A dual function rapid shutdown and ecology system for fuel delivery systems for engines, specially aircraft gas turbine engines, is disclosed. The dual function is accomplished in a single module operated by a single electro-magnetic solenoid valve commanded by the engine electronic control unit. Up
A dual function rapid shutdown and ecology system for fuel delivery systems for engines, specially aircraft gas turbine engines, is disclosed. The dual function is accomplished in a single module operated by a single electro-magnetic solenoid valve commanded by the engine electronic control unit. Upon actuation of the solenoid valve, a large spring loaded piston strokes to the extreme of its travel creating a cavity having a volume sufficient to accommodate all fuel leftover in the fuel manifold and distribution system at shutdown, thus preventing atmospheric pollution or engine damage upon subsequent operation. Simultaneous with actuation of the solenoid valve, fuel pressure differentials cause a small piston to stroke to the extreme of its travel opening fuel passageways and causing all the fuel being delivered to the engine combustion chamber to be bypassed back to pump inlet, thus effectively accomplishing the rapid shutdown function. An alternate embodiment allows for use of the dual function system on engines employing low pressure differentials along the various stages of the fuel control system manifold or where the ecology function is not required.
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1. A gas turbine engine fuel control rapid shut down and ecology system comprising:a first cylindrically shaped valve body, internally bored to define a valve chamber having upper and lower ends;a first cylindrical piston member placed internal to the valve chamber and movable therein along the long
1. A gas turbine engine fuel control rapid shut down and ecology system comprising:a first cylindrically shaped valve body, internally bored to define a valve chamber having upper and lower ends;a first cylindrical piston member placed internal to the valve chamber and movable therein along the longitudinal axis thereof;a bored cavity at the upper end and along the longitudinal axis of the first cylindrical piston member;a bored cavity at the lower end and along the longitudinal axis of the first cylindrical piston member, said bored cavity having a diameter larger than the bored cavity on the opposite end of the first cylindrical piston member;a spirally wound spring positioned internal to the bored cavity at the upper end of the first cylindrical piston member, one end bearing on the base of the bored cavity and the other end bearing on the upper internal end of the valve chamber;a fuel passageway leading from an annular cavity along the outer surface of the first cylindrical piston member to a spring loaded accumulator valve;a fuel passageway leading from the spring loaded accumulator valve to a witness drain;a second cylindrically shaped valve body, internally bored to define a second valve chamber having upper and lower ends;a second cylindrical piston member placed internal to the second valve chamber and movable therein along the longitudinal axis thereof;a fluid passageway connecting the upper end of the first valve chamber to a gas turbine engine fuel manifold immediately upstream of combustion chamber atomizers;a fluid passageway connecting a gas turbine engine fuel manifold immediately downstream of a high pressure fuel pump to the lower ends of both first and second valve chambers;a fluid passageway, including an electrically actuated solenoid valve, connecting the lower end of the first valve chamber and upper end of the second valve chamber to a gas turbine engine fuel manifold immediately downstream of a low pressure fuel pump;a fluid passageway connecting the upper end of the second valve chamber to a gas turbine engine fuel manifold upstream of a valve controlling the fuel pressure delivered to combustion chamber atomizers;whereby when said gas turbine engine is turned off, said solenoid valve will simultaneously open causing fuel pressure differentials to drive both first and second cylindrical piston members downward thus rapidly terminating further fuel flow to the combustion chamber atomizers, and providing a temporary cavity to accommodate all fuel leftover in the manifold and distribution system at shutdown as well as all fuel contained in the annular cavity along the outer surface of the first cylindrical piston member. 2. The gas turbine engine fuel control rapid shut down and ecology system of claim 1, wherein o-ring seals are provided on the first cylindrical piston member at the upper transverse surface and at the bottom peripheral surface. 3. The gas turbine engine fuel control rapid shut down and ecology system of claim 1, wherein an o-ring seal is provided on the lower peripheral surface of the second cylindrical piston. 4. The gas turbine engine fuel control rapid shut down and ecology system of claim 1, wherein the diameter of the first cylindrical piston member at the lower end is about 2.5 inches. 5. The gas turbine engine fuel control rapid shut down and ecology system of claim 4, wherein the diameter of the of the first cylindrical piston member at the location of the o-ring seals on the upper transverse surface is about 2 inches. 6. The gas turbine engine fuel control rapid shut down and ecology system of claim 1, wherein the stroke of the first cylindrical piston member within the valve chamber is about 1.5 inches. 7. The gas turbine engine fuel control rapid shut down and ecology system of claim 1, wherein an orifice is provided on the fluid passageway connecting a gas turbine engine fuel manifold immediately downstream of a high pressure fuel pump to the lower end of the valve chamber. 8. The gas turbine engine fuel control rapid shut down and ecology system of claim 1, wherein the depth and diameter of the bored cavity at the upper end and along the longitudinal axis of the first cylindrical piston member is sized to provide a scavenge volume sufficient to accommodate all fuel left over in the manifold and distribution system at shutdown. 9. The gas turbine engine fuel control rapid shut down and ecology system of claim 1, wherein a fuel passageway leading from an annular cavity along the outer surface of the first cylindrical piston member is connected to a spring loaded check valve and thereafter to a fluid passageway downstream of the low pressure pump, thereby allowing for remote location of the first cylindrical piston member and valve chamber. 10. A gas turbine engine fuel control rapid shut down and ecology system comprising:a first valve body internally bored to define a first valve chamber having upper and lower ends;a first piston member placed internal to the valve chamber and movable therein along a longitudinal axis thereof;an upper bored cavity at the upper end and along a longitudinal axis of the first piston member;a lower bored cavity at a lower end of and along the longitudinal axis of the first piston member, said lower bored cavity having a diameter larger than the upper bored cavity on the upper end of the first piston member;a spring positioned internal to the upper bored cavity, one end bearing on a base of the upper bored cavity and the other end bearing on an upper internal end of the valve chamber;a second valve body internally bored to define a second valve chamber having upper and lower ends;a second piston member placed internal to the second valve chamber and movable therein along a longitudinal axis thereof;a first fluid passageway connecting the upper end of the first valve chamber to a gas turbine engine fuel manifold immediately upstream of combustion chamber atomizers;a second fluid passageway connecting a gas turbine engine fuel manifold immediately downstream of a high pressure fuel pump to the lower ends of both first and second valve chambers;a third fluid passageway, including a passageway valve, connecting the lower ends of the first and second valve chambers and the upper end of the second valve chamber to the gas turbine engine fuel manifold immediately downstream of a low pressure fuel pump;a fourth fluid passageway connecting the upper end of the second valve chamber to the gas turbine engine fuel manifold upstream of a fuel pressure controlling valve controlling a fuel pressure delivered to combustion chamber atomizers;wherein, when the gas turbine engine is turned off, said passageway valve will open causing fuel pressure differentials to drive both first and second piston members from an operating position to a shut-down position, thus terminating further fuel flow to the combustion chamber atomizers, and providing a temporary cavity to accommodate the fuel leftover in the gas turbine engine manifold and distribution system at shutdown. 11. The gas turbine engine fuel control rapid shut down and ecology system of claim 10, wherein the passageway valve is an electrically actuated solenoid valve, the electrically actuated solenoid valve being actuated by a manual command or automatically through one of an overspeed, overtemperature or other fault detection system. 12. The gas turbine engine fuel control rapid shut down and ecology system of claim 10, wherein:the first valve body and the second valve body are cylindrically shaped; andthe first piston member and the second piston member are cylindrically shaped. 13. The gas turbine engine fuel control rapid shut down and ecology system of claim 10, wherein the spring is a spirally wound spring providing a resilient force on the upper end of the first valve body. 14. The gas turbine engine fuel control rapid shut down and ecology system of claim 10 further comprising:a fifth fuel passageway leading from an annular cavity along an outer surface of the first cylindrical piston member to a spring loaded accumulator valve; anda sixth fuel passageway leading from the spring loaded accumulator valve to a witness drain. 15. The gas turbine engine fuel control rapid shut down and ecology system of claim 10, further comprising:a fifth fuel passageway leading from an annular cavity along an outer surface of the first piston member to a spring loaded check valve; anda sixth fuel passageway leading from said spring loaded check valve to a gas turbine engine fuel manifold immediately downstream of a low pressure fuel pump. 16. A gas turbine engine, having a gas turbine engine fuel manifold with a fuel shut down system and an ecology system, comprising:a first valve body internally bored to define a valve chamber having upper and lower ends;a first piston member placed internal to the valve chamber and movable therein along a longitudinal axis thereof;an upper bored cavity at an upper end of and along a longitudinal axis of the first piston member;a lower bored cavity at a lower end of and along the longitudinal axis of the first piston member, said lower bored cavity having a diameter larger than the upper bored cavity on an opposite end of the first piston member;a spring positioned internal to the upper bored cavity, one end bearing on a base of the upper bored cavity and the other end bearing on an upper internal end of the valve chamber;a second valve body internally bored to define a second valve chamber having upper and lower ends;a second piston member placed internal to the second valve chamber and movable therein along a longitudinal axis thereof;a first fluid passageway connecting the upper end of the first valve chamber to a gas turbine engine fuel manifold immediately upstream of combustion chamber atomizers;a second fluid passageway connecting the gas turbine engine fuel manifold immediately downstream of a high pressure fuel pump to the lower ends of both first and second valve chambers;a third fluid passageway, including a passageway valve, connecting the lower end of the first and second valve chambers and the upper end of the second valve chamber to the gas turbine engine fuel manifold immediately downstream of a low pressure fuel pump;a fourth fluid passageway connecting the upper end of the second valve chamber to the gas turbine engine fuel manifold upstream of a pressure rising valve controlling the fuel pressure delivered to combustion chamber atomizers;wherein, when the gas turbine engine is turned off, said passageway valve will simultaneously open causing fuel pressure differentials to drive both first and second cylindrical piston members from an operating position to a shut down position, thus terminating further fuel flow to the combustion chamber atomizers, and providing a temporary cavity to accommodate the fuel leftover in the gas turbine engine fuel manifold system at shutdown. 17. The gas turbine engine of claim 16, further comprising:a fifth fuel passageway leading from an annular cavity along an outer surface of the first cylindrical piston member to a spring loaded accumulator valve; anda sixth fuel passageway leading from the spring loaded accumulator valve to a witness drain. 18. The gas turbine engine of claim 16, further comprising:a fifth fuel passageway leading from an annular cavity along an outer surface of the first cylindrical piston member to a spring loaded check valve; anda sixth fuel passageway leading from said spring loaded check valve to the gas turbine engine fuel manifold immediately downstream of a low pressure fuel pump. 19. A method for providing a gas turbine engine having a fuel control rapid shut down and ecology system comprising:providing a first cylindrically shaped valve body internally bored to define a valve chamber having upper and lower ends;placing a first cylindrical piston member internal to the valve chamber and movable therein along a longitudinal axis thereof;boring an upper cavity at an upper end of and along a longitudinal axis of the first cylindrical piston member;boring a lower cavity at a lower end of and along the longitudinal axis of the first cylindrical piston member, said lower cavity having a diameter larger than the upper cavity;positioning a spirally wound spring internal to the upper cavity, one end bearing on a base of the upper cavity and another end bearing on an upper internal end of the valve chamber;providing a first fuel passageway leading from an annular cavity along an outer surface of the first cylindrical piston member to a spring loaded accumulator valve;providing a second fuel passageway leading from the spring loaded accumulator valve to a witness drain;providing a second cylindrically shaped valve body internally bored to define a second valve chamber having upper and lower ends;placing a second cylindrical piston member internal to the second valve chamber and movable therein along a longitudinal axis thereof;providing a third fluid passageway connecting the upper end of the first valve chamber to a gas turbine engine fuel manifold immediately upstream of combustion chamber atomizers;providing a fourth fluid passageway connecting a gas turbine engine fuel manifold immediately downstream of a high pressure fuel pump to the lower ends of both first and second valve chambers;providing a fifth fluid passageway, including an electrically actuated solenoid valve, connecting the lower end of the first valve chamber and upper end of the second valve chamber to the gas turbine engine fuel manifold immediately downstream of a low pressure fuel pump;providing a sixth fluid passageway connecting the upper end of the second valve chamber to the gas turbine engine fuel manifold upstream of a valve controlling the fuel pressure delivered to combustion chamber atomizers;wherein when the gas turbine engine is turned off, said solenoid valve will simultaneously open causing fuel pressure differentials to drive both first and second cylindrical piston members from an operating position to a shut-down position, thus terminating further fuel flow to the combustion chamber atomizers, and providing a temporary cavity to accommodate the fuel leftover in the gas turbine engine fuel manifold at shutdown as well as all fuel contained in the annular cavity along the outer surface of the first cylindrical piston member.
Nenmeni, Vijay Raghavendran; Rozdolski, Michael John; Chillar, Rahul Jaikaran, System and method for transitioning between fuel supplies for a combustion system.
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