A system and method of a variable speed cooling fan (30) for a skid mounted compressor (22). A magnetic variable speed clutch (38) is mounted to the cooling fan drive shaft (28). The clutch mechanism is driven via by a drive pulley (38) on the crankshaft of the engine (24) driving the compressor (22). The speed of the fan (30) is varied dependent upon the temperature of the fluids being cooled.

Compressor for generating compressed air for a commercial vehicle, having a housing with a piston chamber in a crankcase and a dead space which is configured at least in the cylinder head. The compressor has a valve device with a valve element which has an actuating section and a shut-off body for separating the dead space from the piston chamber, wherein the shut-off body can be lifted up from a valve seat in the direction of the piston chamber in order to open the valve device. The valve element is configured in one piece with the actuating section.

Methods and systems are provided to adaptively control a hydraulic fluid supply to supply a driving fluid for applying a driving force on a piston in a gas compressor, the driving force being cyclically reversed between a first direction and a second direction to cause the piston to reciprocate in strokes. During a first stroke of the piston, a speed of the piston, a temperature of the driving fluid, and a load pressure applied to the piston is monitored. Reversal of the driving force after the first stroke is controlled based on the speed, load pressure, and temperature.

Methods and systems are provided to adaptively control a hydraulic fluid supply to supply a driving fluid for applying a driving force on a piston in a gas compressor, the driving force being cyclically reversed between a first direction and a second direction to cause the piston to reciprocate in strokes. During a first stroke of the piston, a speed of the piston, a temperature of the driving fluid, and a load pressure applied to the piston is monitored. Reversal of the driving force after the first stroke is controlled based on the speed, load pressure, and temperature.

An engine compressor unit including at least one rotary engine; and at least one rotary compressor for compressing at least one gaseous fluid; the rotary engine including an engine housing including at least one engine ring that is rotatably supported in the engine housing about an engine axis, at least one engine cylinder that is arranged in the engine ring, wherein an engine piston is arranged in the at least one engine cylinder so that the engine piston defines a combustion chamber of the at least one engine cylinder together with a wall of the at least one engine cylinder, wherein the engine piston is supported in the at least one engine cylinder by an engine connecting rod so that the engine piston is movable in the at least one engine cylinder in a linear manner.

A reduced-noise pneumatic motor has a housing with a cap disposed at a first end, the cap having an air inlet; a base disposed at a second end, the base having an air outlet hole formed therein and configured to at least partially receive a noise damping system, and a piston pump extending therethrough; and bolts extending from the cap to the base to secure the cap and the base to the housing. A pneumatic piston is disposed within the housing, and includes a shuttle valve situated within a central bore of the pneumatic piston. A piston rod has a first end extending into the piston pump and a second end secured to a spring which biases the piston rod against the pneumatic piston.

In an embodiment, an integrated ground support system for an aircraft is described herein, the system including a frame on which the system is arranged as a singular assembly. An engine, drive train, alternator, bleed air unit, one or more electrical components, and air cycle machine are mounted on the frame. The engine operates at a first operational state associated with a first rotational speed that is independent of a frequency associated with electrical power, if only the electrical power is to be used by the aircraft, and the engine operates at a second operational state associated with a second rotational speed, different from the first rotational speed, that is a function of a pressure associated with bleed air or the conditioned air, if the electrical power and one of the bleed air or the conditioned air are to be used simultaneously by the aircraft.

The power system comprises a working fluid circuit having a high pressure side and a low pressure side and configured to flow a working fluid therethrough. The working fluid circuit further comprises a heater configured to circulate the working fluid in heat exchange relationship with a hot fluid to vaporize the working fluid. The system further comprises serially arranged first expander and second expander fluidly coupled to the working fluid circuit and disposed between the high pressure side and the low pressure side thereof. One of the expanders drives a load and the other expander drives a pump or compressor fluidly coupled to the working fluid circuit between the low pressure side and the high pressure side thereof. A cooler is further arranged and configured to remove heat from the working fluid in the low pressure side of the working fluid circuit.

The power system comprises a working fluid circuit having a high pressure side and a low pressure side and configured to flow a working fluid therethrough. The working fluid circuit further comprises a heater configured to circulate the working fluid in heat exchange relationship with a hot fluid to vaporize the working fluid. The system further comprises serially arranged first expander and second expander fluidly coupled to the working fluid circuit and disposed between the high pressure side and the low pressure side thereof. One of the expanders drives a load and the other expander drives a pump or compressor fluidly coupled to the working fluid circuit between the low pressure side and the high pressure side thereof. A cooler is further arranged and configured to remove heat from the working fluid in the low pressure side of the working fluid circuit.

A pump system and method of operating the same may utilize two relatively smaller turbines that are attached to and used to power a single pump. The two turbines are releasably coupled to the pump via respective one-way clutches, thereby enabling the use of one or both turbines at a time to power the pump. At low loads (e.g., low pump outputs), only one turbine operates to power the pump, and at higher loads (e.g., high pump outputs), both turbines operate to power the pump. By using two smaller turbines instead of one large turbine, the range-ability of the turbine power at the most efficient operating ranges is increased. This improves the fuel efficiency of the pump system. In addition, the dual turbine driven pump system provides increased reliability by preventing the loss of all power to the pump in the event of a turbine malfunction.