Gas combustion turbine and its operation method and gas combustion turbine complex generation equipment
A technology of gas turbine and operation method, applied in mechanical equipment, machine/engine, engine function, etc., can solve problems such as high cost, fuel waste, starting loss, etc.
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Method used
Image
Examples
Embodiment approach 1
[0065] figure 1 Shown is an explanatory diagram of a steam-cooled gas turbine and its cooling system according to Embodiment 1 of the present invention. In this gas turbine, the rotor blades and the like are preheated with the air supplied from the machine room from the start of the gas turbine to the completion of the warm-up of the rotor blades and the like. It is characterized in that after the completion of preheating, the temperature of the cooling air supplied from the machine room and the steam supplied from the outside of the gas turbine are adjusted to be equal, and then the cooling medium is switched to steam. In the following, the switching of the cooling medium of the moving blades from air to steam will be described as an example, but the scope of application of the present invention is not limited to moving blades. For example, it is also applicable to the occasion where the cooling medium of the vane is switched from the auxiliary steam generated by the factor...
Embodiment approach 2
[0098] Figure 7 Shown is a partial cross-sectional view of a gas turbine according to Embodiment 2 of the present invention. This gas turbine is characterized in that it has a header pipe for precipitating the cooling medium. The header pipe is located on the upstream side of the pipe that supplies the cooling medium to the rotor blades and enters the main shaft 2 of the gas turbine. 2 Internal cooling medium supply pipes supply cooling medium.
[0099] As mentioned above, when the cooling medium of the moving blade is switched from machine room air to high-pressure steam, the gas turbine will fail to stall. The reason is that the temperature difference between the moving blade and the rotating system of the gas turbine such as the main shaft of the gas turbine or the impeller disk causes thermal expansion. And caused. Especially when the temperature distribution in the circumferential direction is produced at the gas turbine main shaft 2, the gas turbine main shaft 2 bends...
Deformed example 2
[0103] Figure 9 It is a sectional view perpendicular to the axial direction showing a second modified example of the gas turbine according to Embodiment 2 of the present invention. This gas turbine is characterized in that the number of steam recovery pipes 9 for recovering the steam after cooling the rotor blades is increased compared to conventional ones, thereby making the temperature distribution in the circumferential direction of the main shaft of the gas turbine more uniform. In the past, there were 8 to 12 vapor recovery pipes 9 inside the main shaft 2 of the gas turbine, such as Figure 9 As shown in (b), 8 to 12 high-temperature parts and low-temperature parts occur in the gas turbine main shaft 2 respectively, causing differences in the steam flow rates flowing to the respective steam recovery pipes 9, and the gas turbine main shaft 2 is more likely to occur in the axial direction. Temperature Distribution. here, as Figure 9 As shown in (a), in the gas turbine ...
PUM
Login to View More Abstract
Description
Claims
Application Information
Login to View More 