Honda Motor Co., Ltd.

Honda Giken Kogyo Kabushiki Kaisha

Mineyasu Oana

Osamu Kawamoto

Naoki Kuno

Masayuki Fukutani

Hidehiko Nakata

Shuichi Honda

Seiji Yamamoto

Hiroki Nagata

The effective efficiency of a centrifugal compressor can be improved by achieving a uniform distribution of fluid velocity across the outlet end of a fluid passage of an axial diffuser for the centrifugal compressor and a high static pressure recovery ratio Cp in the axial diffuser passage. The cross section of each axial diffuser passage is configured such that a relatively high velocity fluid flow in an upstream part of the diffuser passage is directed toward a negative pressure side of a cross section thereof. It can be accomplished by directing a minor axis of a cross section of the diffuser passage substantially perpendicularly to a direction directed from a center of the cross section of the diffuser passage to the central axial line of an impeller or directing the minor axis toward the central axial line of the impeller.

Axial diffuser for a centrifugal compressor

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

A throttle valve for adjusting an amount of intake air to an internal combustion engine includes throttle shafts disposed in an intake air passage perpendicularly across the longitudinal axis of the air passage, and first and second valve members mounted on the throttle shafts for opening/closing about the throttle shafts independently of each other. By these first and second valve members, there are formed main air passages for causing air to flow in the intake air passage along the longitudinal axis of the intake air passage toward the internal combustion engine and auxiliary intake air passages for causing air to flow in the intake air passage substantially perpendicularly across the longitudinal axis of the air passage.

Throttle valve

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

Mineyasu Oana