| Patent application number | Description | Published |
|---|
| 20090185896 | GAS TURBINE AND GAS TURBINE COOLING METHOD - A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed. | 07-23-2009 |
| 20090196738 | GAS TURBINE AND GAS TURBINE COOLING METHOD - A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed. | 08-06-2009 |
| 20090320438 | TWO-SHAFT GAS TURBINE - Provided is a two-shaft gas turbine with improved reliability that improves output power and efficiency and is stably operated by establishing a balance between the driving force of a compressor and the output power of a high-pressure turbine in the case where the two-shaft gas turbine is applied to a system in which the flow rate of fluid flowing into a combustor is increased compared with a simple cycle gas turbine. | 12-31-2009 |
| 20100229566 | TWO-SHAFT GAS TURBINE SYSTEM - Disclosed herein is a highly-reliable two-shaft gas turbine system in which the rotational speed of a compressor exceeds its rated rotational speed when the combustion temperature during rated operation is set to the rated combustion temperature of a simple-cycle gas turbine system and in which the drive force for the compressor can be balanced with the output from a high-pressure turbine without turbine efficiency being compromised. | 09-16-2010 |
| 20100275644 | NATURAL GAS LIQUEFACTION PLANT AND MOTIVE POWER SUPPLY EQUIPMENT FOR SAME - A power supply equipment ( | 11-04-2010 |
| 20120060509 | Inner Bleed Structure of 2-Shaft Gas Turbine and a Method to Determine the Stagger Angle of Last Stage Stator of Compressor for 2-Shaft Gas Turbine - An inner bleed structure of the 2-shaft gas turbine includes a slit for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel of the compressor equipped with a last stage rotor of the compressor which is connected to a first rotating shaft and end of an inner casing, and a bleed hole for leading part of compressed air after flowing down the last stage of the compressor to a cavity formed in the inner side of the inner casing at the downstream side of the last stage of the compressor. | 03-15-2012 |
