US 5,410,884 A · Combustor for gas turbines with diverging pilot nozzle cone

Abstract

A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles surround the pilot nozzle. A diverging cone projects from the vicinity of the injection port of the pilot nozzle such that the flame from the main nozzles is sustained by the pilot nozzle and NOx is suppressed. The main nozzles can be provided upstream of the injection port of the pilot nozzle in which case an annular premixing nozzle having a throttled exit end is disposed downstream of the main nozzles. The main nozzle may also be in the form of a fuel nozzle having a plurality of tubes, a gaseous fuel being injected through one of the tubes, and liquid fuel being injected into the annular premixing nozzle through the other of the tubes so that the liquid fuel is atomized to mix the fuel and air homogeneously.

Claims6

Dependent claims

A gas turbine combustor comprising:

a combustion chamber;
a pilot nozzle disposed on the axial centerline of the gas turbine combustor upstream of said combustion chamber, said pilot nozzle having an injection port;
a cone projecting from the vicinity of the injection port of said pilot nozzle, the cone having a diverged base end adjacent the combustion chamber;
a plurality of main nozzles disposed around said pilot nozzle, each of said main nozzles having a fuel injection portion defining an injection port and a respective primary mixing chamber wall surrounding the fuel injection portion to form a primary mixing chamber in the main nozzle;
and a secondary mixing chamber, located between the primary mixing chamber wall of each of said main nozzles and said end of the cone, in which air and a fuel/air mixture from said main nozzles are mixed before passing to the combustion chamber, said secondary chamber being delimited and throttled by said end of the cone.

2 more elements

Dependencies are inferred from the claim text.

Combustor for gas turbines with diverging pilot nozzle cone

Life of this patent

Combustor for gas turbines with diverging pilot nozzle cone

Life of this patent

Abstract

Claims6