US 11,747,017 B2
Combustor and gas turbine including the combustor
Yoshikazu Matsumura, Yokohama (JP); Naoki Abe, Yokohama (JP); Kenji Sato, Yokohama (JP); Shinji Akamatsu, Yokohama (JP); Kenta Taniguchi, Yokohama (JP); and Satoshi Takiguchi, Tokyo (JP)
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Appl. No. 16/628,852
Filed by Mitsubishi Hitachi Power Systems, Ltd., Yokohama (JP)
PCT Filed Jul. 23, 2018, PCT No. PCT/JP2018/027423
§ 371(c)(1), (2) Date Jan. 6, 2020,
PCT Pub. No. WO2019/039161, PCT Pub. Date Feb. 28, 2019.
Claims priority of application No. 2017-158936 (JP), filed on Aug. 21, 2017.
Prior Publication US 2020/0208575 A1, Jul. 2, 2020
Int. Cl. F23R 3/04 (2006.01); F23R 3/16 (2006.01); F23R 3/28 (2006.01); F23R 3/34 (2006.01); F23R 3/10 (2006.01); F23R 3/18 (2006.01)
CPC F23R 3/04 (2013.01) [F23R 3/16 (2013.01); F23R 3/286 (2013.01); F05D 2270/082 (2013.01); F23R 3/10 (2013.01); F23R 3/18 (2013.01); F23R 3/343 (2013.01); F23R 2900/03041 (2013.01); F23R 2900/03042 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A combustor, comprising:
a plurality of fuel nozzles disposed in a circumferential direction;
a flame holding ring extending in the circumferential direction at a radially inner side of outlet portions of the plurality of fuel nozzles;
an upstream-side wall portion extending in the circumferential direction at an upstream side of the flame holding ring, the upstream-side wall portion having a plurality of air inlets for supplying air toward the flame holding ring via an annular space at the radially inner side of the outlet portions of the plurality of fuel nozzles,
wherein the upstream-side wall portion includes:
a plurality of first regions each having a first number of the plurality of air inlets, wherein each of the plurality of first regions extends circumferentially in a respective first range corresponding to a respective fuel nozzle position of each of the plurality of fuel nozzles; and
a plurality of second regions each having a second number of the plurality of air inlets with the second number higher than the first number;
wherein each of the plurality of second regions extends circumferentially in a respective second range corresponding to a respective circumferential position between a respective pair of adjacent fuel nozzles of the plurality of fuel nozzles such that each of the plurality of second regions alternates with each of the plurality of first regions in the circumferential direction, and in which the second number of the plurality of air inlets are formed at a higher density than a density of the first number of the plurality of air inlets, and
wherein a first spacing in the circumferential direction between each air inlet of the second number within a respective second region is smaller than a second spacing in the circumferential direction between any air inlet of the second number within the respective second region and any air inlet of the first number within an adjacent first region.