Ring-segment surface-side member, ring-segment support-side member, ring segment, stationary-side member unit, and method

A ring-segment support-side member that is included in a ring segment disposed at a position opposite to a turbine blade with respect to a radial direction of the gas turbine on a stationary side of a gas turbine, and supports a ring-segment surface-side member serving as a part of a combustion gas flow path through which combustion gas flows,

• the ring-segment support-side member being formed of metal,
• the ring-segment support-side member comprising:
• an engagement portion to be engaged with the ring-segment surface-side member;
• and
• an opposing portion that:
• faces a back surface of the surface portion of the ring-segment surface-side member, the surface portion forming the combustion gas flow path, and
• has a surface forming a cooling space in which cooling air flows between the opposing portion and the surface portion,
• wherein the opposing portion includes a flow-path resistance adjuster configured to adjust a flow-path resistance of the cooling space, the flow-path resistance adjuster including:
• a plurality of dividing plates arranged to divide the cooling space into a plurality of cooling rooms arranged along a direction of combustion gas flow, and
• a plurality of through-holes each configured to supply cooling air to a respective one of the plurality of cooling rooms, and
• and
• wherein the flow-path resistance adjuster is configured to adjust a pressure of the cooling air flowing in the cooling space such that a pressure of the cooling air in an upstream-most one of the cooling rooms with respect to a direction of combustion gas flow through the gas turbine is higher than a pressure of the cooling air in a downstream-most one of the cooling rooms with respect to the direction of combustion gas flow.

A ring segment disposed at a position opposite to a turbine blade with respect to a radial direction of the gas turbine on a stationary side of a gas turbine, the ring segment comprising:

• a ring-segment surface-side member serving as a part of a combustion gas flow path through which combustion gas flows and formed of a ceramic matrix composite;
• and
• a ring-segment support-side member disposed on an outer side of the ring-segment surface-side member in a radial direction of the gas turbine, supporting the ring-segment surface-side member, forming a cooling space in which cooling air flows between the ring-segment support-side member and the ring-segment surface-side member, and formed of metal,
• wherein the ring-segment support-side member includes:
• a seal provided at an end face of the ring-segment support-side member in a rotational direction of the gas turbine, extending in an axial direction of the gas turbine, having both ends being in contact with members adjacent thereto in the axial direction, and sealing air flow in the radial direction of the gas turbine, and
• a flow-path resistance adjuster configured to adjust a flow-path resistance of the cooling space
• wherein the ring-segment surface-side member is disposed on an inner side of the seal in the radial direction of the gas turbine, and
• wherein the flow-path resistance dividing plate includes:
• a plurality of dividing plates arranged to divide the cooling space into a plurality of cooling rooms arranged along a direction of combustion gas flow, and
• a plurality of through-holes each configured to supply cooling air to a respective one of the plurality of cooling rooms, and
• wherein the flow-path resistance dividing plate is configured to adjust a pressure of cooling air flowing in the cooling space such that a pressure of the cooling air in an upstream-most one of the cooling rooms with respect to a direction of combustion gas flow through the gas turbine is higher than a pressure of the cooling air in a downstream-most one of the cooling rooms with respect to the direction of combustion gas flow.