Abstract: An industrial ejector includes: a Laval nozzle in which a first channel which has a throat and along which a fluid flows in a first direction is formed; and a main body which is formed in a tubular shape, in which the Laval nozzle disposed therein is fixed to a part of an inner surface thereof, and in which a second channel is formed between the rest of the inner surface and the Laval nozzle. The second channel is disposed at a first side with respect to the first channel in a second direction perpendicular to the first direction. An opening is obliquely cut and formed in an end of the first channel at a downstream side and inclined toward the first side in the downstream direction and then toward the second channel.

Abstract: An ejector includes: a Laval nozzle in which a first channel which has a throat and along which a fluid flows in a first direction is formed; and a main body which is formed in a tubular shape, in which the Laval nozzle disposed therein is fixed to a part of an inner surface thereof, and in which a second channel is formed between the rest of the inner surface and the Laval nozzle. The second channel is disposed at a first side with respect to the first channel in a second direction perpendicular to the first direction, and an opening formed in an end of the first channel at a downstream side is inclined to be approaching to the first side toward the downstream side.

Abstract: Cavitation is reduced in a rotary pump while the pump performance is maintained by utilizing a low-temperature fluid source already present in the pump system. The fluid from the low-temperature fluid source receives heat from the fluid flowing to the pump, thereby lowering its temperature and the saturated vapor pressure, which increases the allowable margin for a decrease in fluid pressure and reduces the occurrence of cavitation. The pump system may be used for a liquid rocket engine. The fluid velocity of the fluid directed to the pump is low before releasing heat, so there is only a slight pressure loss at the pump. Accordingly, the temperature is lowered and the occurrence of cavitation is reduced within the pump.

Abstract: The occurrence of cavitation is reduced in a rotary pump while the pump performance is maintained. A low-temperature source present in the pump system is utilized, and heat exchange with the fluid flowing to the pump is performed with this low-temperature source, thereby lowering the temperature of the fluid flowing into the pump and lowering the saturated vapor pressure of this fluid, which increases the allowable margin for a decrease in the pressure of the fluid and reduces the occurrence of cavitation. In the case of a liquid rocket engine, a coolant or another propellant B whose temperature is lower than that of the primary propellant A can be employed as this low-temperature source. The propellant B is passed through a heat exchanger 2 by a pump 4, which results in heat exchange with the propellant A from a tank 3, and lowers the fluid temperature. Since the fluid velocity of the propellant A is low at the time of this inflow, there is only slight pressure loss inside the heat exchanger 2.