MECHANICAL DEMAND FUEL PUMPING SYSTEM
A fuel system for a gas turbine engine includes an accessory gearbox driven by a mechanical link to the gas turbine engine, a primary fuel pump providing a first fuel flow during engine operation, and a secondary fuel pump providing a second fuel flow. The primary fuel pump and the secondary fuel pump are driven by an output of the accessory gearbox.
1 . A fuel system for a gas turbine engine comprising:
an accessory gearbox driven by a mechanical link to the gas turbine engine;
a primary fuel pump providing a first fuel flow during engine operation;
a secondary fuel pump providing a second fuel flow, wherein the primary fuel pump and the secondary fuel pump are driven by an output of the accessory gearbox.
2 . The fuel system as recited in claim 1 , wherein the first fuel pump and the second fuel pump both receive fuel flow from a common inlet passage and both the first fuel pump and the second fuel pump communicate the corresponding one of the first fuel flow and the second fuel flow to a common outlet passage.
3 . The fuel system as recited in claim 2 , including a first control valve upstream of the secondary fuel pump and a second control valve downstream of the secondary fuel pump, the first control valve and the second control valve controlling communication of fuel to and from the secondary fuel pump.
4 . The fuel system as recited in claim 2 , including a pump drive gearbox selectively coupled to drive the secondary fuel pump by a clutch means.
5 . The fuel system as recited in claim 1 , including a first pressure relief valve for switching the primary fuel pump and the secondary fuel pump between a series arrangement where the first fuel flow is provided by both the primary and secondary fuel pumps and a parallel arrangement where the first fuel flow is provided by the primary fuel pump and the secondary fuel flow is provided by the secondary fuel pump.
6 . The fuel system as recited in claim 5 , wherein the first pressure relief valve is disposed between an outlet of the primary fuel pump and an inlet of the secondary fuel pump, wherein the first pressure relief valve opens to communicate fuel from the primary fuel pump to the secondary fuel pump to provide the first fuel flow in a first operating condition and the first pressure relief valve closes such that the secondary fuel pump provides the second fuel flow in parallel with the first fuel flow provided by the primary mechanical fuel pump to a common fuel passage in a second operating condition.
7 . The fuel system as recited in claim 6 , including a first check valve in a first passage downstream of the primary mechanical fuel pump to control fuel flow from the first passage into the common fuel passage and a second check valve in a second passage communicating fuel to an inlet of the secondary fuel pump.
8 . The fuel system as recited in claim 7 , including a second pressure relief valve downstream of both the primary fuel pump and the secondary fuel pump for directing fuel flow away from the common fuel passage in response to a pressure within the common fuel passage above a predefined pressure.
9 . The fuel system as recited in claim 1 , wherein a flow capacity of the primary fuel pump and the secondary fuel pump are different.
10 . The fuel system as recited in claim 1 , wherein a flow capacity of the primary fuel pump and the secondary fuel pump are the same.
11 . A gas turbine engine comprising:
a fan rotatable within a fan nacelle;
a core engine including a compressor communicating compressed air to a combustor where compressed air is mixed with fuel and ignited to generate a high-energy gas flow expanded through a turbine;
an accessory gearbox driven by a mechanical link to the turbine;
a primary fuel pump providing a first fuel flow to the combustor during engine operation; and
a secondary fuel pump providing a second fuel flow to the combustor during engine operation in response to a predefined engine operating condition, wherein the primary fuel pump and the secondary fuel pump are driven by an output of the accessory gearbox.
12 . The gas turbine engine as recited in claim 11 , wherein the first fuel pump and the second fuel pump both receive fuel flow from a common inlet passage and both the first fuel pump and the second fuel pump communicate the corresponding one of the first fuel flow and the second fuel flow to a common outlet passage.
13 . The gas turbine engine as recited in claim 12 , including a first control valve upstream of the secondary fuel pump and a second control valve downstream of the secondary fuel pump, the first control valve and the second control valve controlling communication of fuel to and from the secondary fuel pump.
14 . The gas turbine engine as recited in claim 12 , including a pump drive gearbox selectively coupled to drive the secondary fuel pump by a clutch means.
15 . The gas turbine engine as recited in claim 11 , including a first pressure relief valve for switching the primary fuel pump and the secondary fuel pump between a series arrangement where the first fuel flow is provided by both the primary and secondary fuel pumps and a parallel arrangement where the first fuel flow is provided by the primary fuel pump and the secondary fuel flow is provided by the secondary fuel pump.
16 . The gas turbine engine as recited in claim 15 , wherein the first pressure relief valve is disposed between an outlet of the primary fuel pump and an inlet of the secondary fuel pump, the first pressure relief valve opens to communicate fuel from the primary fuel pump to the secondary fuel pump to provide the first fuel flow in a first operating condition and the first pressure relief valve closes such that the secondary fuel pump provides the second fuel flow in parallel with the first fuel flow provided by the primary mechanical fuel pump to a common fuel passage in a second operating condition.
17 . A method of supplying fuel to a combustor of a gas turbine engine comprising:
operating a primary fuel pump to provide a first fuel flow;
operating a secondary fuel pump to provide a second fuel flow, wherein operating the primary fuel pump and the secondary fuel pump comprises driving the primary fuel pump and the secondary fuel pump with an output from an accessory gearbox; and
communicating the first fuel flow to a combustor of the gas turbine engine in a first operating condition and communicating the first fuel flow and the second fuel flow to the combustor in a second operating condition.
18 . The method as recited in claim 17 , wherein communicating the first fuel flow to the combustor comprises directing fuel from an outlet of the primary fuel pump to an inlet of the secondary fuel pump in the first operating condition and communicating both the first fuel flow and the second fuel flow comprises blocking fuel flow from the outlet of the primary fuel pump to the inlet of the secondary fuel pump, communicating fuel from a fuel source to the inlet of the secondary fuel pump and routing both the first fuel flow from the primary pump and the secondary fuel flow from the secondary pump to a common fuel outlet passage.
19 . The method as recited in claim 17 , wherein communicating the first fuel flow to the combustor comprises flowing fuel from primary fuel pump to a common fuel outlet passage and blocking flow from the secondary fuel pump during the first engine operating condition and communicating the first fuel flow and the second fuel flow to the combustor in the second operating condition comprises communicating both the first fuel flow from the primary fuel pump and the second fuel flow from the secondary fuel pump to the common fuel outlet passage.