Granted Patent B2

US 12,693,019 · App. 18/779,279 · Granted Jul 28, 2026

Inventors: Pradeep Naik (Bengaluru, IN); Karthikeyan Sampath (Bengaluru, IN); Michael A. Benjamin (Cincinnati, OH); Sibtosh Pal (Mason, OH); Michael T. Bucaro (Arvada, CO); Prithiviraaj Pet T (Madurai, IN); Pabitra Badhuk (Jhargram, IN); Clayton S. Cooper (Loveland, OH)

Assignee: General Electric Company

F23R3/286F02C3/22F02C9/40F23R3/346

Abstract

Claims (24)

1 . A gas turbine engine, comprising:

a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising:

a combustor liner that at least partially defines a combustion chamber, the combustion chamber defining a centerline; and

a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber and comprising:

a rich fuel supply including a rich mixture of gaseous fuel and air;

a lean fuel supply including a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture;

a rich fluid passage fluidly coupled to the rich fuel supply and emitting the rich mixture in a direction towards the centerline of the combustion chamber into the combustion chamber; and

a lean fluid passage fluidly coupled to the lean fuel supply and emitting the lean mixture in a direction away from the centerline of the combustion chamber into the combustion chamber;

wherein the combustion section includes a wall coupled to the combustor liner;

wherein the gaseous fuel nozzle assembly includes at least a portion of the wall; and

wherein the combustor liner includes a height at the wall;

wherein a ratio of a lean fluid passage diameter of the lean fluid passage to the height of the combustor liner is at least 0.3 and less than or equal to 0.8;

wherein a ratio of a rich fluid passage diameter of the rich fluid passage to the height of the combustor liner is at least 0.1 and less than or equal to 0.6.

2 . The gas turbine engine of claim 1 , wherein the rich mixture of gaseous fuel and air has a first equivalence ratio greater than 4 and less than or equal to 10.

3 . The gas turbine engine of claim 2 , wherein the lean mixture of gaseous fuel and air has a second equivalence ratio of greater than 0 and less than or equal to 0.4.

4 . The gas turbine engine of claim 3 , wherein the gaseous fuel is hydrogen gas.

5 . The gas turbine engine of claim 1 , wherein the rich fluid passage and the lean fluid passage are annular and concentric.

6 . The gas turbine engine of claim 5 , wherein a rich fluid passage output of the rich fluid passage is disposed radially inward of a lean fluid passage output of the lean fluid passage.

7 . The gas turbine engine of claim 1 , wherein the lean fluid passage and the rich fluid passage are configured to provide an amount of air to the combustion chamber; and

wherein the rich fluid passage provides at least 5% and less than or equal to 25% of the amount of air to the combustion chamber.

8 . The gas turbine engine of claim 1 , wherein the rich fluid passage is configured to generate an inside-out recirculation of the rich mixture in the combustion chamber;

wherein the lean fluid passage to configured to generate an outside-in recirculation of the lean mixture in the combustion chamber; and

wherein the gaseous fuel nozzle assembly and the combustor liner are configured such that the outside-in recirculation overlaps with the inside-out recirculation.

9 . The gas turbine engine of claim 1 , further comprising a second gaseous fuel nozzle assembly disposed adjacent the gaseous fuel nozzle assembly.

Assignments (2)

Continuity (1)

References Cited (24)