US 11,867,085 B2
Turbine blade
Satoshi Mizukami, Yokohama (JP); Masamitsu Kuwabara, Yokohama (JP); Satoshi Hada, Yokohama (JP); Saki Matsuo, Yokohama (JP); Yoshitaka Uemura, Yokohama (JP); Ryozo Tamura, Yokohama (JP); and Yasumasa Kunisada, Yokohama (JP)
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Appl. No. 17/778,974
Filed by MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
PCT Filed Mar. 23, 2021, PCT No. PCT/JP2021/011939
§ 371(c)(1), (2) Date May 23, 2022,
PCT Pub. No. WO2021/193610, PCT Pub. Date Sep. 30, 2021.
Claims priority of application No. 2020-053727 (JP), filed on Mar. 25, 2020.
Prior Publication US 2022/0412220 A1, Dec. 29, 2022
Int. Cl. F01D 5/18 (2006.01)
CPC F01D 5/187 (2013.01) [F05D 2220/32 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A turbine blade, comprising an airfoil portion having a leading edge, a trailing edge, and a pressure surface and a suction surface which extend between the leading edge and the trailing edge, the airfoil portion internally forming a cooling passage,
wherein the cooling passage includes:
a first cooling passage located closer to the pressure surface than the suction surface; and
a second cooling passage located closer to the suction surface than the pressure surface,
wherein the first cooling passage and the second cooling passage are separated by a partition member disposed in the airfoil portion,
wherein at least one communication space connecting the first cooling passage and the second cooling passage is formed in the partition member,
wherein the at least one communication space is different from each of the first cooling passage and the second cooling passage, and
wherein the partition member is a solid portion except for the at least one communication space.