Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefit
AssigneeArgo-Tech Corporation
InventorMartin A. Clements
Life of this patent
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Abstract
A fuel delivery system (10) comprises a variable displacement pump (20) for pressurizing fuel. The variable displacement pump has a distinct first pump displacement setting for a first desired mass flow of fuel and a distinct second pump displacement setting for a second desired mass flow of fuel. The variable displacement pump operates in only one of the first and second pump displacement settings. A fuel control (22) with a metering valve downstream of the variable displacement pump selectively regulates fuel delivery.
Claims19
A fuel delivery system for an associated jet aircraft turbine engine during a control system failure comprising:
- a pump for pressurizing fuel, the pump having a distinct first pump displacement setting for a first desired mass flow of fuel and a distinct second pump displacement setting for a second desired mass flow of fuel, wherein the pump operates in only one of the first and second pump displacement settings;
- a metering valve downstream of the pump for selectively regulating fuel delivery;
- and,
- means for preventing engine over-thrust operatively associated with the pump for positioning the pump in the second pump displacement setting in response to a control system failure whereby pump flow to the associated engine is limited to provide over-thrust protection.
A fuel delivery system for an associated jet aircraft turbine engine during a control system failure comprising:
- a pump for pressurizing fuel, the pump having a distinct first pump displacement setting for a first desired high mass flow of fuel and a distinct second pump displacement setting for a second desired low mass flow of fuel, wherein the pump operates in only one of the first and second pump displacement settings, wherein the pump is activated to the second pump displacement setting in response to a control system failure;
- a metering valve downstream of the pump for selectively regulating fuel delivery;
- and,
- a controller for preventing engine over-thrust operatively associated with the pump for positioning the pump in the second pump displacement setting in response to a control system failure whereby pump flow to the associated engine is limited to provide over-thrust protection.
A method of delivering fuel for an associated jet aircraft turbine engine comprising the steps of:
- pressurizing fuel through a pump having first and second fixed displacement settings for a first predetermined, high mass flow of fuel and a second predetermined, low mass flows of fuel;
- metering the fuel through a metering valve for supply to associated fuel nozzles;
- setting the pump to only one of the first and second displacement settings;
- and,
- positioning the pump in the second pump displacement setting in response to a control system failure whereby pump flow to the associated engine is limited to provide over-thrust protection.
A fuel delivery system for preventing engine over-thrust for an associated jet aircraft turbine engine comprising:
- a variable displacement pump for pressurizing fuel operative in either a first predetermined, high mass flow, fuel displacement setting or a second predetermined, low mass flow, fuel displacement setting;
- a metering valve downstream of the variable displacement pump for selectively regulating fuel delivery;
- and,
- a controller for selectively positioning the pump in only one of the first and second fuel displacement settings, and positioning the pump to operate in the second fuel displacement setting in the event of failure of the controller thereby preventing engine over-thrust.
Dependencies are inferred from the claim text.