Abstract: An axial flow device includes: at least one stage of a compressor including a rotor blade row and a stator vane row; a casing housing the compressor; and an operating range expansion unit having a suction port that opens into a region corresponding to the rotor blade row in an inner surface of the casing, a blow-out port that opens anterior to the rotor blade row in the inner surface of the casing, and a hollow section that is formed inside the casing and communicates the suction port with the blow-out port. A flow path in the blow-out port is inclined reversely to a rotation direction of the rotor blade row relative to the radially inward side.

Abstract: Within a compressor case, a plurality of stages of high-pressure compressor statorsare disposed alternately with a plurality of stages of high-pressure compressor rotorsalong an axial direction. Each stage of the high-pressure compressor statorsincludes a plurality of compressor stator vanes. Each of the compressor stator vaneshas, on a camber line, a camber reference pointin which (???e)/?k is 50% (?, ?e and ?k represents a metal angle, an exit metal angle and a camber angle, respectively). In a vane-shaped cross-section, a distance from a leading edgeto the camber reference pointis set to a 26-38% chord.

Abstract: A dual field instrument may include a first microprocessor that includes a first address bus and a first data bus and performs a first operation process, a second microprocessor that includes a second address bus and a second data bus performs a second operation process that is the same with the first operation process, a first code analysis unit that compresses and encodes histories of data on at least one of the first address bus and the first data bus to generate a first code, a second code analysis unit that compresses and encodes histories of data on at least one of the second address bus and the second data bus to generate a second code, and a first collating unit that collates the first code with the second code so as to determine whether or not the first code corresponds with the second code.

Abstract: A fan of an aircraft engine is provided with a rotating fan rotor for feeding air aftward as a spiral flow and a stator vane for rectifying the spiral flow to be an axial flow. The fan stator vane is provided with a hub end portion extending radially relative to a rotating axis of the fan rotor and a tip end portion leaning toward a suction side. Leading edges of the hub end portion and the tip end portion have sweepback angles of from 27 degrees to 33 degrees relative to a radial direction defined by the rotating axis.

Abstract: A fan of an aircraft engine is provided with a rotating fan rotor for feeding air aftward as a spiral flow and a stator vane for rectifying the spiral flow to be an axial flow. The fan stator vane is provided with a hub end portion extending radially relative to a rotating axis of the fan rotor and a tip end portion leaning toward a suction side. Leading edges of the hub end portion and the tip end portion have sweepback angles of from 27 degrees to 33 degrees relative to a radial direction defined by the rotating axis.

Abstract: A low noise fan stationary blade, wherein a negative lean angle &thgr;L in the reverse direction of a rotating direction is provided near a hub and a positive lean angle &thgr;L in the rotating direction is provided on the other tip side, the negative lean angle &thgr;L is −10°±3° in a high loss area near the hub and the positive lean angle &thgr;L is 30°±3° on the tip side, a positive sweep angle &thgr;s is provided, and the positive sweep angle &thgr;s is 20°±3° on the hub side and 20°±3° also on the tip side, whereby a total pressure loss on both hub and tip sides can be reduced, noise can be reduced on both hub and tip sides, and thus noise can be reduced without lowering an aerodynamic performance.

Abstract: There are provided a negative lean angle &thgr;L of a direction opposite to a rotation direction in the vicinity of a hub, and a positive lean angle &thgr;L of the rotation direction in other regions on a chip side. The negative lean angle &thgr;L is −10°±3° in a high loss region in the vicinity of the hub, and the positive lean angle &thgr;L is 30°±3° on the chip side. Moreover, there is provided a positive sweep angle &thgr;s. The positive sweep angle &thgr;s is 20°±3° on the hub side, and is also 20°±3° on the chip side. Total pressure losses on both the hub and chip sides are reduced, noises can be reduced on both the hub and chip sides, and thereby noise reduction can be achieved without deteriorating aerodynamic capabilities.

Abstract: An improved switching power supply which saves power when under a small to no load, wherein a transformer is provided comprising a primary winding to which a DC current is supplied by turning ON and OFF a switching device and a secondary winding for supplying an output signal to the load; an ON state control circuit turns ON the switching device by using the output signal induced at the secondary winding; an OFF state control circuit turns OFF the switching device using a current control signal obtained from the output signal from the secondary winding and a reference signal; and wherein a delay circuit prolongs the time at which the switching device makes the OFF to ON transition.