Abstract: A thermal insulation coating member includes: a substrate having a surface; a binding layer on the surface, and a thermal insulation layer on the binding layer. The thermal insulation layer includes: a first ceramic layer including a plurality of first flat pores, the plurality of first flat pores being inclined at a first angle with respect to the surface and extending in a first direction; and a second ceramic layer including a plurality of second flat pores, the plurality of second flat pores being inclined at a second angle with respect to the surface and extending in a second direction. The second angle differs from the first angle, the second direction differing from the first direction, or the second angle and the second direction respectively differing from the first angle and the first direction.

Abstract: The gas turbine facility 10 of the embodiment includes a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas, a heat exchanger 23 cooling the combustion gas, a heat exchanger 24 removing water vapor from the combustion gas which passed through the heat exchanger 23 to regenerate dry working gas, and a compressor 25 compressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facility 10 includes a pipe 42 guiding a part of the dry working gas from the compressor 25 to the combustor 20 via the heat exchanger 23, a pipe 44 exhausting a part of the dry working gas to the outside, and a pipe 45 introducing a remaining part of the dry working gas exhausted from the compressor 25 into a pipe 40 coupling an outlet of the turbine 21 and an inlet of the heat exchanger 23.

Abstract: A thermal insulation coating member comprises: a substrate having a surface; a binding layer on the surface; and a thermal insulation layer on the binding layer. The thermal insulation layer includes: a first ceramic layer having a plurality of first flat pores, the first flat pores being inclined at a first angle with respect to the surface and extending in a first direction; and a second ceramic layer having a plurality of second flat pores, the second flat pores being inclined at a second angle with respect to the surface and extending in a second direction. The second angle differs from the first angle, the second direction differing from the first direction, or the second angle and the second direction respectively differing from the first angle and the first direction.

Abstract: The gas turbine facility 10 of the embodiment includes a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas, a heat exchanger 23 cooling the combustion gas, a heat exchanger 24 removing water vapor from the combustion gas which passed through the heat exchanger 23 to regenerate dry working gas, and a compressor 25 compressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facility 10 includes a pipe 42 guiding a part of the dry working gas from the compressor 25 to the combustor 20 via the heat exchanger 23, a pipe 44 exhausting a part of the dry working gas to the outside, and a pipe 45 introducing a remaining part of the dry working gas exhausted from the compressor 25 into a pipe 40 coupling an outlet of the turbine 21 and an inlet of the heat exchanger 23.

Abstract: A turbine according to an embodiment includes: a formation object member; a facing member; and a seal part. A formation object member is one of a static part and a rotation part. A facing member is the other of the static part and the rotation part. A seal part at the formation object member is configured to reduce combustion gas leaking between the formation object member and the facing member. The seal part including a ceramics layer. The ceramics layer has a heat conductivity lower than that of the formation object member, and has a concave and convex shape at a surface thereof. The ceramics layer is not in contact with the facing member, or has hardness higher than that of the facing member so that the facing member is preferentially abraded when the facing member and the ceramics layer are in contact with each other.

Abstract: The gas turbine facility 10 of the embodiment includes a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas, a heat exchanger 23 cooling the combustion gas, a heat exchanger 24 removing water vapor from the combustion gas which passed through the heat exchanger 23 to regenerate dry working gas, and a compressor 25 compressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facility 10 includes a pipe 42 guiding a part of the dry working gas from the compressor 25 to the combustor 20 via the heat exchanger 23, a pipe 44 exhausting a part of the dry working gas to the outside, and a pipe 45 introducing a remaining part of the dry working gas exhausted from the compressor 25 into a pipe 40 coupling an outlet of the turbine 21 and an inlet of the heat exchanger 23.

Abstract: A single-flow turbine using CO2 as a working fluid. The turbine includes a balance piston portion configured to optimize an axial load of a rotor on a bearing with a fluid having a temperature lower than a temperature of the working fluid introduced into the turbine, wherein a flow path in which at least a part of the fluid passing through the balance piston portion is extracted from a middle part of the passing, and in which at least a part of the extracted fluid is urged to flow to a middle part of a passage where the working fluid passes and where rotor blades at a plurality of stages are provided, is formed at the turbine.

Abstract: In one embodiment, a turbine using CO2 includes moving blades, stator blades, a working fluid transport flow path, a coolant transport flow path, and a coolant recovery flow path. The stator blades constitute turbine stages together with the moving blades. The working fluid transport flow path is configured to transport the working fluid sequentially to the turbine stages. The coolant transport flow path is configured to transport the coolant by allowing the coolant to sequentially pass through the inside of the stator blades from an upstream to a downstream of the working fluid. The coolant recovery flow path is configured to recover the coolant passing through the inside of the stator blade at a predetermined turbine stage and merge the recovered coolant with the working fluid transport flow path at a turbine stage on an upstream side of the predetermined turbine stage.

Abstract: The gas turbine facility 10 of the embodiment includes a combustor 20 combusting fuel and oxidant, a turbine 21 rotated by combustion gas, a heat exchanger 23 cooling the combustion gas, a heat exchanger 24 removing water vapor from the combustion gas which passed through the heat exchanger 23 to regenerate dry working gas, and a compressor 25 compressing the dry working gas until it becomes supercritical fluid. Further, the gas turbine facility 10 includes a pipe 42 guiding a part of the dry working gas from the compressor 25 to the combustor 20 via the heat exchanger 23, a pipe 44 exhausting a part of the dry working gas to the outside, and a pipe 45 introducing a remaining part of the dry working gas exhausted from the compressor 25 into a pipe 40 coupling an outlet of the turbine 21 and an inlet of the heat exchanger 23.

Abstract: In one embodiment, a turbine using CO2 includes moving blades, stator blades, a working fluid transport flow path, a coolant transport flow path, and a coolant recovery flow path. The stator blades constitute turbine stages together with the moving blades. The working fluid transport flow path is configured to transport the working fluid sequentially to the turbine stages. The coolant transport flow path is configured to transport the coolant by allowing the coolant to sequentially pass through the inside of the stator blades from an upstream to a downstream of the working fluid. The coolant recovery flow path is configured to recover the coolant passing through the inside of the stator blade at a predetermined turbine stage and merge the recovered coolant with the working fluid transport flow path at a turbine stage on an upstream side of the predetermined turbine stage.

Abstract: A turbine according to an embodiment includes: a formation object member; a facing member; and a seal part. A formation object member is one of a static part and a rotation part. A facing member is the other of the static part and the rotation part. A seal part at the formation object member is configured to reduce combustion gas leaking between the formation object member and the facing member. The seal part including a ceramics layer. The ceramics layer has a heat conductivity lower than that of the formation object member, and has a concave and convex shape at a surface thereof. The ceramics layer is not in contact with the facing member, or has hardness higher than that of the facing member so that the facing member is preferentially abraded when the facing member and the ceramics layer are in contact with each other.

Abstract: According to one embodiment, there is provided a single-flow turbine using CO2 as a working fluid. The turbine includes a balance piston portion configured to optimize an axial load of a rotor on a bearing with a fluid having a temperature lower than a temperature of the working fluid introduced into the turbine, wherein a flow path in which at least a part of the fluid passing through the balance piston portion is extracted from a middle part of the passing, and in which at least a part of the extracted fluid is urged to flow to a middle part of a passage where the working fluid passes and where rotor blades at a plurality of stages are provided, is formed at the turbine.