Abstract: A fuel cell module includes a container and a plurality of cell members radially arranged inside the container. Inside the container, a first fluid flow path through which a first fluid that exchanges heat with an inner portion of the plurality of cell members flows is formed, and a second fluid flow path through which a second fluid that exchanges heat with an outer portion of the plurality of cell members flows is formed. A first heat exchange portion that forms the first fluid flow path and exchanges heat with the cell member has a smaller heat transfer area with the cell member than a second heat exchange portion that forms the second fluid flow path and exchanges heat with the cell member. The first fluid having a larger temperature difference with the cell member than the second fluid flows in the first fluid flow path.

Abstract: A load adjustment method, comprising: a step of acquiring a warm-up parameter indicating the degree of warm-up of a gas turbine during operation under load; a step of determining an upper limit of a load increase rate in accordance with the warm-up parameter; and a step of increasing the load of the gas turbine at or below the upper limit of the load increase rate.

Abstract: Such a rotating blade body is supplied as can prevent not only local wear and deformation but also inadvertent vibration and can maintain cooling efficiency. A rotating blade body consists of a rotor disc 2 and rotating blades 1 which are assembled so as to extend from the outer circumference of the rotor disc 2 in a radial pattern, wherein blade root portions 10 of the rotating blades 1 are engaged into blade grooves 20 which are formed along a direction of a rotating shaft on an edge of the outer circumference of the rotor disc 2. Circulation spaces 25 for the cooling air are formed along the direction of a rotating shaft between the bottom-end portions 10a of the blade root portions 10 and the bottom portions 20a of the blade grooves 20. Pushing-up members 3 which push up the rotating blades 1 outward in a radial direction are inserted into the circulation spaces 25, maintaining circulation of the cooling air.

Abstract: Such a rotating blade body is supplied as can prevent not only local wear and deformation but also inadvertent vibration and can maintain cooling efficiency. A rotating blade body consists of a rotor disc 2 and rotating blades 1 which are assembled so as to extend from the outer circumference of the rotor disc 2 in a radial pattern, wherein blade root portions 10 of the rotating blades 1 are engaged into blade grooves 20 which are formed along a direction of a rotating shaft on an edge of the outer circumference of the rotor disc 2. Circulation spaces 25 for the cooling air are formed along the direction of a rotating shaft between the bottom-end portions 10a of the blade root portions 10 and the bottom portions 20a of the blade grooves 20. Pushing-up members 3 which push up the rotating blades 1 outward in a radial direction are inserted into the circulation spaces 25, maintaining circulation of the cooling air.

Abstract: The present invention provides a cast steel for ring-shaped components that has a low average coefficient of thermal expansion in a temperature range of 20° C. to 500° C. and high strength and good oxidation resistance at 500° C., which are required for ring-shaped components for use as blade rings and seal ring retainers of gas turbines, and that can hence be used for blade rings and seal ring retainers of gas turbines. Specifically, the present invention provides a high-strength and low-thermal expansion cast steel comprising, on a mass percentage basis, 0.1 to 0.8% of C, 0.1 to 1.0% of Si, 0.1 to 1.0% of Mn, 0.01 to 0.1% of S, greater than 40% and up to 50% of Ni, not greater than 4% (inclusive of 0%) of Co, greater than 1.5% and up to 4% of Cr, 0.01 to 0.1% of Al, and 0.001 to 0.1% of Mg, the remainder being substantially Fe.

Abstract: The present invention provides a cast steel for ring-shaped components that has a low average coefficient of thermal expansion in a temperature range of 20° C. to 500° C. and high strength and good oxidation resistance at 500° C., which are required for ring-shaped components for use as blade rings and seal ring retainers of gas turbines, and that can hence be used for blade rings and seal ring retainers of gas turbines. Specifically, the present invention provides a high-strength and low-thermal expansion cast steel comprising, on a mass percentage basis, 0.1 to 0.8% of C, 0.1 to 1.0% of Si, 0.1 to 1.0% of Mn, 0.01 to 0.1% of S, greater than 40% and up to 50% of Ni, not greater than 4% (inclusive of 0%) of Co, greater than 1.5% and up to 4% of Cr, 0.01 to 0.1% of Al, and 0.001 to 0.1% of Mg, the remainder being substantially Fe.

Abstract: A gas turbine blade ring is cooled by steam whose temperature, pressure and flow rate are controlled so that a clearance between a moving blade tip and blade ring is maintained appropriately. Steam from a steam turbine bottoming cycle (10) flows into a blade ring cooling passage (8) of a gas turbine (1) via piping (12) for cooling the blade ring. The steam, having cooled the blade ring, is supplied into a transition piece cooling passage (9) of a combustor (3) for cooling the transition piece, and is then recovered into the steam turbine bottoming cycle (10) via piping (14). While the steam cools the blade ring, the temperature, pressure and flow rate of the steam are controlled so that thermal elongation of the blade ring is adjusted and the clearance at the moving blade tip is controlled so as to approach a target value. Thus, the clearance is maintained as small as possible in operation and the gas turbine performance is enhanced.

Abstract: A method for generating an electronic assembly procedure manual and an electronic assembly procedure manual system have a recording means for recording drawing data regarding a two-dimensional drawing (610) showing an object in a partially or totally assembled condition and animation data regarding an animation showing the process of assembling an object partially or totally, a screen image (500) that displays a prescribed two-dimensional drawing (610) based on drawing data, and displays an animation icon (820) identifying an animation corresponding to the two-dimensional drawing (610) at a prescribed position on the two dimensional drawing (610), and a playback means for playing back an animation based on animation data when an operation such as clicking is done with respect to a displayed animation icon.

Abstract: Gas turbine combustor by-pass valve device for opening and closing a by-pass valve is improved to uniformly control air supply into a combustion area for appropriate combustion. A drive shaft 21 for opening and closing a driven by-pass valve 20 is provided in turbine casing 010 where an outside obstruction is located which would interfere with a projecting drive shaft 09. The driven shaft 21 has a short length to be provided in the turbine casing 010. An adjacent main driving shaft 23 for opening and closing main driving by-pass valve 22 is provided adjacent to the driven shaft 21. Link mechanism 26 is provided between the adjacent main driving shaft 23 and the driven shaft 21 so that rotary movement of adjacent main driving shaft 23 driven by outside drive means via the drive shaft 09 is transmitted to the driven shaft 21 and, thus, to the driven by-pass valve 20.

Abstract: Gas turbine blade ring is cooled by steam of which temperature, pressure and flow rate are controlled so that clearance between moving blade tip and blade ring is maintained appropriately. Steam from steam turbine bottoming cycle (10) flows into blade ring cooling passage (8) of gas turbine (1) via piping (12) for cooling blade ring. The steam having cooled the blade ring is supplied into transition piece cooling passage (9) of combustor (3) for cooling transition piece and is then recovered into the steam turbine bottoming cycle (10) via piping (14). While the steam cools the blade ring, temperature, pressure and flow rate of the steam are controlled so that thermal elongation of the blade ring is adjusted and the clearance at the moving blade tip is controlled so as to approach target value. Thus, the clearance is maintained as small as possible in operation and gas turbine performance is enhanced.

Abstract: Gas turbine combustor by-pass valve device for opening and closing by-pass valve is improved to control uniformly air supply into combustion area for appropriate combustion. Drive shaft 21 for opening and closing driven by-pass valve 20 is provided in turbine casing 010 where outside obstruction is located to interfere with projecting drive shaft 09. The driven shaft 21 is made in short length to be provided in the turbine casing 010. Adjacent main driving shaft 23 for opening and closing main driving by-pass valve 22 is provided adjacently to the driven shaft 21. Link mechanism 26 is provided between the adjacent main driving shaft 23 and the driven shaft 21, thereby rotary movement of adjacent main driving shaft 23 driven by outside drive means via the drive shaft 09 is transmitted to the driven shaft 21 and thus to the driven by-pass valve 20.

Abstract: Gas turbine combustor by-pass valve device for opening and closing a by-pass valve is improved to uniformly control air supply into a combustion area for appropriate combustion. A drive shaft 21 for opening and closing a driven by-pass valve 20 is provided in turbine casing 010 where an outside obstruction is located which would interfere with a projecting drive shaft 09. The driven shaft 21 has a short length to be provided in the turbine casing 010. An adjacent main driving shaft 23 for opening and closing main driving by-pass valve 22 is provided adjacent to the driven shaft 21. Link mechanism 26 is provided between the adjacent main driving shaft 23 and the driven shaft 21 so that rotary movement of adjacent main driving shaft 23 driven by outside drive means via the drive shaft 09 is transmitted to the driven shaft 21 and, thus, to the driven by-pass valve 20.