# US 9,435,539 B2 · Variable volume combustor with pre-nozzle fuel injection system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,435,539 B2 - Document ID: US9435539B2 - Status: Granted - Kind: B2 - Application number: 13/760,091 - Filed: 2013-02-06 - Published: 2014-08-07 - Granted: 2016-09-06 - Earliest claimed: 2013-02-06 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Christopher Paul Keener; Thomas Edward Johnson; Johnie Franklin McConnaughhay; Heath Michael Ostebee - Web page: https://patentgrep.com/patent/US9435539B2 ## CPC - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23C 5/06: Provision for adjustment of burner position during operation - F23R 3/10: for primary air (F23R3/06, F23R3/045 take precedence) - F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances} - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F23C: METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN {A CARRIER GAS OR} AIR (burners F23D) ## Abstract 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. ## Claims ### Claim 1 A combustor for use with a gas turbine engine, comprising: a liner; a cap assembly; a seal in between the liner and the cap assembly; a head end with a head end volume; a combustion zone with a combustion zone volume; a plurality of fuel nozzles positioned within the cap assembly; a pre-nozzle fuel injection system supporting the plurality of fuel nozzles, wherein the pre-nozzle fuel injection system separates the head end from the combustion zone; and a linear actuator to maneuver the plurality of fuel nozzles and the pre-nozzle fuel injection system, such that the head end volume is increased as the combustion zone volume is decreased. ### Claim 2 (depends on 1) The combustor of claim 1, wherein the plurality of fuel nozzles comprises a plurality of micro-mixer fuel nozzles. ### Claim 3 (depends on 1) The combustor of claim 1, further comprising a common fuel tube in communication with the pre-nozzle fuel injection system. ### Claim 4 (depends on 1) The combustor of claim 1, wherein the pre-nozzle fuel injection system comprises a fuel nozzle manifold. ### Claim 5 (depends on 4) The combustor of claim 4, wherein the fuel nozzle manifold comprises a center hub. ### Claim 6 (depends on 1) The combustor of claim 1, wherein the pre-nozzle fuel injection system comprises a plurality of support struts supporting the plurality of fuel nozzles. ### Claim 7 (depends on 6) The combustor of claim 6, wherein the plurality of support struts comprises a substantially aerodynamically contoured shape. ### Claim 8 (depends on 6) The combustor of claim 6, wherein the plurality of support struts is positioned upstream of the plurality of fuel nozzles. ### Claim 9 (depends on 6) The combustor of claim 6, wherein the plurality of support struts comprises a plurality of fuel injections holes. ### Claim 10 (depends on 9) The combustor of claim 9, wherein the plurality of support struts comprises a first side wall and a second side wall and wherein the plurality of fuel injection holes is positioned thereon. ### Claim 11 (depends on 9) The combustor of claim 9, wherein a pre-nozzle fuel flow passes through the plurality of fuel injection holes. ### Claim 12 (depends on 11) The combustor of claim 11, wherein the pre-nozzle flow comprises about twenty percent or less of a flow of fuel to the plurality of fuel nozzles. ### Claim 13 (depends on 1) The combustor of claim 1, wherein the linear actuator comprises a drive rod in communication with the pre-nozzle fuel injection system. ### Claim 14 A method of operating a combustor in a gas turbine engine, the combustor comprising a liner, a cap assembly, and a seal in between the liner and the cap assembly, the method comprising: supporting a plurality of fuel nozzles about a plurality of support struts, the plurality of fuel nozzles positioned within the cap assembly; flowing a flow of fuel through the plurality of support struts to the plurality of fuel nozzles; actuating the plurality of fuel nozzles from a first position to a second position, such that a head end volume of the combustor is increased as a combustion zone volume of the combustor is decreased; diverting a pre-nozzle flow of fuel from the plurality of support struts; flowing a flow of air through the plurality of support struts; and mixing the flow of air and the pre-nozzle flow of fuel upstream of the plurality of fuel nozzles. ### Claim 15 A combustor for use with a gas turbine engine, comprising: a liner; a cap assembly; a seal in between the liner and the cap assembly; a head end with a head end volume; a combustion zone with a combustion zone volume; a plurality of micro-mixer fuel nozzles positioned within the cap assembly; a plurality of support struts supporting the plurality of micro-mixer fuel nozzles; the plurality of support struts comprising a plurality of fuel injections holes thereon; and a linear actuator to maneuver the plurality of micro-mixer fuel nozzles and the plurality of support struts, such that the head end volume is increased as the combustion zone volume is decreased. ### Claim 16 (depends on 15) The combustor of claim 15, wherein the plurality of support struts comprises a substantially aerodynamically contoured shape. ### Claim 17 (depends on 15) The combustor of claim 15, wherein the plurality of support struts is positioned upstream of the plurality of fuel nozzles. ### Claim 18 (depends on 15) The combustor of claim 15, wherein the plurality of support struts comprises a first side wall and a second side wall and wherein the plurality of fuel injection holes is positioned thereon. ### Claim 19 (depends on 15) The combustor of claim 15, wherein a pre-nozzle fuel flow passes through the plurality of fuel injection holes.