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Title: Variable volume combustor with center hub fuel staging

Abstract

The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle.

Inventors:
; ; ;
Publication Date:
Research Org.:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1303583
Patent Number(s):
9,422,867
Application Number:
13/760,099
Assignee:
General Electric Company (Schenectady, NY) NETL
DOE Contract Number:
FC26-05NT42643
Resource Type:
Patent
Resource Relation:
Patent File Date: 2013 Feb 06
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Ostebee, Heath Michael, McConnaughhay, Johnie Franklin, Stewart, Jason Thurman, and Keener, Christopher Paul. Variable volume combustor with center hub fuel staging. United States: N. p., 2016. Web.
Ostebee, Heath Michael, McConnaughhay, Johnie Franklin, Stewart, Jason Thurman, & Keener, Christopher Paul. Variable volume combustor with center hub fuel staging. United States.
Ostebee, Heath Michael, McConnaughhay, Johnie Franklin, Stewart, Jason Thurman, and Keener, Christopher Paul. 2016. "Variable volume combustor with center hub fuel staging". United States. doi:. https://www.osti.gov/servlets/purl/1303583.
@article{osti_1303583,
title = {Variable volume combustor with center hub fuel staging},
author = {Ostebee, Heath Michael and McConnaughhay, Johnie Franklin and Stewart, Jason Thurman and Keener, Christopher Paul},
abstractNote = {The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = 2016,
month = 8
}

Patent:

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  • The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.
  • The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system.
  • The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts.
  • A port (60) for axially staging fuel and air into a combustion gas flow path 28 of a turbine combustor (10A). A port enclosure (63) forms an air path through a combustor wall (30). Fuel injectors (64) in the enclosure provide convergent fuel streams (72) that oppose each other, thus converting velocity pressure to static pressure. This forms a flow stagnation zone (74) that acts as a valve on airflow (40, 41) through the port, in which the air outflow (41) is inversely proportion to the fuel flow (25). The fuel flow rate is controlled (65) in proportion to enginemore » load. At high loads, more fuel and less air flow through the port, making more air available to the premixing assemblies (36).« less
  • The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.