Method for regulating fuel flow in a gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorHing C. Chan
Life of this patent
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Abstract
Fuel flow to the combustor of a gas turbine engine is regulated by controlling the amount of fuel delivered to the primary and secondary fuel orifices of a hybrid fuel nozzle. A one-way valve extending between primary and secondary fuel manifolds is controlled by an electronic sensor that acts upon signals received from sensors at station 4.5 of the engine, and by sensors that measure engine speed. By opening and closing the valve based upon T.sub.4.5 and N.sub.2 speed, optimum engine operating conditions are achieved.
Claims9
A method for regulating fuel flow to the combustor of a gas turbine engine, wherein the fuel flows through a hybrid fuel nozzle into the combustor and the nozzle has a primary and secondary orifice, comprises:
- a first fuel flow regime during which fuel flows to the primary orifice at a pressure between about 250 and 300 psi and to the secondary orifice at a pressure between about 1 and 5 psi;
- a second fuel flow regime during which fuel flows to both the primary and secondary orifices at a pressure between about 5 and 30 psi;
- and a third fuel flow regime during which fuel flows to the primary orifice at a pressure between about 250 and 300 psi and to the secondary orifice at a pressure consistent with engine operation in excess of 50% N.sub.2 speed, wherein the first flow regime is operational between the initiation of engine start up and the attainment of stable fuel combustion in the combustor;
- the second fuel flow regime is operation between the attainment of stable combustion conditions and approximately 50% N.sub.2 speed;
- and the third flow regime is operational thereafter.
A method for regulating fuel flow to the combustor of a gas turbine engine, wherein fuel flows from a fuel pump through a hybrid fuel nozzle into the combustor, the nozzle having a primary orifice and a secondary orifice, and fuel flows from the pump to the primary orifice through a primary fuel manifold, and from the pump to the secondary orifice through a secondary manifold, the method comprising the steps of:
- flowing fuel to the combustor during a first fuel flow regime wherein fuel flows from the pump through the primary manifold and to the primary orifice at a pressure between about 250 and 300 psi, and from the pump through the secondary manifold to the secondary orifice at a pressure between about 1 and 5 psi;
- measuring the temperature at station 4.5 of the engine, and terminating the flow of 250 to 300 psi fuel from the pump through the primary manifold and to the primary orifice when such temperature is between about 275.degree. and 325.degree. C.;
- flowing fuel to the combustor during a second fuel flow regime wherein fuel flows from the pump to both the primary and secondary orifices at a pressure between about 5 and 30 psi, wherein the second fuel flow regime includes the step of flowing fuel from the pump through the secondary fuel manifold and then to the primary fuel manifold through a one-way valve extending therebetween, such that no fuel flows from the pump through the primary fuel manifold upstream of the valve;
- and a third fuel flow regime during which fuel flows from the pump through the primary manifold and to the primary orifice at a pressure between about 250 and 300 psi, and from the pump through the secondary manifold and to the secondary orifice at a pressure consistent with engine operation in excess of 50% N.sub.2 speed, wherein the third flow regime is operational after the second flow regime and until the engine speed is reduced approximately to ground idle speed.
Dependencies are inferred from the claim text.