Variable volume combustor with an air bypass system

Patent metadata

Field	Value
Publication number	US-9562687-B2
Application number	US-201313760101-A
Country	US
Kind code	B2
Filing date	Feb 6, 2013
Priority date	Feb 6, 2013
Publication date	Feb 7, 2017
Grant date	Feb 7, 2017

Abstract

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.

First claim

We claim:

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.

Assignees

• Gen Electric

Inventors

• Johnson Thomas Edward
• Ziminsky Willy Steve
• Ostebee Heath Michael
• Keener Christopher Paul

Classifications

• F23R3/045

  using pipes · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/04 Primary

  Air inlet arrangements · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic