초록 ▼

In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting

In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting a flame holding condition about a fuel injector. The method may include the steps of: detecting an upstream pressure upstream of the secondary fuel injector; detecting a downstream pressure downstream of the secondary fuel injector; determining a measured pressure difference between the upstream pressure and the downstream pressure; and comparing the measured pressure difference to an expected pressure difference.

대표청구항 ▼

1. In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector upstream of the fuel nozzle, a system for detecting a flame about the secondary fuel injector, the system comprising: a fir

1. In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector upstream of the fuel nozzle, a system for detecting a flame about the secondary fuel injector, the system comprising: a first pressure sensor that detects an upstream pressure upstream of the secondary fuel injector;a second pressure sensor that detects a downstream pressure downstream of the secondary fuel injector;means for determining a measured pressure difference between the upstream pressure and the downstream pressure; andmeans for comparing the measured pressure difference to an expected pressure difference;wherein the combustor comprises a combustion chamber, and the fuel nozzle comprises a position directly upstream of the combustion chamber;wherein the expected pressure difference comprises a pressure difference that is expected when there is no flame about the secondary fuel injector;wherein the means for determining the measured pressure difference comprises a transducer operably connected to detect the pressure difference between the upstream pressure and the downstream pressure;wherein the means for comparing the measured pressure difference to an expected pressure difference comprises a computer-implemented controller;wherein the computer-implemented controller is configured to determine the expected pressure difference via at least one of a) consulting a stored value; and b) calculating by applying an algorithm to parameters of the gas turbine engine and measured operating conditions; andwherein the computer-implemented controller is configured to indicate that there is a flame about the secondary fuel injector in response the difference between the expected pressure difference and the measured pressure difference exceeding a predetermined threshold. 2. The system of claim 1, wherein the secondary fuel injector comprises a fuel injector that is configured to inject fuel into a flow annulus of the combustor. 3. The system of claim 2, wherein: the combustor includes a combustor casing, and a cap assembly;the cap assembly is defined, at least in part, at a forward end by an end cover and at an aft end by the fuel nozzle;wherein a fuel line extends through the end cover and the interior of the cap assembly to engage the fuel nozzle; andthe combustor casing is positioned about the cap assembly such that a combustor casing annulus is formed therebetween. 4. The system of claim 3, wherein the secondary fuel injector comprises a fuel injector that is configured to inject fuel into the combustor casing annulus. 5. The system of claim 4, wherein, at the aft end, the cap assembly engages a liner that surrounds the combustion chamber; wherein, toward the forward end, the cap assembly comprises an inlet that fluidly connects the combustor casing annulus to the interior of the cap assembly; and wherein the secondary fuel injector comprises a fuel injector that is configured to inject fuel into the combustor casing annulus at an axial position that is between: a) the axial position at which the cap assembly engages the liner and b) the axial position of the inlet. 6. The system of claim 4, the first pressure sensor is positioned in the flow annulus of the combustor and upstream of the secondary fuel injector. 7. The system of claim 6, wherein the first pressure sensor comprises a position within the combustor casing annulus. 8. The system of claim 6, wherein the second pressure sensor comprises a position within the combustor casing annulus; further comprising means for calculating an amount by which the expected pressure difference exceeds the measured pressure difference, and means for determining whether the calculated amount by which the expected difference exceeds the measured pressure difference is greater than a predetermined threshold, wherein the predetermined threshold corresponds to a flame holding condition about the secondary fuel injector. 9. The system of claim 8, wherein the predetermined threshold comprises approximately 0.2%. 10. The system of claim 6, wherein the second pressure sensor comprises a position within the interior of the cap assembly and upstream of the fuel nozzle; further comprising means for calculating an amount by which the expected pressure difference exceeds the measured pressure difference, and means for determining whether the calculated amount by which the expected difference exceeds the measured pressure difference is greater than a predetermined threshold, wherein the predetermined threshold corresponds to a flame holding condition about the secondary fuel injector. 11. The system of claim 10, wherein the predetermined threshold comprises approximately 0.5%. 12. The system of claim 6, wherein the second pressure sensor comprises a position within the combustion chamber; further comprising means for calculating an amount by which the expected pressure difference exceeds the measured pressure difference, and means for determining whether the calculated amount by which the expected difference exceeds the measured pressure difference is greater than a predetermined threshold, wherein the predetermined threshold corresponds to a flame holding condition about the secondary fuel injector. 13. The system of claim 12, wherein the predetermined threshold comprises approximately 0.5%. 14. The system of claim 1, further comprising an integrated probe, the integrated probe extending through an air flow path of the combustor into the combustion chamber; wherein: the first pressure sensor is located on a portion of the integrated probe that is positioned in the air flow path; andthe second pressure sensor is located on a portion of the integrated probe that is positioned in the combustion chamber. 15. In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, wherein the combustor comprises a combustion chamber, and the fuel nozzle comprises a position directly upstream of the combustion chamber, a method for detecting a flame holding condition about a fuel injector, the method including the steps of: detecting an upstream pressure upstream of the secondary fuel injector;detecting a downstream pressure downstream of the secondary fuel injector;determining a measured pressure difference between the upstream pressure and the downstream pressure;comparing the measured pressure difference to an expected pressure difference;determining the expected pressure difference via at least one of a) consulting a stored value; and b) calculating by applying an algorithm to parameters of the gas turbine engine and measured operating conditions; andindicating that there is a flame about the secondary fuel injector in response the difference between the expected pressure difference and the measured pressure difference exceeding a predetermined threshold. 16. The method of claim 15, wherein: the combustor includes a combustor casing and a cap assembly;the cap assembly is defined, at least in part, at a forward end by an end cover and at an aft end by the fuel nozzle;wherein a fuel line extends through the end cover and the interior of the cap assembly to engage the fuel nozzle;the combustor casing is positioned about the cap assembly such that a combustor casing annulus is formed therebetween; andthe secondary fuel injector comprises a fuel injector that is configured to inject fuel into the combustor casing annulus. 17. The method of claim 15, further comprising the steps of: calculating an amount by which the expected pressure difference exceeds the measured pressure difference;determining whether the calculated amount by which the expected difference exceeds the measured pressure difference is greater than a predetermined threshold; andwherein the predetermined threshold corresponds to a flame holding condition about the secondary fuel injector. 18. The method of claim 15, wherein the downstream pressure comprises a first downstream pressure, and the detecting the first downstream pressure downstream of the secondary fuel injector comprises detecting a pressure at a position that is upstream of the fuel nozzle; further comprising the steps of: detecting a second downstream pressure downstream of the primary fuel injector;determining a measured pressure difference between the first downstream pressure and the second downstream pressure;comparing the measured pressure difference between the first downstream pressure and the second downstream pressure to an expected pressure difference;determining if a flame holding condition is about the primary fuel injector or the secondary fuel injector based upon the comparisons between the measured pressures and expected pressures between a) the first downstream pressure and the second downstream pressure and b) the first downstream pressure and the second downstream pressure.