an air therein, and a spinner rotationally driving the fan first-stage moving blade, the spinner has a spiral blade extending spirally to an outer side in a radial direction, sucking the air from a front face of the spinner and supplying the air to the fan first-stage moving blade. Further, the fan first-stage moving blade and the spinner are integrally coupled, and the spiral blade and the fan first-stage moving blade are formed such that blade surfaces are smoothly connected.

Abstract: A turbofan engine has a fan on a front side thereof and a turbine driving the fan. The turbofan engine includes a disk rotationally driven by the turbine, a spinner detachably mounted at a front side of the disk, a spiral blade integrally mounted on a surface of the spinner, and a rear moving blade detachably mounted on an outer circumferential surface of the disk. The spiral blade and the rear moving blade form a first-stage moving blade of the fan.

Abstract: A microwave reflection control device of the present invention comprises a reflection member which divides the inside of an inlet duct of a gas turbine engine into a plurality of areas in a peripheral or radial direction with respect to a duct center axis. The reflection member is formed into a reflection curved surface shape to block and diffuse a microwave which comes toward a fan moving blade from the inlet duct. Thus, reflection of the microwave by the fan moving blade is suppressed.

Abstract: An axial flow compressor is disclosed. The axial flow compressor has a casing defining a compression passage therein. The casing has an inner surface and a center axis extending along the elongated direction of the casing. A plurality of rotor blades fixed to a disk rotate in the compression passage around the center axis. Each of the rotor blades has a tip, and the tip defines a rotation area having a width extending in the direction along the center axis. A circular concavity is formed on the inner surface of the casing extending completely around the inner surface. The circular concavity has a continuous curved shape in a sectional view, and the circular concavity is formed at a portion corresponding to a front part of the rotation area of the rotor blades.