Abstract: A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

Abstract: In a turbine designing and manufacturing method attendant on a material change of a rotor disk of a turbine rotor, a temperature rise time ratio is determined which is a desired ratio of a temperature rise time of the temperature of the rotor disk from a first temperature to a second temperature after the material change to the temperature rise time before the material change. An inter-surface distance between surfaces on upstream and downstream sides of the rotor disk after the material change is determined, and a shape of the rotor disk after the material change is determined based on the inter-surface distance. The turbine is designed based on the determined shape of the rotor disk. After the material change in the shape determined in the designing process, the rotor disk and the turbine are manufactured based on the result of the designing process.

Abstract: A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

Abstract: The present invention provides a gas turbine nozzle capable of reducing stress related to thermal elongation caused by a rise in gas turbine nozzle temperature and thus reducing stress produced when thermal deformation occurs in the gas turbine nozzle. The gas turbine nozzle according to the present invention includes nozzles formed integrally through an inner perimeter end wall and an outer perimeter end wall. The inner perimeter end wall has an upstream connection portion and a downstream connection portion. The upstream connection portion extends radially inward to be connected to an inner perimeter diaphragm. The downstream connection portion is located downstream from the upstream connection portion and extends radially inward to be connected to the inner perimeter diaphragm.

Abstract: The present invention reduces the concentration of thermal stress on a burner. A gas turbine combustor receiving compressed air from a compressor, mixing the compressed air with a fuel, burning the mixture to generate a combustion gas, and supplying the combustion gas to a turbine. The combustor includes: an inner cylinder internally forming a combustion chamber; an outer cylinder covering the inner cylinder and forming a cylindrical outer circumferential flow path between the inner and outer cylinders to allow the compressed air to flow; and a burner mounted on an end of the outer cylinder, which is positioned on an opposite side to a turbine side, and facing the combustion chamber. The burner includes a cylindrical base frame including a cavity distributing the fuel, and fuel nozzles circularly arranged as viewed from the combustion chamber and connected to the cavity.

Abstract: In a turbine designing method attendant on a material change of a rotor disk of a turbine rotor, let a time require for a temperature of the rotor disk to reach from a first temperature to a second temperature at the time of starting of a turbine be temperature rise time, and let a distance between surfaces on an upstream side and a downstream side of the rotor disk be inter-surface distance, then the turbine designing method includes: determining a temperature rise time ratio that is a desired ratio of the temperature rise time after the material change to the temperature rise time before the material change, determining the inter-surface distance after the material change on the basis of the determined temperature rise time, determining a shape of the rotor disk after the material change on the basis of the determined inter-surface distance, and designing the turbine while reflecting the determined shape of the rotor disk on the turbine rotor.

Abstract: The present invention provides a gas turbine nozzle capable of reducing stress related to thermal elongation caused by a rise in gas turbine nozzle temperature and thus reducing stress produced when thermal deformation occurs in the gas turbine nozzle. The gas turbine nozzle according to the present invention includes nozzles formed integrally through an inner perimeter end wall and an outer perimeter end wall. The inner perimeter end wall has an upstream connection portion and a downstream connection portion. The upstream connection portion extends radially inward to be connected to an inner perimeter diaphragm. The downstream connection portion is located downstream from the upstream connection portion and extends radially inward to be connected to the inner perimeter diaphragm.

Abstract: Provided is a two-shaft gas turbine power generation equipment that includes: an induction motor which receives/transmits power from/to a power system; and a speed reducer that makes a rotational speed of a motor rotor of the induction motor lower than a rotational speed of a compressor rotor of a two-shaft gas turbine. The speed reducer includes: a compressor-side shaft; a motor-side shaft; a first compressor-side helical gear and a second compressor-side helical gear which are mounted on the compressor-side shaft; and a first motor-side helical gear and a second motor-side helical gear which are mounted on the motor-side shaft. The first compressor-side helical gear meshes with the first motor-side helical gear, and the second compressor-side helical gear meshes with the second motor-side helical gear.

Abstract: The present invention reduces thermal stress that is applied to the weld zone of a cavity formed in the structural material of a burner. The burner includes the cavity distributing a fuel to fuel nozzles. The cavity is demarcated by a groove formed in the structural material of the burner so as to create a level difference at an opening, and a cover fitted into the level difference to close the groove. The cover is formed by a web covering the opening in the groove and a flange extending in the depth direction of the groove to be fitted into the level difference, and is joined by welding to the structural material in such a manner as to have an L-shaped cross-section. When viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange forming a lateral surface of the cavity is flush with a groove-side inner surface that is an inner surface of the groove forming a lateral surface of the cavity.

Abstract: The present invention reduces thermal stress that is applied to the weld zone of a cavity formed in the structural material of a burner. The burner includes the cavity distributing a fuel to fuel nozzles. The cavity is demarcated by a groove formed in the structural material of the burner so as to create a level difference at an opening, and a cover fitted into the level difference to close the groove. The cover is formed by a web covering the opening in the groove and a flange extending in the depth direction of the groove to be fitted into the level difference, and is joined by welding to the structural material in such a manner as to have an L-shaped cross-section. When viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange forming a lateral surface of the cavity is flush with a groove-side inner surface that is an inner surface of the groove forming a lateral surface of the cavity.

Abstract: The present invention reduces the concentration of thermal stress on a burner. A gas turbine combustor receiving compressed air from a compressor, mixing the compressed air with a fuel, burning the mixture to generate a combustion gas, and supplying the combustion gas to a turbine. The combustor includes: an inner cylinder internally forming a combustion chamber; an outer cylinder covering the inner cylinder and forming a cylindrical outer circumferential flow path between the inner and outer cylinders to allow the compressed air to flow; and a burner mounted on an end of the outer cylinder, which is positioned on an opposite side to a turbine side, and facing the combustion chamber. The burner includes a cylindrical base frame including a cavity distributing the fuel, and fuel nozzles circularly arranged as viewed from the combustion chamber and connected to the cavity.

Abstract: Provided is a two-shaft gas turbine power generation equipment that includes: an induction motor which receives/transmits power from/to a power system; and a speed reducer that makes a rotational speed of a motor rotor of the induction motor lower than a rotational speed of a compressor rotor of a two-shaft gas turbine. The speed reducer includes: a compressor-side shaft; a motor-side shaft; a first compressor-side helical gear and a second compressor-side helical gear which are mounted on the compressor-side shaft; and a first motor-side helical gear and a second motor-side helical gear which are mounted on the motor-side shaft. The first compressor-side helical gear meshes with the first motor-side helical gear, and the second compressor-side helical gear meshes with the second motor-side helical gear.

Abstract: An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200.

Abstract: A regenerative gas turbine combustor is provided that enable to reduce an amount of leakage of compressed air before preheating to compressed air after the preheating. The regenerative gas turbine combustor is such that a compressed air passage between a combustor inner cylinder 10 and a tail cylinder 12, and a combustor outer cylinder 7 is blocked by a division wall 15 at a position between a bleeding port 13 and an injection port 14, and compressed air is preheated in a regenerator 4 and then the compressed air thus preheated is burnt together with fuel. This combustor includes seal rings 17a-17c, a holder 16 installed on the inner circumferential portion of the division wall 15 and having ring grooves 25a-25c for holding the respective seal rings 17a-17c, and gaps 20 provided between the inner circumferential surfaces of the ring grooves 25a-25c and the outer circumferential surfaces of the seal rings 17a-17c.

Abstract: An axial-flow compressor with variable stator vanes located at a single stage can be modified by adding variable stator vanes to the axial-flow compressor so that the variable stator vanes are located at a plurality of stages. The axial-flow compressor includes stator vane rows located at the plurality of stages and include the variable stator vanes extending in a radial direction of the axial-flow compressor and rotating around rotary shafts of the variable stator vanes so as to adjust angles of the variable stator vanes; a plurality of rings are connected to the stator vane rows and drive and rotate the variable stator vanes of the stator vane rows that correspond to respective rings; a plurality of levers that correspond to the plurality of rings; a rotary shaft that holds the plurality of levers so as to enable the levers to pivot.

Abstract: Disclosed is a gas turbine and a gas turbine power facility which flexibly accommodate changes in layout of devices and in user's needs. This invention includes an air compressor 1; a turbine 2 coaxially coupled to the compressor 1; a turbine casing 4 accommodating the compressor 1 and the turbine 2; a compressor output shaft 23 for coupling rotary devices including a power generator 200, the compressor output shaft 22 protruding from the turbine casing 4 towards the compressor 1; and a turbine output shaft 23 for coupling the rotary devices, the turbine output shaft 23 protruding from the turbine casing 4 towards the turbine 2.

Abstract: It is an object of the present invention to provide a compressor that has a simple structure, produces a damping effect and improves aerodynamic performance. In a compressor including stator blades 4 circumferentially mounted to an inner circumferential surface side of a casing 6 forming a annular path; and an inner barrel 7 supported by the casing and arranged on the radially inside of the stator blade as a partition wall on the radial side of the annular path; the stator blade includes an outer shroud 10 mounted to an inner circumferential surface of the casing at a position facing the inner barrel, and an inner shroud 11 supporting a blade portion at an inner diameter side, the inner shroud being disposed in an annular groove formed in an outer circumferential surface of the inner barrel facing the inner shroud. The stator blade including the outer shroud 10, the inner shroud 11 and the blade portions 9 are formed in a monolithic structure by milling.

Abstract: An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200.

Abstract: A regenerative gas turbine combustor is provided that enable to reduce an amount of leakage of compressed air before preheating to compressed air after the preheating. The regenerative gas turbine combustor is such that a compressed air passage between a combustor inner cylinder 10 and a tail cylinder 12, and a combustor outer cylinder 7 is blocked by a division wall 15 at a position between a bleeding port 13 and an injection port 14, and compressed air is preheated in a regenerator 4 and then the compressed air thus preheated is burnt together with fuel. This combustor includes seal rings 17a-17c, a holder 16 installed on the inner circumferential portion of the division wall 15 and having ring grooves 25a-25c for holding the respective seal rings 17a-17c, and gaps 20 provided between the inner circumferential surfaces of the ring grooves 25a-25c and the outer circumferential surfaces of the seal rings 17a-17c.

Abstract: Disclosed is a gas turbine and a gas turbine power facility which flexibly accommodate changes in layout of devices and in user's needs. This invention includes an air compressor 1; a turbine 2 coaxially coupled to the compressor 1; a turbine casing 4 accommodating the compressor 1 and the turbine 2; a compressor output shaft 23 for coupling rotary devices including a power generator 200, the compressor output shaft 22 protruding from the turbine casing 4 towards the compressor 1; and a turbine output shaft 23 for coupling the rotary devices, the turbine output shaft 23 protruding from the turbine casing 4 towards the turbine 2.