Granted Patent B2

US 12,607,357 · App. 18/105,012 · Granted Apr 21, 2026

Inventor: Tin Cheung John Hu (Markham, CA)

Assignee: PRATT & WHITNEY CANADA CORP.

F23R3/286F23D14/82F23D2212/20

Abstract

Claims (22)

1 . A combustor for a gas turbine engine comprising:

a liner surrounding a gaseous fuel and air mixing body;

a gaseous fuel supply passage, said fuel supply passage communicating into an open fuel plenum downstream of said fuel supply passage;

a wall of the mixing body having air openings to receive air flow, and communicate air into a plurality of mixing passages, said plurality of mixing passages passing through said fuel plenum, fuel openings in the plurality of mixing passages allow fuel to flow from the fuel plenum into the plurality of mixing passages and mix with the air;

a plurality of passage sections extend downstream of the fuel plenum, such that said mixed air and fuel travels downstream of the fuel plenum and through a plurality of outlets into a combustion chamber;

wherein there is at least one of an open cell material or cellular metallic material (CMM), at least within the plurality of passage sections downstream of the fuel plenum;

wherein the at least one of the open cell material or cellular metallic material is also at a location of the fuel openings; and

wherein said fuel supply includes a central fuel passage at a generally central location in the mixing body, with the fuel plenum extending both circumferentially and radially on both sides of the central fuel passage.

2 . The combustor as set forth in claim 1 , wherein an inner face of the mixing body at the combustor is generally non-planar to an axis of the central fuel passage.

3 . The combustor as set forth in claim 2 , wherein at least some of said passage sections which are radially closer to the central fuel passage extend for a shorter axial length than do others of said passage sections spaced further from said central fuel passage.

4 . A gas turbine engine comprising:

a compressor section and a turbine section;

a combustor intermediate said compressor and said turbine;

a gaseous fuel supply delivering fuel into a mixing body in the combustor, a liner surrounding the mixing body;

the fuel supply communicating with a fuel supply passage, said fuel supply passage communicating into an open fuel plenum downstream of said fuel supply passage;

a wall of the mixing body having air openings to receive air flow, and communicate air into plurality of mixing passages, said plurality of said plurality of mixing passages passing through said fuel plenum, fuel openings in the plurality of said plurality of mixing passages allow fuel to flow from the fuel plenum into the mixing passages and mix with the air;

plurality of passage sections extend downstream of the fuel plenum, such that said mixed air and fuel travels downstream of the fuel plenum and through a plurality of outlets into a combustion chamber;

wherein there is at least one of an open cell material or cellular metallic materials (CMM), at least within the plurality of passage sections downstream of the fuel plenum;

wherein the open cell material or cellular metallic material is also at a location of the fuel openings; and

wherein said fuel supply passage includes a central fuel passage at a generally central location in the mixing body, with the fuel plenum extending both circumferentially and radially on both sides of the central fuel passage.

5 . The gas turbine engine as set forth in claim 4 , wherein an inner face of the mixing body at the combustor is generally non-planar to an axis of the central fuel passage.

6 . The gas turbine engine as set forth in claim 5 , wherein at least some of the plurality of passage sections which are radially closer to the central fuel passage extend for a shorter axial length than do others of said plurality of passage sections spaced further from said central fuel passage.

Assignments (1)

Continuity (1)

References Cited (50)