Abstract: A pump assembly includes a pump unit having a centrifugal pump and a variable pump supplying pressurized flow. A fuel control assembly receives flow from the pump unit and includes at least one metering valve and at least one throttling valve. A control for the variable pump receives first and second pressure signals indicative of a pressure differential across the throttling valve, or across the metering valve/throttling valve combination, for altering operation of the variable pump in response to the pressure differential.

Abstract: A multi-stage centrifugal pump assembly allows for multiple fixed ratio pressure levels. The multiple pressure levels permit optimization of actuation loops without the need for pressure regulators, and can be used directly by the actuators.

Abstract: A fuel system includes a pump unit having at least a fixed displacement pump supplying pressurized flow. A fuel control assembly receives flow from the pump unit and includes at least one metering valve and at least one throttling valve. A control (bypass valve control) for the fixed displacement pump receives first and second pressure signals indicative of a pressure differential across the throttling valve, or across the metering valve/throttling valve combination, for altering output from the fixed displacement pump in response to the pressure differential. In other embodiments, the pump unit includes a centrifugal pump and a fixed displacement pump that can be fully or partially redundant depending on sizing of the pumps, and the system requirements.

Abstract: A multi-stage centrifugal pump assembly allows for multiple fixed ratio pressure levels. The multiple pressure levels permit optimization of actuation loops without the need for pressure regulators, and can be used directly by the actuators.

Abstract: A fuel system includes a pump unit having at least a fixed displacement pump supplying pressurized flow. A fuel control assembly receives flow from the pump unit and includes at least one metering valve and at least one throttling valve. A control (bypass valve control) for the fixed displacement pump receives first and second pressure signals indicative of a pressure differential across the throttling valve, or across the metering valve/throttling valve combination, for altering output from the fixed displacement pump in response to the pressure differential. In other embodiments, the pump unit includes a centrifugal pump and a fixed displacement pump that can be fully or partially redundant depending on sizing of the pumps, and the system requirements.

Abstract: A pump assembly includes a pump unit having a centrifugal pump and a variable pump supplying pressurized flow. A fuel control assembly receives flow from the pump unit and includes at least one metering valve and at least one throttling valve. A control for the variable pump receives first and second pressure signals indicative of a pressure differential across the throttling valve, or across the metering valve/throttling valve combination, for altering operation of the variable pump in response to the pressure differential.

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 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: 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: 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 bearing assembly is provided for a fuel delivery system that includes a pump (10) having a housing that rotatably receives a rotor (20) carrying vanes (26) thereon, a cam ring (70) received between the housing and rotor (20), and a support member of yoke (50) encompassing the cam ring (70) to selectively vary fuel flow. The bearing assembly (80) is a journal bearing between the yoke (50) and the cam ring (70) and includes an annular surface having a central opening therethrough. The annular surface includes a first, high pressure pad (102) and a second, low pressure pad (104) substantially diametrically opposite the first pad and separated by first and second lands (106, 108). The circumferential extent of the first pad (102) is at least as great as an inner diameter of the cam ring (70). Circumferential ends of the second pad (104) are wider than circumferential ends of the first pad.

Abstract: A bearing assembly is provided for a fuel delivery system that includes a pump (10) having a housing that rotatably receives a rotor (20) carrying vanes (26) thereon, a cam ring (70) received between the housing and rotor (20), and a support member of yoke (50) encompassing the cam ring (70) to selectively vary fuel flow. The bearing assembly (80) is a journal bearing between the yoke (50) and the cam ring (70) and includes an annular surface having a central opening therethrough. The annular surface includes a first, high pressure pad (102) and a second, low pressure pad (104) substantially diametrically opposite the first pad and separated by first and second lands (106, 108). The circumferential extent of the first pad (102) is at least as great as an inner diameter of the cam ring (70). Circumferential ends of the second pad (104) are wider than circumferential ends of the first pad.

Abstract: A dual lobe, split ring, variable displacement roller vane pump is provided for supplying an aircraft engine varying amount of fuel. The pump includes a housing having an inlet and an outlet, a rotor rotatably mounted within the housing and having a plurality of slots, and a plurality of roller vane assemblies operatively mounted within the slots. The roller vane assemblies include a shoe or rocker that receives a roller. The rocker is mounted for pivoting movement in the slot whereby large bearing surfaces carry the load. Moreover, the pivoting design of the roller vane assembly provides for a substantial contribution from under vane pump flow.