Granted Patent B2

US 12,359,812 · App. 18/663,324 · Granted Jul 15, 2025

Inventors: Perumallu Vukanti (Bengaluru, IN); Sibtosh Pal (Mason, OH); Pradeep Naik (Bengaluru, IN); R Narasimha Chiranthan (Bengaluru, IN); Ajoy Patra (Bengaluru, IN); Michael T. Bucaro (Arvada, CO); Aritra Chakraborty (Bengaluru, IN); Arijit Sinha Roy (Bengaluru, IN); Pabitra Badhuk (Bengaluru, IN); Bhavya Naidu Panduri (Bengaluru, IN)

Assignee: GENERAL ELECTRIC COMPANY

F23R3/06

Abstract

Claims (72)

1. A gas turbine engine comprising:

a compressor section, combustor section, and turbine section defining an engine rotational axis, the combustor section comprising:

a combustor liner at least partially defining a combustion chamber;

a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber;

a fuel nozzle located on the dome wall and fluidly coupled to the combustion chamber;

a first set of openings provided in the dome wall with each opening of the first set of openings configured to emit air into the combustion chamber along a first flow path streamline; and

a second set of openings provided in the dome wall with each opening of the second set of openings configured to emit air into the combustion chamber along a second flow path streamline;

wherein the first flow path streamline intersects the second flow path streamline at an intersection point; and

wherein the first set of openings are aligned in circumferential arrangement at a first common radius about the engine rotational axis and the second set of openings are aligned in circumferential arrangement at a second common radius about the engine rotational axis.

2. The gas turbine engine of claim 1 , wherein the first set of openings are radially unaligned with the second set of openings.

3. The gas turbine engine of claim 1 , wherein each opening of the first set of openings is aligned with one opening of the second set of openings defined in a radial direction relative to the engine rotational axis.

4. A combustor for a turbine engine defining an engine rotational axis, the combustor comprising:

a dome wall;

a fuel nozzle located on the dome wall;

a first opening provided in the dome wall configured to emit air along a first flow path streamline; and

a second opening provided in the dome wall configured to emit air along a second flow path streamline;

wherein the first flow path streamline intersects the second flow path streamline at an intersection point; and

wherein the first opening and the second opening are aligned in circumferential arrangement at a common radius about the engine rotational axis.

5. The combustor of claim 4 , wherein the first opening is unaligned with the second opening in a radial direction relative to the engine rotational axis.

6. A gas turbine engine comprising:

a compressor section, combustor section, and turbine section defining an engine rotational axis, the combustor section comprising:

a combustor liner at least partially defining a combustion chamber;

a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber;

a fuel nozzle located on the dome wall and fluidly coupled to the combustion chamber;

a first set of openings provided in the dome wall with each opening of the first set of openings configured to emit air into the combustion chamber along a first flow path streamline; and

a second set of openings provided in the dome wall with each opening of the second set of openings configured to emit air into the combustion chamber along a second flow path streamline;

wherein the first flow path streamline intersects the second flow path streamline at an intersection point;

wherein each opening of the first set of openings is paired with one opening of the second set of openings to define pairs of openings, and wherein each pair of openings includes the first flow path streamline that intersects the second flow path streamline at the intersection point; and

wherein a first pair of openings of the pairs of openings defines a first opening axis and a second pair of openings of the pairs of openings defines a second opening axis, and wherein the first pair of openings and the second pair of openings are arranged such that the first opening axis is arranged perpendicular to and intersecting the second opening axis.

7. The gas turbine engine of claim 6 , wherein at least one pair of openings of the first pair of openings or the second pair of openings spans adjacent segments of the dome wall.

8. A gas turbine engine comprising:

a compressor section, combustor section, and turbine section defining an engine rotational axis, the combustor section comprising:

a combustor liner at least partially defining a combustion chamber;

a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber;

a fuel nozzle located on the dome wall and fluidly coupled to the combustion chamber;

a first set of openings provided in the dome wall with each opening of the first set of openings configured to emit air into the combustion chamber along a first flow path streamline; and

a second set of openings provided in the dome wall with each opening of the second set of openings configured to emit air into the combustion chamber along a second flow path streamline;

wherein the first flow path streamline intersects the second flow path streamline at an intersection point;

wherein each opening of the first set of openings is paired with one opening of the second set of openings to define pairs of openings, and wherein each pair of openings includes the first flow path streamline that intersects the second flow path streamline at the intersection point;

wherein each pair of openings includes a radially inner opening and a radially outer opening, and wherein the radially inner opening is radially offset from the radially outer opening for each pair of openings relative to a radial axis extending from the engine rotational axis; and

wherein at least some openings of the pairs of openings are positioned radially interior of the fuel nozzle and at least some openings of the pairs of openings are positioned radially exterior of the fuel nozzle relative to the radial axis extending from the engine rotational axis.

9. A gas turbine engine comprising:

a compressor section, combustor section, and turbine section defining an engine rotational axis, the combustor section comprising:

a combustor liner at least partially defining a combustion chamber;

a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber;

a fuel nozzle located on the dome wall and fluidly coupled to the combustion chamber;

a first set of openings provided in the dome wall with each opening of the first set of openings configured to emit air into the combustion chamber along a first flow path streamline; and

a second set of openings provided in the dome wall with each opening of the second set of openings configured to emit air into the combustion chamber along a second flow path streamline;

wherein the first flow path streamline intersects the second flow path streamline at an intersection point;

wherein each opening of the first set of openings is paired with one opening of the second set of openings to define pairs of openings, and wherein each pair of openings includes the first flow path streamline that intersects the second flow path streamline at the intersection point; and

wherein the pairs of openings are aligned in a circumferential direction defined relative to the engine rotational axis.

10. A gas turbine engine comprising:

a compressor section, combustor section, and turbine section defining an engine rotational axis, the combustor section comprising:

a combustor liner at least partially defining a combustion chamber;

a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber;

a fuel nozzle located on the dome wall and fluidly coupled to the combustion chamber;

a first set of openings provided in the dome wall with each opening of the first set of openings configured to emit air into the combustion chamber along a first flow path streamline; and

a second set of openings provided in the dome wall with each opening of the second set of openings configured to emit air into the combustion chamber along a second flow path streamline;

wherein the first flow path streamline intersects the second flow path streamline at an intersection point;

wherein each opening of the first set of openings is paired with one opening of the second set of openings to define pairs of openings, and wherein each pair of openings includes the first flow path streamline that intersects the second flow path streamline at the intersection point; and

wherein at least some pairs of openings are positioned radially exterior of the fuel nozzle and at least some pairs of openings are positioned radially interior of the fuel nozzle.

11. A gas turbine engine comprising:

a compressor section, combustor section, and turbine section defining an engine rotational axis, the combustor section comprising:

a combustor liner at least partially defining a combustion chamber;

a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber;

a fuel nozzle located on the dome wall and fluidly coupled to the combustion chamber;

a first set of openings provided in the dome wall with each opening of the first set of openings configured to emit air into the combustion chamber along a first flow path streamline; and

a second set of openings provided in the dome wall with each opening of the second set of openings configured to emit air into the combustion chamber along a second flow path streamline;

wherein the first flow path streamline intersects the second flow path streamline at an intersection point;

wherein each opening of the first set of openings is paired with one opening of the second set of openings to define pairs of openings, and wherein each pair of openings includes the first flow path streamline that intersects the second flow path streamline at the intersection point; and

wherein each pair of openings includes a pair axis defining an angle relative to a radial axis extending from the engine rotational axis and wherein the pair axis for the pairs of openings varies based upon distance of the pairs of openings from the fuel nozzle.

12. The gas turbine engine of claim 11 , wherein the angle increases for the pairs of openings as distance from the fuel nozzle increases.

Assignments (2)

Continuity (2)

References Cited (15)