초록 ▼

A gas turbine engine for an aircraft. The gas turbine comprises a combustor, a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor, a water injection system connected with a source of water and which is configured to inject water into the combustor,

A gas turbine engine for an aircraft. The gas turbine comprises a combustor, a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor, a water injection system connected with a source of water and which is configured to inject water into the combustor, and a control system. The control system is configured to identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein.

대표청구항 ▼

1. A method comprising operating an aircraft gas turbine engine, the method comprising: providing a source of fuel and a source of water;identifying an atmospheric condition;determining a water-fuel ratio for injection into a combustor of the gas turbine engine in response to the atmospheric conditi

1. A method comprising operating an aircraft gas turbine engine, the method comprising: providing a source of fuel and a source of water;identifying an atmospheric condition;determining a water-fuel ratio for injection into a combustor of the gas turbine engine in response to the atmospheric condition;injecting water and fuel according to said water-fuel ratio into the combustor to control soot emissions caused by combustion of fuel therein. 2. The method of claim 1, in which the determined water-fuel ratio reduces soot emissions compared to a dry mode of operation. 3. The method of claim 1, in which the atmospheric condition is an atmospheric condition causative of a condensation trail, optionally a persistent condensation trail. 4. The method of claim 1, in which the water-fuel ratio is determined on the basis of the time-integrated effect of a persistent condensation contrail over its lifespan given a current atmospheric condition and a predicted future atmospheric condition. 5. The method of claim 1, further comprising detecting the atmospheric condition using a direct measurement device. 6. The method of claim 1, further comprising inferring the atmospheric condition. 7. The method of claim 1, in which the water is injected upstream of a primary zone of the combustor. 8. The method of claim 7, in which the fuel is injected by one or more fuel injectors, each one of which has an associated water injector configured to co-inject water with fuel. 9. The method of claim 1, wherein the determining step comprises: identifying a condition to the effect that an optical depth of a condensation trail produced by the engine should be reduced;evaluating a water-fuel ratio that varies soot production to reduce ice particle formation. 10. The method of claim 1, wherein the determining step comprises: identifying a condition to the effect that an optical depth of a condensation trail produced by the engine should be increased;evaluating a water-fuel ratio that varies soot production to increase ice particle formation. 11. A gas turbine engine for an aircraft, comprising: a combustor;a fuel injection system connected with a source of fuel and configured to inject fuel into the combustor;a water injection system connected with a source of water and which is configured to inject water into the combustor;a control system configured to: identify an atmospheric condition; determine a water-fuel ratio for injection into the combustor of the gas turbine engine in response to the atmospheric condition; and control injection of fuel and water by the fuel injection system and the water injection system according to said water-fuel ratio to control an soot emissions caused by combustion of fuel therein. 12. The gas turbine engine of claim 11, in which the control system is configured to determine a water-fuel ratio that reduces soot emissions compared to a dry mode of operation. 13. The gas turbine engine of claim 11, in which the atmospheric condition is an atmospheric condition causative of a condensation trail, optionally a persistent condensation trail. 14. The gas turbine engine of claim 11, in which control system is configured to determine the water-fuel ratio on the basis of the time-integrated effect of a persistent condensation contrail over its lifespan given a current atmospheric condition and a predicted future atmospheric condition. 15. The gas turbine engine of claim 11, further comprising a direct measurement device for detecting the atmospheric condition. 16. The gas turbine engine of claim 11, in which the atmospheric condition is inferred. 17. The gas turbine engine of claim 11, in which the water injection system comprises one or more water injectors located upstream of a primary zone of the combustor. 18. The gas turbine engine of claim 17, in which the fuel injection system comprises one or more fuel injectors, each one of which has an associated water injector configured to co-inject water with fuel injected by the fuel injector. 19. The gas turbine engine of claim 11, in which the control system is configured to determine the water-fuel ratio by: identifying a condition to the effect that an optical depth of a condensation trail produced by the engine should be reduced;evaluating a water-fuel ratio that varies soot production to reduce ice particle formation. 20. The gas turbine engine of claim 11, in which the control system is configured to determine the water-fuel ratio by: identifying a condition to the effect that an optical depth of a condensation trail produced by the engine should be increased;evaluating a water-fuel ratio that varies soot production to increase ice particle formation.