US 12,134,975 B2
Blade ring assembly, gas turbine, and method for refurbishing gas turbine
Hiroaki Kobayashi, Tokyo (JP); Norihiko Nagai, Tokyo (JP); Kazuharu Hirokawa, Tokyo (JP); Shinya Hashimoto, Tokyo (JP); Naoki Taketa, Tokyo (JP); Takeshi Umehara, Tokyo (JP); Koji Watanabe, Tokyo (JP); Yoshio Fukui, Tokyo (JP); and Kenta Nakamura, Tokyo (JP)
Assigned to MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Appl. No. 18/284,969
Filed by MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
PCT Filed Apr. 12, 2022, PCT No. PCT/JP2022/017571
§ 371(c)(1), (2) Date Sep. 29, 2023,
PCT Pub. No. WO2022/224871, PCT Pub. Date Oct. 27, 2022.
Claims priority of application No. 2021-070571 (JP), filed on Apr. 19, 2021.
Prior Publication US 2024/0183277 A1, Jun. 6, 2024
Int. Cl. F01D 9/04 (2006.01); F02C 7/16 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 9/042 (2013.01); F02C 7/16 (2013.01); F05D 2240/35 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A blade ring assembly comprising:
a turbine blade ring that extends in a circumferential direction around an axis;
a cooling target component that is disposed on an inner peripheral side of the turbine blade ring; and
an outer peripheral side component that is disposed on an outer peripheral side of the turbine blade ring,
wherein the turbine blade ring includes a cooling medium intake port leading to an inner peripheral surface of the turbine blade ring from an outer peripheral surface of the turbine blade ring,
the outer peripheral side component includes
a first wall portion that covers at least a portion of the cooling medium intake port from the outer peripheral side of the turbine blade ring and that extends to be closer to an axial downstream side, which is opposite to an axial upstream side in an axial direction in which the axis extends, than the cooling medium intake port is, and
a second wall portion that extends toward the outer peripheral surface of the turbine blade ring from an end portion of the first wall portion on the axial downstream side and that covers at least a portion of a space between the first wall portion and the cooling medium intake port from the axial downstream side,
wherein the outer peripheral side component is an outer peripheral side cover disposed on the outer peripheral side of the turbine blade ring,
wherein the turbine blade ring further includes a first protrusion portion that protrudes toward the axial upstream side, and a second protrusion portion that is provided at a position different from the first protrusion portion in the circumferential direction and that protrudes toward the axial upstream side,
the cooling medium intake port is positioned between the first protrusion portion and the second protrusion portion in the circumferential direction, and
the outer peripheral side cover is disposed over a region between the first protrusion portion and the second protrusion portion.