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US 12,215,869 B2Granted
Gas turbine combustor fuel nozzle assembly and combustor liner having dilution holes in arrangements
AssigneeGeneral Electric Company
InventorsNayan Vinod Patel, Michael A. Benjamin
Life of this patent
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Abstract
A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
Claims20
A turbine engine comprising:
- a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section including a combustor defining a longitudinal axis, the combustor comprising:
- a combustor liner partially defining a combustion chamber;
- and
- a set of dilution holes provided in the combustor liner, with the set of dilution holes arranged into pairs of adjacent dilution holes, with each pair of adjacent dilution holes being spaced to define a distance defined in one or both of an axial direction and a circumferential direction, relative to the longitudinal axis;
- wherein, relative to the longitudinal axis, a first pair of adjacent dilution holes are positioned forward of a second pair of adjacent dilution holes, the first pair of adjacent dilution holes are spaced to define a first distance, and the second pair of adjacent dilution holes are spaced to define a second distance lesser than the first distance;
- and
- wherein at least one dilution hole of the set of dilution holes is arranged at a non-orthogonal angle relative to the longitudinal axis.
4 more elements
A turbine engine comprising:
- a compressor section, a combustion section, and a turbine section in serial flow arrangement, and the combustion section having a combustor defining a longitudinal axis and comprising:
- a combustor liner partially defining a combustion chamber;
- a set of dilution holes provided in the combustor liner, with the set of dilution holes arranged into pairs of adjacent dilution holes, with each pair of adjacent dilution holes being spaced to define a distance;
- a deflector coupled to the combustor liner and partially defining the combustion chamber;
- a set of air-fuel nozzles arranged on the deflector, with each air-fuel nozzle of the set of air-fuel nozzles comprising:
- a body having a nozzle outlet arranged on the deflector and the nozzle outlet fluidly coupled to the combustion chamber;
- an air flow passage located within the body and having an air outlet at least partially defining the nozzle outlet;
- and
- a fuel flow passage located within the air flow passage and having a fuel outlet at least partially defining the nozzle outlet, and
- wherein at least one dilution hole of the set of dilution holes is arranged at a non-orthogonal angle relative to the longitudinal axis.
7 more elements
Dependencies are inferred from the claim text.