A multi-pump apparatus of a work vehicle may include a main housing, a motor shaft, a water pump, and a refrigerant pump. The main housing has a first housing portion and a second housing portion coupled to the first housing portion. The motor shaft is positioned through the first housing portion. The water pump is coupled to the first housing portion and is operable to pump coolant. The water pump is driven by the motor shaft. The refrigerant pump is coupled to the second housing portion and is operable to pump refrigerant. The refrigerant pump is also driven by the motor shaft.

A multi-pump apparatus of a work vehicle may include a main housing, a motor shaft, a water pump, and a refrigerant pump. The main housing has a first housing portion and a second housing portion coupled to the first housing portion. The motor shaft is positioned through the first housing portion. The water pump is coupled to the first housing portion and is operable to pump coolant. The water pump is driven by the motor shaft. The refrigerant pump is coupled to the second housing portion and is operable to pump refrigerant. The refrigerant pump is also driven by the motor shaft.

A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.

A liquid-cooling heat dissipation device including a base and two pumps. The base has a first inlet and a first outlet. The two pumps are disposed on the base and connected to the first inlet and the first outlet in a parallel arrangement.

A pressure washing device is provided with a bypass mode. The device comprises a bypass mode and bypass structure that is in fluid communication with a fluid tank for at least one of storing and cooling a fluid that has been heated to unacceptable levels. The present disclosure further provides various devices and features for managing and mitigating heating and over-heating of fluids and components in communication with the fluids.

A water pump cooler for CPU wherein coolant may efficiently perform heat exchange, comprising at least: at least a heat absorbing component, at least a heat-transfer water pump, at least a heat exchange component and connecting water pipes, wherein a closed loop is formed by the heat-transfer water pump, connecting water pipes and heat exchange component. The heat-transfer water pump is disposed above the heat absorbing component to serve as a cycle power source for the coolant. The heat-transfer water pump includes at least a water pump component, which includes at least a base plate and a plurality of rotor axial impeller sections and rotor centrifugal impeller sections. The coolant is driven by the rotor axial impeller sections to flow into the rotor centrifugal impeller sections, and is then thrown at a high speed by the rotor centrifugal impeller sections to the heat exchange component for efficient heat dissipation. In this way, the coolant may perform heat exchange at a high speed within the closed loop.

A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.

A rotary machine for conveying a fluid includes a drive unit configured to drive a shaft, an impeller arranged at the shaft, and configured to convey the fluid, at least one mechanical seal configured to seal the shaft, a first and a second heat exchange system configured to cool or heat the mechanical seal, the first heat exchange system configured for direct application of a fluid heat carrier at the mechanical seal and the second heat exchange system comprising a heat exchange jacket capable of having a fluid heat carrier flow therethrough without direct contact with the mechanical seal, the first and the second heat exchange systems forming a common heat exchange system in which a common fluid heat carrier is capable of being circulated, and a fan wheel configured to circulate the common fluid heat carrier in the common heat exchange system.

A liquid-cooling heat dissipation device including a base and two pumps. The base has a first inlet and a first outlet. The two pumps are disposed on the base and connected to the first inlet and the first outlet in a parallel arrangement.

A pressure washing device is provided with a bypass mode. The device comprises a bypass mode and bypass structure that is in fluid communication with a fluid tank for at least one of storing and cooling a fluid that has been heated to unacceptable levels. The present disclosure further provides various devices and features for managing and mitigating heating and over-heating of fluids and components in communication with the fluids.