US 12,291,981 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)
Filed by MITSUBISHI HEAVY INDUSTRIES, LTD., Tokyo (JP)
Filed on May 24, 2024, as Appl. No. 18/674,160.
Application 18/674,160 is a division of application No. 18/284,969, previously published as PCT/JP2022/017571, filed on Apr. 12, 2022.
Claims priority of application No. 2021-070571 (JP), filed on Apr. 19, 2021.
Prior Publication US 2024/0309770 A1, Sep. 19, 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)] 9 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 one of two opposite sides 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 L-shaped pipe formed in an L-like shape,
the L-shaped pipe includes
a first pipe portion that extends in a radial direction of the turbine blade ring from the cooling medium intake port, and
a second pipe portion that extends to a side opposite to the axial downstream side from an end portion of the first pipe portion that is on a side opposite to the turbine blade ring,
the second pipe portion communicates with the first pipe portion and includes an opening portion that is on a side opposite to the first pipe portion,
wherein the L-shaped pipe includes an orifice portion having a flow path area smaller than a flow path area of another portion of the L-shaped pipe, and
wherein the orifice portion is provided to be detachable with respect to the other portion of the L-shaped pipe.