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| Number | Title | Issue Date |
| 6973790 | Gas turbine combustor, gas turbine, and jet engine For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the cylinder an... | 12/13/2005 |
| 6860098 | Gas turbine combustor having bypass and annular gas passage for reducing uneven temperature distribution in combustor tail cross section There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through th... | 03/01/2005 |
| 6837051 | Gas turbine combustor A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume,... | 01/04/2005 |
| 6837050 | Gas turbine combustor A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume,... | 01/04/2005 |
| 6640544 | Gas turbine combustor, gas turbine, and jet engine For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the ... | 11/04/2003 |
| 6481967 | Gas turbine moving blade A gas turbine moving blade is provided which prevents occurrence of cracks caused by thermal stresses due to temperature differences between a blade and a platform while the gas turbine is being stopped. During steady operation time of the moving blade, c... | 11/19/2002 |
| 6442927 | Gas turbine for combined cycle power plant A combined cycle power plant has a gas turbine and an exhaust heat recovery boiler to which exhaust gas from the gas turbine is supplied. The exhaust heat recovery boiler is configured to generate steam for cooling. The combined cycle power plant has seve... | 09/03/2002 |
| 6419447 | Gas turbine equipment and turbine blade Turbine blade of gas turbine etc. and gas turbine equipment using the turbine blade suppress occurrence of thermal stress caused by temperature difference and provide high reliability. In gas turbine equipment comprising rotational portion of rotor (1) an... | 07/16/2002 |
| 6315518 | Stationary blade of gas turbine In a stationary blade of a gas turbine, the pressure resisting strength can be decreased by using low-pressure cooling air, and effective cooling can be performed by means of a simple construction. An inside shroud 1 and an outside shroud 2 are cooled by ... | 11/13/2001 |
| 6290462 | Gas turbine cooled blade A gas turbine cooled blade is constructed without an increase in the number of parts or time requirements, in which seal air is maintained at a lower temperature with the heat exchange rate being suppressed, and the heat transfer rate of the cooling mediu... | 09/18/2001 |
| 6264426 | Gas turbine stationary blade In cooling a gas turbine stationary blade, steam and air are used as cooling media, the steam is recovered surely without leakage and used effectively, and the amount of air required for cooling is decreased to provide a margin for combustion air, by whic... | 07/24/2001 |
| 6253537 | Revolution speed control method in gas turbine shutdown process Stress occurring in a moving blade in a gas turbine stopping process is decreased. Time t1 is load decrease start or fuel throttling start, time t2 is no load operation start, time t3 is fuel shut-off and time t4 | 07/03/2001 |
| 6254346 | Gas turbine cooling moving blade The present invention relates to a gas turbine cooling moving blade and is applied to a large-sized blade for a high temperature so as to reduce its thickness and increase cooling efficiency and easily process the moving blade. A cavity is formed in the i... | 07/03/2001 |
| 6217279 | Device for sealing gas turbine stator blades A sealing device for a gas turbine stator blade, in which an outer shroud (32) is mounted by heat insulating rings (32a,32b) on a blade ring (50). The blade ring (50) has a first air hole (1), which communicates with a space (53), and a second air hole (5... | 04/17/2001 |
| 6196791 | Gas turbine cooling moving blades In gas turbine cooled moving blade, a cooling air passage is made shortest and temperature elevation and pressure drop of the cooling air are suppressed. The cooling air passage (16) is bored in a turbine cylinder wall (15) located below a first stage sta... | 03/06/2001 |
| 6196799 | Gas turbine moving blade platform A gas turbine moving blade platform having a simplified cooling structure for effecting uniform cooling of the platform. The platform (1) includes cavities (2, 3, 4) and an impingement plate (11) provided below the cavities (2, 3, 4). A cooling hole (5) c... | 03/06/2001 |
| 6189891 | Gas turbine seal apparatus A gas turbine seal structure provided between end portions of a moving blade platform and a stationary blade inside shroud. The sealing performance of the seal structure is improved by increasing the resistance to the flow of air. A seal plate (21, 31) is... | 02/20/2001 |
| 6190130 | Gas turbine moving blade platform A gas turbine moving blade platform having a simplified platform cooling structure. A cooling effect of the platform side end portions is increased resulting in uniform cooling of the entire platform. Cooling passages (2, 3) are bored in the platform (1) ... | 02/20/2001 |
| 6152695 | Gas turbine moving blade In a gas turbine moving blade 1, the convection of cooling air is promoted to enhance the heat transfer rate, the cooling effect of a shroud 2 is enhanced and the entire cooling effect of the blade is enhanced. An inner cavity 10 is formed in the blade ov... | 11/28/2000 |
| 6151881 | Air separator for gas turbines An air separator for a gas turbine, in which cracks are prevented from occurring at a flange portion of the air separator due to fretting fatigue. The air separator (20) has a cylindrical split structure formed by two separator members (20-1 and 20-2), of... | 11/28/2000 |
| 6146091 | Gas turbine cooling structure A gas turbine having cooling structure disposed on an outside peripheral side in a radial direction of a movable vane in which the cooling efficiency is further improved and sealing structure disposed on an inner peripheral side to suppress leakage of sea... | 11/14/2000 |
| 6099253 | Gas turbine rotor blade A gas turbine rotor blade has a plurality of first cooling holes for the flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane di... | 08/08/2000 |
| 6099244 | Cooled stationary blade for a gas turbine In the present invention, seal air passes through a tube extending in a stationary blade from an outside shroud to an inside shroud, flows into a cavity to keep the pressure in the cavity high so as to seal the high-temperature combustion gas, and is disc... | 08/08/2000 |
| 6089826 | Turbulator for gas turbine cooling blades A gas turbine cooled blade has leading edge turbulators. A rounded tip portion of the leading edge portion cooling passage (3) is approximated by a triangular cooling passage (1) having orthogonal turbulators (11, 12) and a smoothly curved rear portion th... | 07/18/2000 |
| 6079946 | Gas turbine blade In the cooling system for the gas turbine blade, the apparatus of the present disclosure ensures cooling of the trailing edge part of the blade for which machining is difficult, while aiming at improvement of the thermal efficiency. The steam cooling stru... | 06/27/2000 |
| 6077034 | Blade cooling air supplying system of gas turbine In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling pa... | 06/20/2000 |
| 6039531 | Gas turbine blade The present disclosure provides a gas turbine blade in which the tip end thereof is cooled effectively to decrease the metal temperature for the prevention of burning and the temperature gradient of blade metal is decreased to prevent the occurrence of cr... | 03/21/2000 |
| 6036436 | Gas turbine cooling stationary vane There is provided a cooled stationary blade of a gas turbine in which the portions which can be cooled sufficiently by air are air-cooled, and the portions which are difficult to cool by air are steam-cooled, by which high temperatures can be overcome. In... | 03/14/2000 |
| 6036440 | Gas turbine cooled moving blade The present invention relates to a gas turbine cooled moving blade in order to cool the gas turbine using steam alone. In the moving blade, two cavities are installed in the lower part of the moving blade root section of the moving blade, a steam inlet is... | 03/14/2000 |
| 6019573 | Heat recovery type gas turbine In a steam cooled type gas turbine, taking the effect of efficiency and power output into consideration, a rear stage is sufficiently cooled by air in place of cooling all of the stages by steam. In a rotor of the gas turbine having a steam cooled moving ... | 02/01/2000 |
| 6019579 | Gas turbine rotating blade A gas turbine rotating blade comprises a serpentine passage provided in the blade width direction in plural rows in a blade profile portion except the portion near the trailing edge having a small blade thickness, a steam cooling passage provided around t... | 02/01/2000 |
| 5997245 | Cooled shroud of gas turbine stationary blade The invention relates to a cooled shroud in a gas turbine stationary blade which is able to flow a cooling air in the entire area of an inner shroud for cooling thereof. Three stationary blades are fixed to the inner shroud 2, a cover 13, 14 is provided t... | 12/07/1999 |
| 5971707 | Gas turbine moving blade steam cooling system A gas turbine moving blade steam cooling system in which leakage of steam for cooling a moving blade is prevented and thermal stress at a blade root end portion is mitigated. Each end portion of a blade root portion (3) of the moving blade (1) is projecte... | 10/26/1999 |
| 5967745 | Gas turbine shroud and platform seal system A gas turbine shroud and platform seal system, which is constructed so that the flow of sealing air does not disturb a combustion gas flow, and thus any aerodynamic loss is reduced. The leaking air (60) leaks from between a platform (2) of moving blade (1... | 10/19/1999 |
| 5954475 | Gas turbine stationary blade A gas turbine stationary blade, having a simple structure in which sufficient cooling is achieved and the drop in pressure of cooling vapor is decreased so that the turbine efficiency is prevented from lowering. The shape of a vapor passage is simplified ... | 09/21/1999 |
| 5915923 | Gas turbine moving blade A gas turbine moving blade in which the moving blade operating in a high temperature operating gas is cooled from its interior by steam and the steam after being used for the cooling is recovered, by use of a simple structure. A supply side passage (10), ... | 06/29/1999 |
| 5795130 | Heat recovery type gas turbine rotor Disclosed is a gas turbine rotor (5) having multi-stage moving blades, each fitted to a disc (12), characterized in comprising: an inner cavity (9) and an outer cavity (8) provided between each disc (12); a blade cooling passage (6) of each moving blade e... | 08/18/1998 |
