Fuse for flame holding abatement in premixer of combustion chamber of gas turbine and associated method
First Claim
1. A fuel nozzle assembly for a combustor of a gas turbine comprising:
- a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front is proximate to a combustion section of the combustor;
an outer casing around the inner tube and the outer casing includes a weakened region, wherein an air passage is defined between the outer casing and the inner tube;
an expandable fuel conduit arranged in the air passage and radially outward of the inner tube, an expandable fuel conduit having an outlet which is both proximate to the front of the nozzle body and adjacent the weakened region, wherein fuel flows through an expandable fuel conduit only after a flashback condition occurs in the combustor and opens the weakened region, anda premix fuel passage and port discharging fuel to a premix section of the combustor, wherein an expandable fuel conduit has an inlet open to the premix fuel passage and the port is radially outward of the outer casing.
1 Assignment
0 Petitions
Accused Products
Abstract
A fuel nozzle assembly for a combustor of a gas turbine including: a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front proximate to a combustion section of the combustor; an outer casing around the inner tube, wherein an air passage is defined between the outer casing and the inner tube; a gas conduit arranged in the air passage and having an outlet proximate to the front of the nozzle body, wherein fuel starts flowing through the expandable conduit only after a flashback condition occurs in the combustor, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein the gas conduit has an inlet open to the premix fuel passage.
37 Citations
20 Claims
-
1. A fuel nozzle assembly for a combustor of a gas turbine comprising:
-
a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body, wherein the front is proximate to a combustion section of the combustor; an outer casing around the inner tube and the outer casing includes a weakened region, wherein an air passage is defined between the outer casing and the inner tube; an expandable fuel conduit arranged in the air passage and radially outward of the inner tube, an expandable fuel conduit having an outlet which is both proximate to the front of the nozzle body and adjacent the weakened region, wherein fuel flows through an expandable fuel conduit only after a flashback condition occurs in the combustor and opens the weakened region, and a premix fuel passage and port discharging fuel to a premix section of the combustor, wherein an expandable fuel conduit has an inlet open to the premix fuel passage and the port is radially outward of the outer casing. - View Dependent Claims (2, 3, 4, 5, 6)
-
-
7. A fuel nozzle assembly for a combustor of a gas turbine comprising:
-
a nozzle body having a front and an inner tube defining a fuel passage extending through the nozzle body; an outer tube around the inner tube and defining an air passage between the outer tube and the inner tube; a weakened region of the outer tube which burns through in event of a flashback thereby causing premix fuel to flow through the burned weakened region of the outer tube; an expandable conduit arranged in the air passage and radially outward of the inner tube, and the expandable conduit having an outlet adjacent the weakened region, wherein fuel flows through the expandable conduit when the weakened region of the outer tube burns through and the fuel flows from the conduit, through the weakened region and towards the front of the nozzle body, and a collar attached to the nozzle body, the collar including a premix fuel passage, wherein the expandable conduit has an inlet open to the premix fuel passage and the premix fuel passage extends to a port which discharges the fuel wherein the port is radially outward of the outer tube. - View Dependent Claims (8, 9, 10, 11, 12, 13, 14)
-
-
15. A method for quenching a flashback condition in a combustor of a gas turbine, the method comprising:
-
injecting fuel and compressed air from a fuel injector assembly to a premix chamber of the combustor, wherein the injected fuel and compressor air does not normally combust in the premix chamber; combusting the fuel and compressed in a combustion chamber downstream of the premix chamber in the combustor; providing air to the combustion chamber from a front of the injector assembly through an air passage extending through a nozzle body of the fuel injector; injecting fuel to the combustion chamber from a fuel passage having an outlet at the front of the injector assembly; in response to a flashback condition, opening an outlet of a conduit adjacent the fuel injector assembly and radially inward of the premix chamber, wherein the outlet is proximate the front of the injector assembly, wherein the conduit extends through and is inside of the air passage; diverting fuel from the premix chamber to the conduit by the opening of the outlet, and quenching flames of the flashback condition by the diversion of fuel. - View Dependent Claims (16, 17, 18, 19, 20)
-
Specification