Abstract: A heat pump system, utilizing a multi-component refrigerant blend in which a low pressure component is zeotropic with respect to the remainder of the blend, separates the low pressure component by rectification to enhance heating capability in low ambient temperatures. Vapor is separated from liquid in the effluent of the condenser of a heat pump, at a pressure in equilibrium at a temperature midway between the evaporator and condenser effluent temperatures, the vapor being applied to an auxiliary inlet at a mid pressure point in the compression stroke of the compressor.

Abstract: A heat pump system, utilizing a multi-component refrigerant blend in which a low pressure component is zeotropic with respect to the remainder of the blend, separates the low pressure component by rectification to enhance heating capability in low ambient temperatures. Vapor is separated from liquid in the effluent of the condenser of a heat pump, at a pressure in equilibrium at a temperature midway between the evaporator and condenser effluent temperatures, the vapor being applied to an auxiliary inlet at a mid pressure point in the compression stroke of the compressor.

Abstract: One or more thermostatically responsive valves are positioned to regulate the diversion of suction gas flow over the motor to cool the motor. The valves are responsive to motor temperature and only open when motor cooling is required.

Abstract: Improved axial compliance in a scroll compressor 10 between a fixed scroll 11 and an orbiting scroll 13 is achieved by providing at least one dynamic back pressure chamber 25 disposed behind the orbiting scroll 13. A pressurized fluid is bled from a selected one of compression pockets 19 through a port 21 formed in the orbiting scroll 13 into the dynamic back chamber 25 to provide varying on sub-cycle basis back pressure to reduce friction between the fixed and orbiting scrolls. A static back pressure chamber 27, also disposed behind the orbiting scroll 13, may be provided into which pressurized fluid is bled from a selected one of the compression pockets 19 to provide an additional back pressure on the scroll 13 which is substantially constant over the cycle.

Abstract: The motion of the orbiting scroll is used to cause pumping of oil in a hermetic horizontal scroll compressor.

Abstract: A scroll compressor includes a fixed scroll element stationarily mounted on a support and an orbiting scroll element which is caused by an eccentric crank portion of a drive shaft to conduct an orbiting motion relative to the fixed scroll element. The drive shaft is rotatably mounted on the support by respective support bearings and carries a plurality of counterweights which have such respective masses and angular distributions about the shaft that the loadings of the support bearings by the drive shaft during the operation of the scroll compressor are minimized.

Abstract: A supersonic combustion ram cannon (1) includes a conical projectile (8) with a flat base (9) which produces a subsonic wake (12) as it flies through a barrel (2). The projectile is configured to avoid a normal shock, relying instead on supersonic compression, combustion and gas expansion. The supersonic combustion of a fuel-oxidizer mixture around the tail of the subsonic wake, pressurizes the wake and drives the projectile forward. By utilizing wake stabilized supersonic combustion, the compression and combustion pressures can be matched to the limiting barrel working pressure, thereby providing for optimum thrust and maximum projectile acceleration.

Abstract: For a winged high speed missile that includes a two-dimensional inlet supplying air to the missile power plant, the compression ramp of the inlet is oriented with respect to the outwash angle produced by the missile body and the underneath surface of the wing such that the compression ramp of the inlet is subjected to an effective angle of attack. By proper inlet orientation the captured flow is turned inwardly toward the missile center line further compressing the incoming air.

Abstract: Precompression fins extending perpendicular from the wings of a high speed missile are judiciously located relative to an axisymmetric inlet of an airbreathing power plant such that the outwash angle induced by the body and wing of the missile enhances the performance of the inlet.