Variable volume combustor with an air bypass system
The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles.
1. A combustor for use with a flow of fuel and a flow of air in a gas turbine engine, comprising:
a plurality of micro-mixer fuel nozzles, wherein the plurality of micro-mixer fuel nozzles is positioned within a cap assembly, wherein the assembly is positioned within a liner;
a seal positioned between the cap assembly and the liner;
an air bypass system positioned about the liner, wherein the air bypass system comprises:
a plurality of air bypass holes through the liner,
an open position when the cap assembly is advanced in a downstream direction such that the seal is maneuvered downstream of the plurality of air bypass holes to prevent the flow of air therethrough, and
a closed position when the cap assembly is retracted in an upstream direction such that the seal is maneuvered upstream of the plurality of air bypass holes to enable a bypass portion of the flow of air to bypass the plurality of micro-mixer fuel nozzles.
2. The combustor of claim 1 , wherein the plurality of micro-mixer fuel nozzles comprises a plurality of micro-mixer fuel tubes and a fuel plate.
3. The combustor of claim 1 , wherein the plurality of air bypass holes is configured in a row.
4. The combustor of claim 1 , wherein the plurality of air bypass holes is configured in a plurality of rows.
5. The combustor of claim 1 , wherein the seal is positioned about an aft end of the cap assembly.
6. The combustor of claim 1 , wherein the open position comprises the cap assembly in a full aft position.
7. The combustor of claim 1 , wherein the air bypass system comprises a partially opened position with the seal partially upstream of the air bypass system.
8. The combustor of claim 1 , wherein the seal comprises a hula seal.
9. The combustor of claim 1 , further comprising a linear actuator to maneuver the plurality of micro-mixer fuel nozzles within the liner.
10. A method of turning down a combustor for use with a flow of fuel and a flow of air in a gas turbine engine, comprising:
positioning a plurality of micro-mixer fuel nozzles within a liner;
positioning a plurality of air bypass holes through the liner;
maneuvering a seal positioned about the plurality of micro-mixer fuel nozzles to open the air bypass holes in the liner;
flowing a bypass portion of the flow of air away from the plurality of micro-mixer fuel nozzles; and
reducing the flow of fuel to the plurality of micro-mixer fuel nozzles.