| Patent application number | Description | Published |
|---|
| 20080240924 | TURBINE BLADE - An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vain root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of ±2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion. | 10-02-2008 |
| 20100005808 | TWIN-SHAFT GAS TURBINE - A twin-shaft gas turbine | 01-14-2010 |
| 20100180604 | METHOD FOR STARTING PREMIXED COMBUSTION IN COMBUSTOR FOR TWO-SHAFT GAS TURBINE - A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out. | 07-22-2010 |
| 20110126547 | TWIN-SHAFT GAS TURBINE - A twin-shaft gas turbine | 06-02-2011 |
| 20110167833 | METHOD FOR STARTING PREMIXED COMBUSTION IN COMBUSTOR FOR TWO-SHAFT GAS TURBINE - A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out. | 07-14-2011 |
| 20110236195 | Compressor - It is an object of the present invention to provide a compressor that has a simple structure, produces a damping effect and improves aerodynamic performance. | 09-29-2011 |
