Controlling soot
A gas turbine engine comprising a variable geometry combustor having pilot fuel injectors and main fuel injectors; a fuel metering system configured to control fuel flow to the pilot fuel injectors and the main fuel injectors; a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary the airflow through the pilot fuel injectors and/or the main fuel injectors; a control system configured to control the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow through the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced by combustion.
1. A gas turbine engine comprising:
a variable geometry combustor having pilot fuel injectors and main fuel injectors;
a fuel meter configured to control fuel flow to the pilot fuel injectors and the main fuel injectors;
a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary the airflow through the pilot fuel injectors and/or the main fuel injectors; and
a control system configured to control the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow through the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced by combustion,
wherein the control system is configured to respond to a decrease in the target index of soot emissions by controlling the variable geometry airflow arrangement to decrease the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors.
2. The gas turbine engine of claim 1 , in which the control system is configured to derive the target index of soot emissions in dependence upon an atmospheric condition which is causative of a condensation trail.
3. The gas turbine engine of claim 2 , in which the control system is configured to derive the target index of soot emissions by:
identifying a condition to the effect that an optical depth of a condensation trail produced by the engine should be either reduced or increased;
in response to identifying that the optical depth should be reduced, updating the target index of soot emissions so as to reduce ice particle formation; and
in response to identifying that the optical depth should be increased, updating the target index of soot emissions so as to increase ice particle formation.
4. The gas turbine engine of claim 1 , in which the control system is configured to respond to an increase in the target index of soot emissions by controlling the variable geometry airflow arrangement to increase the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors.
5. The gas turbine engine of claim 1 , in which the control system is further configured to control the fuel meter to effect changes in the fuel flow to the pilot fuel injectors and the main fuel injectors in dependence upon the target index of soot emissions.
6. The gas turbine engine of claim 5 , in which the control system is configured to respond to an increase in the target index of soot emissions during operation of both the pilot fuel injectors and the main fuel injectors by:
controlling the variable geometry airflow arrangement to increase the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors; and
controlling the fuel meter to increase fuel flow to the pilot fuel injectors relative to the main fuel injectors.
7. The gas turbine engine of claim 5 , in which the control system is configured to respond to the decrease in the target index of soot emissions during operation of both the pilot fuel injectors and the main fuel injectors by:
controlling the variable geometry airflow arrangement to decrease the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors; and
controlling the fuel meter to decrease fuel flow to the pilot fuel injectors relative to the main fuel injectors.
8. The gas turbine engine of claim 5 , in which the control system is configured to respond to the decrease in the target index of soot emissions during operation of only the pilot fuel injectors by:
controlling the variable geometry airflow arrangement to decrease the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors; and
controlling the fuel meter to decrease fuel flow from the pilot fuel injectors and introduce fuel flow to the main fuel injectors.
9. The gas turbine engine of claim 1 , in which the pilot fuel injectors are variable geometry pilot fuel injectors and comprise the variable geometry airflow arrangement, whereby variation of the airflow through the pilot fuel injectors varies the airflow through the main fuel injectors.
10. The gas turbine engine of claim 1 , in which the main fuel injectors are variable geometry main fuel injectors and comprise the variable geometry airflow arrangement, whereby variation of the airflow through the main fuel injectors varies the airflow through the pilot fuel injectors.
11. The gas turbine engine of claim 1 , in which the pilot fuel injectors are variable geometry pilot fuel injectors and the main fuel injectors are variable geometry main fuel injectors, whereby the pilot fuel injectors and the main fuel injectors comprise the variable geometry airflow arrangement.
12. The gas turbine engine of claim 1 , comprising a plurality of duplex fuel nozzles, each one of which comprises one of the pilot fuel injectors and one of the main fuel injectors.
13. The gas turbine engine of claim 1 , in which the combustor is a parallel staged combustor in which the pilot fuel injectors are configured to inject fuel into a first combustion zone and the main fuel injectors are configured to inject fuel into a second combustion zone radially offset from the first combustion zone, or the combustor is a series staged combustor in which the pilot fuel injectors are configured to inject fuel into a first combustion zone and the main fuel injectors are configured to inject fuel into a second combustion zone axially offset from the first combustion zone.
14. A method of controlling an index of soot emissions of a gas turbine combustor, comprising:
providing pilot fuel injectors for rich combustion and main fuel injectors for lean combustion in said combustor;
providing a variable geometry airflow arrangement for varying the airflow through the pilot fuel injectors and/or main fuel injectors;
controlling the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow to the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced in the combustor; and
responding to a decrease in the target index of soot emissions by decreasing the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors.
15. The method of claim 14 , in which the target index of soot emissions is derived in dependence upon an atmospheric condition.
16. The method of claim 15 , in which the target index of soot emissions is derived by:
identifying a condition to the effect that an optical depth of a condensation trail produced by the engine should be either reduced or increased;
in response to identifying that the optical depth should be reduced, updating the target index of soot emissions so as to reduce ice particle formation; and
in response to identifying that the optical depth should be increased, updating the target index of soot emissions so as to increase ice particle formation.
17. The method of claim 14 , further comprising responding to an increase in the target index of soot emissions by increasing the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors.
18. The method of claim 14 , further comprising controlling fuel flow to the pilot fuel injectors and the main fuel injectors in dependence upon the target index of soot emissions.
19. A gas turbine engine comprising:
a variable geometry combustor having pilot fuel injectors and main fuel injectors;
a fuel meter configured to control fuel flow to the pilot fuel injectors and the main fuel injectors;
a variable geometry airflow arrangement for the variable geometry combustor, which is configured to vary the airflow through the pilot fuel injectors and/or the main fuel injectors; and
a control system configured to control the variable geometry airflow arrangement in dependence upon airflow delivered to the combustor, the fuel flow to the pilot fuel injectors and the main fuel injectors, and a target index of soot emissions, thereby controlling airflow through the pilot fuel injectors and/or the main fuel injectors and hence the quantity of soot produced by combustion,
wherein the control system is configured to respond to an increase in the target index of soot emissions by controlling the variable geometry airflow arrangement to increase the airflow through the main fuel injectors relative to the airflow through the pilot fuel injectors.