US 11,867,079 B2
Flange cooling structure for gas turbine engine
Hayato Hirota, Kobe (JP); Tateki Sakimoto, Kobe (JP); Atsunori Arai, Kobe (JP); Tatsuya Okuwa, Kobe (JP); and Hikaru Maesato, Kobe (JP)
Assigned to KAWASAKI JUKOGYO KABUSHIKI KAISHA, Kobe (JP)
Appl. No. 17/800,056
Filed by KAWASAKI JUKOGYO KABUSHIKI KAISHA, Kobe (JP)
PCT Filed Feb. 18, 2021, PCT No. PCT/JP2021/006116
§ 371(c)(1), (2) Date Aug. 16, 2022,
PCT Pub. No. WO2021/167001, PCT Pub. Date Aug. 26, 2021.
Claims priority of provisional application 62/978,996, filed on Feb. 20, 2020.
Prior Publication US 2023/0080666 A1, Mar. 16, 2023
Int. Cl. F01D 5/08 (2006.01); F01D 25/24 (2006.01); F02C 7/18 (2006.01); F23R 3/42 (2006.01); F01D 25/08 (2006.01); F01D 25/12 (2006.01); F02C 7/12 (2006.01); F02C 7/32 (2006.01)
CPC F01D 5/082 (2013.01) [F01D 25/243 (2013.01); F02C 7/18 (2013.01); F23R 3/42 (2013.01); F01D 5/081 (2013.01); F01D 25/08 (2013.01); F01D 25/12 (2013.01); F01D 25/24 (2013.01); F01D 25/246 (2013.01); F02C 7/12 (2013.01); F02C 7/32 (2013.01); F05D 2260/20 (2013.01); F05D 2260/39 (2013.01); F23R 2900/03044 (2013.01); F23R 2900/03045 (2013.01)] 7 Claims
OG exemplary drawing
 
1. A flange cooling structure of a gas turbine engine in which a compressor, a combustor, and a turbine are arranged along a rotating shaft,
the flange cooling structure comprising:
a first member including a first main body and a first flange, the first main body defining a first space, the first flange projecting from the first main body, heat of the combustor being transferred to the first member;
a second member including a second main body and a second flange, the second main body defining a second space between the first main body and the second main body, the second flange projecting from the second main body, the second member being lower in temperature than the first member during operation of the gas turbine engine; and
fasteners that fasten the first flange and the second flange to each other to form a flange laminated body that divides the second space, wherein:
the second space is lower in temperature than the first space during the operation of the gas turbine engine;
the second space includes a first region located at one side of the flange laminated body and a second region located at the other side of the flange laminated body;
the first region is higher in pressure than the second region during the operation of the gas turbine engine;
one of the first flange and the second flange is a high pressure flange that faces the first region;
the other of the first flange and the second flange is a low pressure flange that faces the second region; and
a contact surface of the high pressure flange or a contact surface of the low pressure flange includes a cooling groove that communicates with the first region and the second region.