US 12,247,522 B2
Burner assembly, gas turbine combustor, and gas turbine
Shinichi Fukuba, Tokyo (JP); Satoshi Takiguchi, Tokyo (JP); Keisuke Miura, Tokyo (JP); Tomohiro Asai, Tokyo (JP); Kenji Miyamoto, Yokohama (JP); Tomo Kawakami, Yokohama (JP); Kenta Taniguchi, Yokohama (JP); and Katsuyoshi Tada, Tokyo (JP)
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Filed by MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Filed on Aug. 12, 2022, as Appl. No. 17/886,802.
Application 17/886,802 is a continuation of application No. PCT/JP2020/027016, filed on Jul. 10, 2020.
Claims priority of application No. 2020-076142 (JP), filed on Apr. 22, 2020.
Prior Publication US 2022/0381184 A1, Dec. 1, 2022
Int. Cl. F02C 7/22 (2006.01); F23D 14/62 (2006.01); F23R 3/00 (2006.01); F23R 3/28 (2006.01)
CPC F02C 7/22 (2013.01) [F23D 14/62 (2013.01); F23R 3/002 (2013.01); F23R 3/286 (2013.01); F05D 2240/35 (2013.01)] 5 Claims
OG exemplary drawing
 
1. A burner assembly, comprising a plurality of burners for mixing fuel and air,
wherein each of the plurality of burners includes:
at least one fuel nozzle for injecting the fuel; and
a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced via an inlet of the mixing passage,
wherein the plurality of burners includes a first burner, and a second burner having the mixing passage that is closest to the mixing passage of the first burner,
wherein the mixing passage of the first burner and the mixing passage of the second burner are separated by a partition portion,
wherein, for each of the first burner and the second burner, each of the at least one fuel nozzle includes a protruding portion protruding upstream from an upstream end portion of the partition portion in a flow direction of the air, and at least one fuel injection hole formed on a side surface of the protruding portion,
wherein, for each of the first burner and the second burner, a top surface of the protruding portion of each of the at least one fuel nozzle, which is an upstream end surface of the protruding portion in the flow direction of the air, includes a convex curved surface,
wherein the at least one fuel nozzle of the first burner includes a first fuel nozzle which is closest to the mixing passage of the first burner and the mixing passage of the second burner, and the at least one fuel injection hole of the first fuel nozzle includes a first fuel injection hole for supplying the fuel to the mixing passage of the first burner and a second fuel injection hole for supplying the fuel to the mixing passage of the second burner,
wherein, a cross-section of the partition portion in a plane passing through a center of the inlet of the mixing passage of the first burner and a center of the inlet of the mixing passage of the second burner and taken along a central axis of the mixing passage of the first burner is defined as a first cross-section,
wherein a thickness of the partition portion in the first cross-section decreases upstream in the flow direction of the air from a downstream end of the upstream end portion of the partition portion to an upstream end surface of the upstream end portion of the partition portion in the flow direction of the air, and
wherein the upstream end surface of the partition portion in the flow direction of the air includes a convex curved line in the first cross-section.