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Gas turbine and method of operating gas turbine

一种燃气轮机、空气的技术，应用在燃气轮机装置、发动机的冷却、机器/发动机等方向，能够解决空气量的调整单元没有任何公开等问题，达到抑制热效率的降低的效果

Active Publication Date: 2011-05-25
MITSUBISHI POWER LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the above-mentioned patent documents, there is no disclosure of any adjustment unit for the air volume relative to such turbine load fluctuations.

Method used

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  • Gas turbine and method of operating gas turbine
  • Gas turbine and method of operating gas turbine

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Embodiment approach 1

[0026] figure 1 It is an overall view of the gas turbine system according to the first embodiment. figure 2 It is a schematic configuration diagram of the gas turbine 3 according to the first embodiment. like figure 1 and figure 2 As shown, the combustion air supplied to the gas turbine 3 of this embodiment is introduced into the compressor 20 through the air filter 71 . Combustion air compressed to a predetermined pressure by the compressor 20 is supplied to the combustor 30 and mixed with fuel for combustion. Combustion gas generated in the combustor 30 is introduced into the turbine 10 , and when flowing down the turbine-side stationary blades 12 and the turbine-side moving blades 13 , thermal energy is converted into rotational energy of the rotor 50 of the turbine 10 and taken out as electric power from the generator 80 .

[0027] The gas turbine 3 of this embodiment is such as figure 2 As shown, a compressor 20 , a combustor 30 , a turbine 10 , and an exhaust cha...

Embodiment approach 2

[0072] Figure 7 It is an overall view of the gas turbine system according to the second embodiment. In Embodiment 2, a case is shown in which a plurality of air sources for cooling air are provided in order to cool the turbine-side rotor blade 13 at the rear stage to be supplied to the turbine 10 .

[0073] like Figure 7 As shown, the gas turbine system 2 is equipped with a compressor high-pressure suction port 27 , a compressor low-pressure suction port 28 , and an air inlet 29 as air sources. The gas turbine system 2 includes an external passage 68 from each air source to a shaft end seal portion 67 provided at the shaft end of the rotor 50 of the turbine 10 .

[0074] Compressor high-pressure suction port 27 and compressor low-pressure suction port 28 can extract compressed air from the middle section of the compressor. The compressor high-pressure air outlet 27 and the compressor low-pressure air outlet 28 are not limited to two as required, and more than three air ou...

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Abstract

The present invention relates to a gas turbine and a method of operating a gas turbine. The gas turbine has an axial path provided in a rotating member which extends along the center axis, or the rotation axis, of a rotor and rotates about the center axis and allowing cooling air to flow therein along the center axis of the rotor; radial paths circumferentially arranged in the rotating member so as to extend outward from the center of the rotor, compressing the cooling air, and each having one end communicating with the axial path and the other end communicating with the outside of the rotating member; and an external path provided with an air volume regulating means and having one end communicating with an air source from which the external path takes in air and the other end communicating with the axial path to introduce the cooling air into the external path.

Description

technical field [0001] The present invention relates to a gas turbine and a method of operating the gas turbine. More specifically, the present invention relates to a gas turbine for cooling rotor blades on the turbine side and a method of operating the gas turbine. Background technique [0002] Currently, there is a gas turbine as a device that obtains energy from combustion gas that burns air and fuel. The gas turbine rotates a turbine using energy of combustion gas generated by combusting fuel and compressed air to output rotational energy from a rotor. However, in order to supply the combustion gas to the turbine in a high-temperature state, rotor blades of the turbine receiving the high-temperature combustion gas are also exposed to a high-temperature atmosphere. Therefore, for example, Patent Document 1 discloses that air is supplied from the compressor side, which is a supply source of cooling air, to the rotor blade, which is a supply target of cooling air, through ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/18
CPCF05B2240/12F05D2260/20F05D2240/12F01D5/087F02C7/141F01D5/085F05B2240/61F05D2240/61F05B2260/20F01D5/08F01D5/18F02C7/18
Inventor 高村启太桥本真也由里雅则
Owner MITSUBISHI POWER LTD
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