Honda Motor Co., Ltd.

Honda Giken Kogyo Kabushiki Kaisha

Osamu Kawamoto

Mineyasu Oana

Masayuki Fukutani

Hiroki Nagata

To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. The intake passageincludes an inlet portion, a curved portionand a reduced diameter portion. The bypass ductis curved away from the central axial line CL in a region corresponding to the curved portionand reduced diameter portionof the intake passage. Between the intake passageand bypass ductis defined an annular space. In the reduced diameter portion, the outer lineris formed with a large number of foreign matter introduction openingsin a circumferential arrangement for communication between the intake passageand annular space. The inner casingis formed with a plurality of foreign matter ejection holesin a circumferential arrangement in a part thereof that curves outward for communication between the annular spaceand bypass duct

Gas turbine engine provided with a foreign matter removal passage

A compressor having a front fan, which rotates to compress intake air, a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air, and a single-stage high-pressure compressor which compresses the compressed air compressed by the low-pressure compressor; a ratio (R/R) of a pressure ratio (R) of the high-pressure compressor to a pressure ratio (R) of the low-pressure compressor is within a range of 4.5 to 6.0.

Compressor having low-pressure and high-pressure compressor operating at optimum ratio between pressure ratios thereof and gas turbine engine adopting the same

In an impeller for centrifugal compressors comprising a plurality of blades each having a base end attached to a central hub, each of the blades is given with a thickness which increases progressively toward a hub end thereof, and a suction surface side of the blade is given with a greater thickness increase rate with respect to a neutral plane than a pressure surface side of the blade. Thereby, the inter-blade channel is narrowed locally in the region near the hub end of the suction surface of each blade, and this locally reduces the aerodynamic loading on the blade. In particular, the surge property is improved, and the generation of radially outwardly directed secondary flows can be minimized. This allows the distribution of aerodynamic loading in the radial direction or from the tip end to the hub end of each blade to be controlled at will, and enables the optimum design of the impeller.

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Wako, Japan

Osamu Kawamoto