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US 2012/0186673 A1Published application
Aircraft engine fuel system
AssigneeHamilton Sundstrand Corporation
InventorSteven A. Heitz
Life of this patent
Estimating the term…
Abstract
An aircraft fuel system is provided and includes a metering valve having inlet and outlet sides to monitor 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 and 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.
Claims20
An aircraft fuel system, comprising:
- a metering valve having inlet and outlet sides to monitor 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;
- and
- 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.
1 more element
An aircraft engine fuel system, comprising:
- a metering valve having inlet and outlet sides to monitor fuel flow from the inlet to the outlet side;
- main and auxiliary pumps to pump first and second fuel toward the inlet side, respectively;
- a pressure regulating valve operably disposed between the main pump and the inlet side to restrict the first fuel flow in accordance with a pressure differential between the outlet side and second fuel pressure and to force a portion of the first fuel into a bypass condition;
- a check valve, coupled to the pressure regulating valve, which, when closed restricts a flow of the bypassed portion of the first fuel toward the auxiliary pump;
- and
- an ejector valve, operably disposed between the check valve and the auxiliary pump, which, when the check valve is closed, pumps second fuel from the pressure regulating valve toward the auxiliary pump.
3 more elements
An aircraft engine fuel system, comprising:
- a first valve to monitor fuel flow;
- first and second pumps to pump fuel toward the first valve;
- second and third valves to regulate an amount of fuel permitted to be pumped to the first valve;
- and
- a third pump operably disposed between the third valve and the second pump to pump a portion of fuel toward the second pump, wherein:
- during start conditions, substantially all of the fuel pumped by the first and second pumps is permitted to be pumped to the first valve,
- during climb conditions, substantially all of the fuel pumped by the first pump is permitted to be pumped to the first valve and excess fuel pumped by the second pump is bypassed, and
- during idle conditions, substantially all of the fuel pumped by the second pump and excess fuel pumped by the first pump is bypassed.
5 more elements
Dependencies are inferred from the claim text.