Abstract: A fuel supply pipe assembly according to at least one embodiment of the present disclosure is a fuel supply pipe assembly for supplying fuel to a fuel nozzle provided on a side portion of a combustion liner of a gas turbine combustor, provided with: a fuel supply pipe for supplying the fuel to the fuel nozzle; a first flange portion capable of coupling with a flange portion of a fuel line for supplying the fuel to the fuel supply pipe; and a second flange portion capable of coupling with a top hat portion of the gas turbine combustor. The first flange portion has a plurality of radially outward protrusions arranged at intervals in the circumferential direction, and a plurality of first bolt holes penetrating the first flange portion in the axial direction. The first bolt holes are formed at the same circumferential positions as the protrusions, respectively.

Abstract: A combustor includes a combustion tube which has a tubular shape around an axis; a secondary fuel nozzle which is able to inject a secondary fuel in a radially inner direction with respect to the axis, inside the combustion tube; a fuel manifold which is disposed external to the combustion tube, and defines a fuel space which is able to temporarily store the secondary fuel; and a support which supports the fuel manifold with a gap extending radially from the combustion tube. The support has a support plate which is separated from the combustion tube by the gap and spreads in a circumferential direction with respect to the axis, and a support leg which is attached to the combustion tube and supports the support plate to define the gap between the support plate and the combustion tube.

Abstract: A combustor component of a combustor for combusting fuel to produce a combustion gas includes a combustion cylinder forming a passage for the combustion gas, a first acoustic device which internally includes a first cavity communicating with the passage via a first through hole formed in the combustion cylinder, a second acoustic device which is located on a radially outer side of the first acoustic device so as to cover the first acoustic device, and internally includes a second cavity communicating with the passage via a second through hole formed in the combustion cylinder, and a first communication passage causing the first cavity and an outer space of the combustion cylinder to communicate with each other without via the first through hole and the second cavity.

Abstract: A high-temperature part of the present disclosure includes: a high-temperature part body which includes a base and a coating layer formed on a part of a surface of the base; and a protective layer which is formed on at least a part of a surface of the coating layer. The protective layer is formed of a material which is allowed to disappear from a surface of the coating layer under an operation environment of a gas turbine.

Abstract: An outlet seal connects a combustor that combusts a fuel to generate combustion gas and a shroud for a stator. The outlet seal has a gas path surface, a first connection section, and a second connection section. The shape of the gas path surface in a cross section perpendicular to an axis is an arc centered on the axis. The first connection section is formed at a first side in an axial direction and is connected to the combustor. The second connection section is formed at a second side in the axial direction and is connected to the shroud. The gas path surface has an inclined surface that is inclined with respect to the axis in a cross section including the axis, such that the flow-path area of a combustion-gas flow path is reduced toward the second side.

Abstract: A fuel supply pipe assembly according to at least one embodiment of the present disclosure is a fuel supply pipe assembly for supplying fuel to a fuel nozzle provided on a side portion of a combustion liner of a gas turbine combustor, provided with: a fuel supply pipe for supplying the fuel to the fuel nozzle; a first flange portion capable of coupling with a flange portion of a fuel line for supplying the fuel to the fuel supply pipe; and a second flange portion capable of coupling with a top hat portion of the gas turbine combustor. The first flange portion has a plurality of radially outward protrusions arranged at intervals in the circumferential direction, and a plurality of first bolt holes penetrating the first flange portion in the axial direction. The first bolt holes are formed at the same circumferential positions as the protrusions, respectively.

Abstract: A combustor includes a combustion tube which has a tubular shape around an axis; a secondary fuel nozzle which is able to inject a secondary fuel toward a radially inner side with respect to the axis, inside the combustion tube; a fuel manifold which is disposed on an outer peripheral side of the combustion tube, and form a fuel space which is able to temporarily store the secondary fuel; and a support which supports the fuel manifold with a gap from the combustion cylinder in the radial direction. The support has a support plate which is separated from the combustion tube to the radially outer side and spreads in a circumferential direction with respect to the axis, and a support leg which is attached to the combustion tube and supports the support plate so that a space is formed between the support plate and the combustion tube.

Abstract: A combustor component of a combustor for combusting fuel to produce a combustion gas includes a combustion cylinder forming a passage for the combustion gas, a first acoustic device which internally includes a first cavity communicating with the passage via a first through hole formed in the combustion cylinder, a second acoustic device which is located on a radially outer side of the first acoustic device so as to cover the first acoustic device, and internally includes a second cavity communicating with the passage via a second through hole formed in the combustion cylinder, and a first communication passage causing the first cavity and an outer space of the combustion cylinder to communicate with each other without via the first through hole and the second cavity.

Abstract: An outlet seal connects a combustor that combusts a fuel to generate combustion gas and a shroud for a stator. The outlet seal has a gas path surface, a first connection section, and a second connection section. The shape of the gas path surface in a cross section perpendicular to an axis is an arc centered on the axis. The first connection section is formed at a first side in an axial direction and is connected to the combustor. The second connection section is formed at a second side in the axial direction and is connected to the shroud. The gas path surface has an inclined surface that is inclined with respect to the axis in a cross section including the axis, such that the flow-path area of a combustion-gas flow path is reduced toward the second side.

Abstract: A method of manufacturing a turbine blade includes forming a blade body divided body constituting a blade body of the turbine blade by a three-dimensional lamination method; individually forming a plurality of shroud divided bodies constituting a shroud of the turbine blade for each of the shroud divided bodies by a three-dimensional lamination method; joining the shroud divided bodies together; and joining the blade body divided body and the shroud divided bodies.

Abstract: There is provided an additive manufactured (AM) article formed of a Co based alloy having a composition comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 30% or less in total of Fe and Ni, the Fe being 5% or less; 5-12% in total of W and/or Mo; 0.5-2% in total of Ti, Zr, Nb and Ta; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The AM article comprises crystal grains with an average size of 10-100 ?m. In the crystal grains, segregation cells with an average size of 0.15-1.5 ?m are formed, in which components constituting an MC type carbide phase comprising the Ti, Zr, Nb and/or Ta are segregated in boundary regions of the cells, and/or grains of the MC type carbide phase are precipitated at an average intergrain distance of 0.15-1.5 ?m.

Abstract: There is provided an additive manufactured (AM) article formed of a Co based alloy having a composition comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 30% or less in total of Fe and Ni, the Fe being 5% or less; 5-12% in total of W and/or Mo; 0.5-2% in total of Ti, Zr, Nb and Ta; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The AM article comprises crystal grains with an average size of 10-100 ?m. In the crystal grains, segregation cells with an average size of 0.15-1.5 ?m are formed, in which components constituting an MC type carbide phase comprising the Ti, Zr, Nb and/or Ta are segregated in boundary regions of the cells, and/or grains of the MC type carbide phase are precipitated at an average intergrain distance of 0.15-1.5 ?m.

Abstract: A method of manufacturing a turbine blade includes forming a blade body divided body constituting a blade body of the turbine blade by a three-dimensional lamination method; individually forming a plurality of shroud divided bodies constituting a shroud of the turbine blade for each of the shroud divided bodies by a three-dimensional lamination method; joining the shroud divided bodies together; and joining the blade body divided body and the shroud divided bodies.

Abstract: There is provided an additive manufactured (AM) article formed of a Co based alloy having a composition comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 30% or less in total of Fe and Ni, the Fe being 5% or less; 5-12% in total of W and/or Mo; 0.5-2% in total of Ti, Zr, Nb and Ta; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The AM article comprises crystal grains with an average size of 10-100 ?m. In the crystal grains, segregation cells with an average size of 0.15-1.5 ?m are formed, in which components constituting an MC type carbide phase comprising the Ti, Zr, Nb and/or Ta are segregated in boundary regions of the cells, and/or grains of the MC type carbide phase are precipitated at an average intergrain distance of 0.15-1.5 ?m.

Abstract: There is provided an additive manufactured (AM) article formed of a Co based alloy having a composition comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 30% or less in total of Fe and Ni, the Fe being 5% or less; 5-12% in total of W and/or Mo; 0.5-2% in total of Ti, Zr, Nb and Ta; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The AM article comprises crystal grains with an average size of 10-100 ?m. In the crystal grains, segregation cells with an average size of 0.15-1.5 ?m are formed, in which components constituting an MC type carbide phase comprising the Ti, Zr, Nb and/or Ta are segregated in boundary regions of the cells, and/or grains of the MC type carbide phase are precipitated at an average intergrain distance of 0.15-1.5 ?m.

Abstract: There is provided an additive manufactured (AM) article formed of a Co based alloy having a composition comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 30% or less in total of Fe and Ni, the Fe being 5% or less; 5-12% in total of W and/or Mo; 0.5-2% in total of Ti, Zr, Nb and Ta; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The AM article comprises crystal grains with an average size of 10-100 ?m. In the crystal grains, segregation cells with an average size of 0.15-1.5 ?m are formed, in which components constituting an MC type carbide phase comprising the Ti, Zr, Nb and/or Ta are segregated in boundary regions of the cells, and/or grains of the MC type carbide phase are precipitated at an average intergrain distance of 0.15-1.5 ?m.

Abstract: There is provided an additive manufactured (AM) article formed of a Co based alloy having a composition comprising: in mass %, 0.08-0.25% C; 0.1% or less B; 10-30% Cr; 30% or less in total of Fe and Ni, the Fe being 5% or less; 5-12% in total of W and/or Mo; 0.5-2% in total of Ti, Zr, Nb and Ta; 0.5% or less Si; 0.5% or less Mn; 0.003-0.04% N; and the balance being Co and impurities. The AM article comprises crystal grains with an average size of 10-100 ?m. In the crystal grains, segregation cells with an average size of 0.15-1.5 ?m are formed, in which components constituting an MC type carbide phase comprising the Ti, Zr, Nb and/or Ta are segregated in boundary regions of the cells, and/or grains of the MC type carbide phase are precipitated at an average intergrain distance of 0.15-1.5 ?m.

Abstract: A combustor includes a first tube which supplies fuel and air from an opening formed in a distal end thereof, and a second tube which is configured such that flames are formed on an inner circumferential side thereof by the fuel and the air and the distal end of the first tube is inserted into an inner circumferential side of a proximal end thereof. The first tube includes a first tube main body and a ring part forming the distal end of the first tube. The ring part has a main body of a tubular shape and a plurality of protrusions that are integrally formed with the main body on an outer circumferential surface of the main body and protrude radially outward. When viewed in an axial direction, the outer circumferential surface of the main body has a polygonal cross-sectional shape within a range within which the protrusions are formed.

Abstract: A combustor includes a first tube which supplies fuel and air from an opening formed in a distal end thereof, and a second tube which is configured such that flames are formed on an inner circumferential side thereof by the fuel and the air and the distal end of the first tube is inserted into an inner circumferential side of a proximal end thereof. The first tube includes a first tube main body and a ring part forming the distal end of the first tube. The ring part has a main body of a tubular shape and a plurality of protrusions that are integrally formed with the main body on an outer circumferential surface of the main body and protrude radially outward. When viewed in an axial direction, the outer circumferential surface of the main body has a polygonal cross-sectional shape within a range within which the protrusions are formed.

Abstract: A cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79£DoutDin£0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.