Gas turbine with cooling air cooling system and method for operation of gas turbine at low part load

A technology for cooling air and gas turbines, applied in gas turbine installations, charging systems, engine cooling, etc., can solve problems such as harmful compressor efficiency, and achieve the effects of reducing energy consumption, simple structure, and satisfying emission adaptability

Inactive Publication Date: 2015-04-15
ANSALDO ENERGIA IP UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to this difference in thermal deformation of the compressor components, the tip clearances of the compressor blades or vanes become smaller than in steady par

Method used

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  • Gas turbine with cooling air cooling system and method for operation of gas turbine at low part load
  • Gas turbine with cooling air cooling system and method for operation of gas turbine at low part load
  • Gas turbine with cooling air cooling system and method for operation of gas turbine at low part load

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Embodiment Construction

[0026] figure 1 A schematic diagram of a first embodiment of a gas turbine according to the invention is shown with a cooling air cooling system for the inlet air to the compressor 1 and a preheater system 8 . The gas turbine 10 basically includes a compressor 1 , a combustor 2 and a turbine 3 . The gas turbine 10 is also provided in this embodiment with a preheater system 8 upstream of the air inlet 9 , whereby the inlet air flowing to the compressor 1 is heated, especially in part-load operation of the gas turbine 10 . Due to having at least a first cooling air line 4 or a cooling air bleeder pipe at the first pressure level of the compressor 1 and at least one second cooling air line 5 at a position downstream of the compressor 1 with respect to the first cooling air line 4 , the cooling air cooling system of the gas turbine 10 is particularly suitable for part-load operation, ie for cooling air that initially has a higher temperature and pressure. Cooling air from the co...

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PUM

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Abstract

Gas turbine (10) and method for operating a gas turbine (10), comprising a compressor (1), a combustor (2), a turbine (3) and a cooling air cooling system having at least a first cooling air line (4) going from a first bleed of the compressor (1) to the turbine (3), and at least one second cooling air line (5) at a downstream position of the compressor (1) relative to the first cooling air line (4), whereby a heat exchanger (7) is arranged in the second cooling air line (5) for cooling the extracted air of higher pressure, and the heat exchanger (7) is connected with an air inlet side of the compressor (1) such that heat is transferred in order to heat up the inlet air of the compressor (1).

Description

technical field [0001] The invention relates to a gas turbine with cooling air cooling system and also to a method for operating such a gas turbine at particularly low partial loads. In particular, the invention relates to a gas turbine having a cooling air cooling system which draws air at the bleed pipe downstream of the first bleed pipe on the compressor side, so that cooling air is drawn at different pressure levels for use in for the purpose of cooling turbine components. Background technique [0002] Parallel to the requirements regarding the performance and efficiency of such gas turbines, these requirements are increasing with respect to the cooling of highly stressed machine components on the one hand and the design and dimensioning of cooling systems on the other hand. From an operational safety point of view, it is necessary to ensure adequate cooling under all possible operating conditions of the gas turbine. This is especially true for gas turbines operating a...

Claims

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Application Information

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IPC IPC(8): F02C7/18F02C6/04
CPCF02C9/52F02C7/143F02C9/18F02C7/18F02C6/08
Inventor K.克纳普K.多伊贝林
Owner ANSALDO ENERGIA IP UK LTD
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