Patent ID: 8991152
Filing Date: 2015-03-31
Classification: F02C,F05D,Y10T

Abstract:
1. An aircraft fuel system, comprising: a metering valve having inlet and outlet sides to control fuel flow from the inlet to the outlet side; a check valve that, when opened, allows fuel to flow toward the inlet side during start and climb conditions and, when closed, prevents such fuel flow; an ejector pump, which is operably disposed between the check valve and the metering valve, and which, with the check valve closed, pumps fuel toward the inlet side during idle conditions; and a pressure regulating valve (PRV) to restrict fuel flow from main and auxiliary pumps, which are disposed to pump fuel along separate fuel lines to the inlet side in accordance with a pressure differential between the outlet side and fuel pumped by the auxiliary pump, the PRV comprising: first and second connected piston heads elastically anchored to a first valve end and biased toward a second valve end, the second piston head having a groove that fluidly communicates with a conduit by which excess fuel pumped by the auxiliary pump is bypassed from the inlet side with the first and second piston heads moved toward the first valve end by a first distance from the second valve end, and the first piston head having a groove that fluidly communicates with a conduit by which excess fuel pumped by the main pump is bypassed from the inlet side with the first and second piston heads only moved toward the first valve end by a second distance from the second valve end, which is larger than the first distance.