Abstract: A tape cassette that includes a box-shaped cassette case whose outline being defined by a bottom wall, a top wall, and a side wall and including a plurality of corner portions, at least one tape contained within a tape containment area defined within the outline, a pair of cavities extending from the bottom wall and being provided between the tape containment area and the outline at opposite ends of a diagonal line connecting one of the corner portions to another of the corner portions, and a side face indicator portion provided in the side wall, indicating a type of the tape, and including a plurality of indicator portions disposed in a pattern in accordance with the type of the tape, each of the indicator portions being one of a switch hole and a surface portion.

Abstract: A tape cassette that includes a tape cassette that includes a housing having a top surface, a bottom surface, a rear wall, a front wall, and a tape feed exit located on the front wall, a tape included at least partially within the housing and configured to be fed along a tape feed path extending to the tape feed exit, and a first indicator aperture positioned on the front wall and a second indicator aperture position on a rear portion of the bottom surface. A position of the first indicator aperture on the front wall indicates a type of the tape included within the housing. A position of the second indicator aperture indicates a color of characters.

Abstract: A tape cassette that includes a box-shaped cassette case whose outline being defined by a bottom wall, a top wall, and a side wall and including a plurality of corner portions, at least one tape contained within a tape containment area defined within the outline, a pair of cavities extending from the bottom wall and being provided between the tape containment area and the outline at opposite ends of a diagonal line connecting one of the corner portions to another of the corner portions, and a side face indicator portion provided in the side wall, indicating a type of the tape, and including a plurality of indicator portions disposed in a pattern in accordance with the type of the tape, each of the indicator portions being one of a switch hole and a surface portion.

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 gas turbine nozzle has nozzles formed integrally through an inner endwall and an outer endwall. The inner endwall has an upstream connection portion, a downstream connection portion, and an inner endwall body. The upstream connection portion extends radially inward and is connected to the inner turbine diaphragm. The downstream connection portion is located downstream from the upstream connection portion, extends radially inward, and is connected to the inner turbine diaphragm. The inner endwall body extends from upstream toward downstream and the upstream connection portion and the downstream connection portion are formed on the inner endwall body. The inner endwall body has a digging area that is dug radially outward in a position between the upstream connection portion and the downstream connection portion, and an impingement cooling plate is installed on a surface of the digging area.

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: A reduction gear W1 that is configured to reduce a rotation speed input to an input shaft 1, and output the reduced rotation speed from an output shaft, the reduction gear including: an inner trochoid 8 that has a wavy curved surface formed on an inner circumferential side surface thereof; an inner trochoid holder 9 that is designed to hold the inner trochoid 8; an outer trochoid 3 that has a wavy curved surface formed on an outer circumferential side surface thereof; a rotation restriction unit that is designed to restrict rotation of the outer trochoid 3 around an axis thereof; and an output pin 9 that is pinched between the outer circumferential side surface of the outer trochoid 3 and the inner circumferential side surface of the inner trochoid 8.

Abstract: A monitoring camera system includes a camera and a master device communicating with the camera and a mobile communication terminal having a display. The camera detects movement of a person at a first timing in an imaging area and transmits a predetermined notification to the master device at a second timing. The master device transmits an image request for requesting a first captured image captured at the first timing and a second captured image captured at the second timing to the camera, based on the predetermined notification from the camera. The camera transmits the first captured image and the second captured image in association with each other to the master device based on the image request transmitted from the master device. The master device transmits the first captured image and the second captured image in association with each other to the mobile communication terminal to be displayed on the display.

Abstract: In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.

Abstract: A monitoring camera system includes a camera and a master device capable of communicating with the camera and a mobile communication terminal having a display. The camera detects movement of a person at a first timing in an imaging area and transmits a predetermined notification to the master device at a second timing. The master device transmits an image request for requesting a first captured image captured at the first timing and a second captured image captured at the second timing from the camera, to the camera, based on the predetermined notification from the camera. The camera transmits the first captured image and the second captured image in association with each other to the master device based on the image request transmitted from the master device. The master device transmits the first captured image and the second captured image in association with each other to the mobile communication terminal so as to be displayed on the display.

Abstract: The invention provides a gas turbine blade that is capable of reducing the temperature difference between the pressure side and the suction side even if the trailing-edge cooling channel is narrow, thereby lessening thermal stress as well. A gas turbine blade 1 comprises: an internal trailing-edge cooling channel formed by a suction-side cooling target surface 6a and a pressure-side cooling target surface 6b that face each other; and multiple vortex-generator-shaped fins 10 disposed between the two cooling target surfaces 6a and 6b such that the fins 10 connect the two cooling target surfaces 6a and 6b. Each of the vortex-generator-shaped fins 10 includes an oblique surface 33 located on the downstream side of the flow direction of a cooling medium. A normal line 34 to the oblique surface 33 intersects with one of the two cooling target surfaces 6a and 6b.

Abstract: In a gas turbine in which a seal member seals a gap between a transition piece and a nozzle end wall in a turbine first stage, the transition piece and the nozzle end wall has a seal groove. The seal member includes a hook portion that slides in the turbine radial direction with respect to the flange and a seal plate portion inserted in the groove. The groove and the portion are configured to include a surface contact region in which a surface of the groove and the portion are in surface contact with each other, a non-contact region disposed on a side closer to the transition piece than the region, and a hole provided at the portion so as to face the surface in the groove across a gap in the region.

Abstract: A screw hole which is formed on one end of a substrate and through which an electronic device is attached to a metal frame by using a metal screw provided, an NAND memory as a heating section is provided on the screw hole side, a heat conducting sheet which covers an upper peripheral portion of the screw hole and an upper portion of the NAND memory is provided, and heat of the NAND memory is conducted to the metal frame through the heat conducting sheet and the metal screw fitted into the screw hole.

Abstract: A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion having a cooling passage therein; and an end wall portion located at an inner band end portion of the airfoil portion in the turbine-radial direction. Cooling holes are disposed in the leading edge side hook portion of the end wall portion. The plurality of cooling holes are arranged at different distance of intervals in the circumferential direction of the gas turbine. Cooling air that has flowed in the cooling passage is configured to flow from the cooling holes toward the leading edge of the end wall portion.

Abstract: A gas turbine blade includes a hollow-blade-form portion formed by a leading edge on an upstream side of an working fluid of a gas turbine in a flow direction, a trailing edge on a downstream side of the working fluid in the flow direction, and a suction surface and a pressure surface reaching the trailing edge from the leading edge, and a shank portion for supporting the blade form portion. The blade also includes a partition for connecting the suction surface and the pressure surface in a hollow region of the blade-form portion, coolant paths formed by the partition, the suction surface, and the pressure surface, an impingement cooling hole formed in the partition for dividing the first path that is a flow path nearest to the leading edge side among the coolant paths and the second path adjacent to the first path, and first and second converter portions.

Abstract: A computer implemented method resumes a computer from a power-saving state in a short time. Prior to shifting to a power-saving state, a drive sets a status flag indicating a loading state of a disk at a flash memory. For resumption from the power-saving state, the BIOS requests a ready notification from the drive. When it is determined that the status flag indicates not-loading of a disk, the drive skips the detection processing of the disk including initialization of a read/write circuit and a servo mechanism such as a spindle motor and sends a ready notification indicating not-loading of the disk to the BIOS. Receiving the ready notification, the BIOS can continue the resume processing.

Abstract: There is provided a shroud structure for gas turbines capable of suppressing a drop in the amount of cooling air for cooling the inner shroud by reducing the amount of cooling air leakage that occurs along the cooling air path when feeding cooling air from the one-piece outer shroud to the inner shroud of the gas turbine and ensure more reliable cooling of the inner shroud. The gas turbine shroud structure contains a one-piece outer shroud, and an inner shroud retained on the inner circumferential side of the outer shroud in a structure divided into multiple inner shrouds along the periphery. An inner seal plate groove is formed on the outer circumference of the hook formed on the inner shroud, a seal plate is inserted in the inner seal plate groove, and the seal plate is mounted so that a section of the seal plate protrudes in the gap between the hook mechanism of the outer shroud and the inner shroud.

Abstract: The invention provides a gas turbine blade that is capable of reducing the temperature difference between the pressure side and the suction side even if the trailing-edge cooling channel is narrow, thereby lessening thermal stress as well. A gas turbine blade 1 comprises: an internal trailing-edge cooling channel formed by a suction-side cooling target surface 6a and a pressure-side cooling target surface 6b that face each other; and multiple vortex-generator-shaped fins 10 disposed between the two cooling target surfaces 6a and 6b such that the fins 10 connect the two cooling target surfaces 6a and 6b. Each of the vortex-generator-shaped fins 10 includes an oblique surface 33 located on the downstream side of the flow direction of a cooling medium. A normal line 34 to the oblique surface 33 intersects with one of the two cooling target surfaces 6a and 6b.

Abstract: A gas turbine airfoil is provided that is superior in the cooling performance of an end wall and in the thermal efficiency of a gas turbine. A gas turbine airfoil includes an airfoil portion having a cooling passage therein; and an end wall portion located at an inner band end portion of the airfoil portion in the turbine-radial direction. Cooling holes are disposed in the leading edge side hook portion of the end wall portion. The plurality of cooling holes are arranged at different distance of intervals in the circumferential direction of the gas turbine. Cooling air that has flowed in the cooling passage is configured to flow from the cooling holes toward the leading edge of the end wall portion.

Abstract: A computer implemented method resumes a computer from a power-saving state in a short time. Prior to shifting to a power-saving state, a drive sets a status flag indicating a loading state of a disk at a flash memory. For resumption from the power-saving state, the BIOS requests a ready notification from the drive. When it is determined that the status flag indicates not-loading of a disk, the drive skips the detection processing of the disk including initialization of a read/write circuit and a servo mechanism such as a spindle motor and sends a ready notification indicating not-loading of the disk to the BIOS. Receiving the ready notification, the BIOS can continue the resume processing.