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.

Inactive Publication Date: 2003-04-09
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In this way, energy is required to cool the air in the machine room, and it is specially used to cool the air in the machine room, so it takes time to warm up the moving blades, etc., resulting in a corresponding waste of fuel
As mentioned above, gas turbines using steam cooling in the past had the problem of starting loss, that is, the cost of starting the gas turbine to obtain the rated output was large.

Method used

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  • Gas combustion turbine and its operation method and gas combustion turbine complex generation equipment
  • Gas combustion turbine and its operation method and gas combustion turbine complex generation equipment
  • Gas combustion turbine and its operation method and gas combustion turbine complex generation equipment

Examples

Experimental program
Comparison scheme
Effect test

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 ...

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Abstract

A steam temperature Ts and a casing air temperature Ta are measured by thermometers. The measurement results are taken into measuring devices and converted into electric signals. The electric signal is A / D converted by the measuring device and then, is sent to a control apparatus where a difference between both the temperature is calculated by a subtracter of a processor provided in the control apparatus. When an absolute value DELTA T = Ta - Ts of this difference is contained within 10 DEG C continuously ten times, a control signal is sent from a computing unit to a controller which is the control section, a pressure adjustingvalve and the like are controlled and a cooling medium is switched to steam.

Description

field of invention [0001] The present invention relates to a gas turbine using steam to cool high-temperature components, its operating method, and gas turbine composite power generation equipment. Background technique [0002] At present, in order to improve the thermal efficiency in the combined cycle of gas turbines, steam is used instead of air as the cooling medium, and the technology of steam cooling high-temperature parts such as moving blades and stationary blades of gas turbines is used. Here, the low-pressure specific heat of dry steam is cp=1.86kJ / kgK under standard conditions, which is close to twice the low-pressure specific heat of air, cp=1.00kJ / kgK. Therefore, under the same mass, the heat capacity of steam is larger than that of air, and the heat absorption effect is higher than that of air. Moreover, if wet steam is used as the cooling medium, the latent heat of evaporation of the wet part can also be used for cooling, thus further improving the heat absor...

Claims

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Application Information

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Patent Type & AuthorityApplications(China)
IPC IPC(8): F01D21/12F01D25/12F01D25/14F01D25/26F02C7/16
CPCF01D25/26F01D25/14Y02E20/16F02C7/16F01D25/12F05D2260/2322F01D21/12
Inventor百武慎德藤田泰弘
OwnerMITSUBISHI HEAVY IND LTD