Abstract: A multistage gear pump assembly includes first and second gear pumps that use common shafts and are axially separated by a fixed spacer within the housing. Pressurized bearings are provided at opposite axial ends of the first and second gear pumps. The second gear pump handles cruise and idle operations of the aircraft while the first gear pump stage assists in meeting higher demand modes of engine operation. Otherwise, the first gear pump is maintained at a minimal pressure to reduce energy consumption and still provide desired stability and eliminate issues associated with bearing oil whirl associated with prior known arrangements. When additional assistance is required, such as during takeoff, climb, or windmill relight, the first gear pump advantageously contributes to the increased pressure.

Abstract: Vane pump mechanical losses are reduced by removing vane friction losses and replacing them with lower magnitude journal bearing fluid film viscous drag losses. A freely rotating cam ring is supported by a journal bearing. A relatively low sliding velocity is imposed between the cam ring and the vanes). This permits the use of less expensive and less brittle materials in the pump by allowing the pump to operate at much higher speeds without concern for exceeding vane tip velocity limits.

Abstract: Vane pump mechanical losses are reduced by removing vane friction losses and replacing them with lower magnitude journal bearing fluid film viscous drag losses. A freely rotating cam ring is supported by a journal bearing. A relatively low sliding velocity is imposed between the cam ring and the vanes). This permits the use of less expensive and less brittle materials in the pump by allowing the pump to operate at much higher speeds without concern for exceeding vane tip velocity limits.

Abstract: Vane pump mechanical losses are reduced by removing vane friction losses and replacing them with lower magnitude journal bearing fluid film viscous drag losses. A freely rotating cam ring is supported by a journal bearing. A relatively low sliding velocity is imposed between the cam ring and the vanes. This permits the use of less expensive and less brittle materials in the pump by allowing the pump to operate at much higher speeds without concern for exceeding vane tip velocity limits.

Abstract: A filter assembly for a fuel delivery system for actuators and fuel control system of an aircraft engine includes a wash flow filter. Fuel flow velocity is increased through the filter through use of a recirculating passage that is effectively achieved through use of an ejector pump. A portion of the pressurized fuel delivered by the main fuel pump is diverted and serves as a motive fluid that scavenges unfiltered flow from downstream of the filter and recirculates or discharges the recirculated flow to an inlet of the filter. This provides increased velocity to maintain sufficient washing of the filter openings.

Abstract: A rotary machine includes a housing, and a rotating component received therein for rotation relative to the housing. A shaft imparts rotational movement to the rotating component around a first axis from an associated motive input. A bearing assembly is interposed between the rotating shaft and the housing and the bearing assembly includes a bearing member that is self-aligning. The self-aligning bearing assembly includes a bearing member having a recess extending substantially parallel to the first axis, and a journal sleeve received in the recess and interposed between the shaft and the bearing member. The journal sleeve is fixed to the shaft for rotation therewith and includes a flexible joint connection with the shaft to permit self-alignment of the shaft and bearing.

Abstract: A pump assembly includes a housing having a chamber in communication with an inlet and an outlet. A rotating ring, variable displacement vane pump is received in the chamber. The pump, and particularly the rotating ring, is supported by a fluid bearing in the chamber. A control is provided for selectively altering fluid flow to the bearing in response to one of hydrodynamic bearing pressure, boost flow pressure, and the pump stroke.

Abstract: The present invention provides a heat exchange system for a closed loop fuel delivery system. The heat exchange system generally includes a first pump, a heat exchanger, a high pressure pump pressurizes fuel. The heat exchanger, which is located downstream of the first pump, receives the pressurized fuel flow. The high pressure pump, which is located downstream of the heat exchanger, delivers a predetermined amount of fuel flow to a jet engine. The circulating pump receives fuel flow downstream of the heat exchanger and recirculates the fuel flow upstream of the heat exchanger.