Abstract: In order to reduce driving power of an engine cooling system in which a cooling fan for cooling a radiator and a water pump are driven by a motor, according to the invention, a pump motor of the water pump 5 which circulates liquid coolant is used as a drive source of the cooling fan. An electromagnetic clutch is provided between the pump motor and the cooling fan, and when the liquid coolant exiting from an engine is at a predetermined temperature or higher, the electromagnetic clutch is brought into a connected state, whereas when the liquid coolant is at a temperature lower than the predetermined temperature, the electromagnetic clutch is brought into a disconnected state. When the liquid coolant is at a temperature lower than the predetermined temperature, and the vehicle speed is at a predetermined speed or higher, the electromagnetic clutch is brought into a connected state, and a rotational force of the cooling fan receiving driving wind is transmitted to the pump motor to reduce its load.

Abstract: The invention provides a gas turbine combustor in which the size of a combustor outer casing can be reduced. A transition inner duct and a transition outer duct are disposed in a main housing, inlet openings for a fluid to cool the transition inner duct are formed at ends of the transition outer duct on both sides nearer to the combustor liner and the turbine, and the transition outer duct is formed as an extraction flow passage for extracting the cooling fluid having flown in through the inlet openings to a recuperator. A partition member is also provided to prevent the fluid in the main housing and the fluid in the combustor outer casing from mixing with each other.

Abstract: A multi-lobe foil gas bearing which can accomplish high accuracy rotation by means of a stable fluid lubricating film without being affected by a rotational position or a driving system of a journal at the time of starting is provided. Since two foils are arranged with different phases in a circumferential direction so that each vertex part of one of the two foils is positioned in an arc surface part of the other foil in a plan view seen from a shaft end of the journal, a part having low rigidity and a part having high rigidity of the multi-lobe foil gas bearing compensate each other to eliminate a local part having low bearing rigidity. As a result, it is possible to eliminate a phenomenon such as moving or leaning of the journal at the time of starting, while the fluid lubricating film can exist over the entire circumferential surface of the journal to keep stable high accuracy rotation of the journal.

Abstract: A multi-lobe bearing is of simple construction such that a foil sheet in the form of a closed loop is arranged on a journal shaft by joining both ends of two sheets together, with a bearing gap therebetween and filling a viscoelastic body in an air gap between the foil sheet and an inside of a bearing holding member, whereby the bearing gap between the journal shaft and the foil sheet is configured to be liable to generate a fluid pressure. Also, the bearing is simply constructed to be made easy in assembly, and in particular, appropriate in bearing the journal shaft having a small diameter.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: A multi-lobe bearing is of simple construction such that a foil sheet in the form of a closed loop is arranged on a journal shaft by joining both ends of two sheets together, with a bearing gap therebetween and filling a viscoelastic body in an air gap between the foil sheet and an inside of a bearing holding member, whereby the bearing gap between the journal shaft and the foil sheet is configured to be liable to generate a fluid pressure. Also, the bearing is simply constructed to be made easy in assembly, and in particular, appropriate in bearing the journal shaft having a small diameter.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: The invention provides a gas turbine combustor in which the size of a combustor outer casing can be reduced. A transition inner duct and a transition outer duct are disposed in a main housing, inlet openings for a fluid to cool the transition inner duct are formed at ends of the transition outer duct on both sides nearer to the combustor liner and the turbine, and the transition outer duct is formed as an extraction flow passage for extracting the cooling fluid having flown in through the inlet openings to a recuperator. A partition member is also provided to prevent the fluid in the main housing and the fluid in the combustor outer casing from mixing with each other.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: A gas turbine has a rotor shaft which includes a plurality of discs, each having a plurality of moving blades driven by combustion gas and arranged annularly on the peripheral portion and having spaces arranged between the discs. The respective discs and spacers are arranged in the axial direction. Gap portions are formed between the rotor axis side regions of the discs facing the spacers and adjacent spacers. Contact surfaces contacting each other on both rotor peripheral side regions of the discs facing the spaces and adjacent spacers are formed. A first flow path for supplying a coolant into the moving blades and a second flow path for recovering the coolant heated by the moving blades from the moving blade are provided. A third flow path for introducing fluid into the gap portions is formed in the discs with the third flow path being independent from the first and second flow paths.

Abstract: Operational reliability of a gas turbine is improved by suppressing the thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs. Gap portions are formed between a region on the rotor shaft center portion side of the discs facing the spacers and spacers adjacent thereof. Contact surfaces are formed which contact on both a region on the rotor peripheral side of the discs facing the spacers and adjacent spacers thereto. Furthermore, a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: A high efficiency coolant collection type gas turbine is obtained by forming coolant supply and collection flow paths for moving blades in a more outer peripheral side of a gas turbine rotor than a hub, supplying the coolant supplied from a shaft end into the moving blades through the supply flow path, collecting the coolant after cooling into a combustion chamber side, supplying air extracted from a compressor to cool moving blades of a downstream side stage or a rotor outer wall through slits formed from a turbine rotor central portion to the hub, reducing rotor thermal stress and a pressure loss of the coolant flow paths and cooling a high stage side of a compressor rotor.

Abstract: A gas turbine combustor has a premixing burner for jetting out a premixed gas of fuel and air. A stabilizer forms a circulation of combustion gas generated by combustion of the premixed gas at the downstream side of the stabilizer to stabilize flame formed by the combustion of the premixed gas. Before the operation of the combustor, a relationship between a temperature of the stabilizer and combustion conditions of the premixed gas is checked. Thereafter during operation of the combustor, the temperature of the stabilizer is measured during combustion and the combustion conditions are checked according to only the measured temperature of the stabilizer and the aforesaid relationship. The stabilizer has a heat receiving surface at the most downstream side thereof. The temperature of a portion of the stabilizer around the heat receiving surfaces measured to allow an accurate assessment of the combustion conditions.