Variable volume combustor with an air bypass system

{
  "publication_number": "US9562687B2",
  "country": "US",
  "kind": "B2",
  "title": "Variable volume combustor with an air bypass system",
  "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.",
  "claims": [
    "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."
  ],
  "cpc": [
    "F23R 3/04",
    "F23R 2900/00012",
    "F23R 3/045",
    "F23R 3/286",
    "Y02T 50/60",
    "Y02T 50/675"
  ],
  "assignees": [
    "GEN ELECTRIC"
  ],
  "filing_date": "2013-02-06",
  "publication_date": "2017-02-07",
  "grant_date": "2017-02-07",
  "priority_date": "2013-02-06",
  "application_number": "US-201313760101-A",
  "family_id": "51238244",
  "citations": [
    "US2009016810A1",
    "US2010175380A1",
    "US2011252805A1",
    "US2012085100A1",
    "US2012198851A1",
    "US2012198856A1",
    "US3738106A",
    "US3742703A",
    "US3745766A",
    "US4044553A",
    "US4365910A",
    "US4417846A",
    "US4497170A",
    "US4532762A",
    "US4545196A",
    "US4567724A",
    "US4844649A",
    "US5195853A",
    "US5319923A",
    "US5343697A",
    "US5404633A",
    "US5540056A",
    "US5551228A",
    "US5664412A",
    "US5895211A",
    "US6425240B1",
    "US6438959B1",
    "US7093445B2",
    "US7500347B2",
    "US7661267B2"
  ]
}