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Gas turbine

A technology of gas turbines and turbines, applied in the direction of gas turbine devices, mechanical equipment, engine components, etc., can solve the problem of not providing auxiliary blades to cool turbine blades, etc.

Inactive Publication Date: 2013-03-27
ANSALDO ENERGIA IP UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Also, in this case there is no provision for cooling the turbine blades with auxiliary blades

Method used

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Embodiment Construction

[0022] The idea that is part of the invention is to integrate independent compressor stages on the gas turbine shaft, with the explicit primary goal of producing cooling air only at the required pressure level. Thus, the individual stages can be designed in an optimized manner to meet the cooling requirements and no specific cooling needs to be taken into account during the compression of the main mass flow of combustion air. The generation of the necessary pressure levels can be achieved by all available types of compressors (axial, radial or diagonal). It is also conceivable to use the surge effect through a simple channel on / in the rotor.

[0023] figure 2 and figure 1 Similarly, a schematic diagram of a (generally) exemplary embodiment of a gas turbine according to the invention is shown. figure 2 The gas turbine 20 shown has and figure 1 The gas turbine 10 shown has the same core elements 11 to 17 . However, the cooling design of the gas turbine is different. To g...

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Abstract

The invention refers to a gas turbine (20), comprising a compressor (12), which, via an air intake (11), inducts and compresses air, a combustion chamber (13), in which a fuel (14) is combusted, using the compressed air, and a hot gas is produced, and also a turbine (15), equipped with turbine blades (32), in which the hot gas is expanded, performing work, wherein first means are provided in order to cool turbine blades with compressed cooling air. Improved efficiency is achieved by the first means comprising at least one separate compressor stage (22) which produces compressed cooling air independently of the compressor (12).

Description

technical field [0001] The invention relates to the technical field of gas turbines. The invention relates to a gas turbine according to the preamble of claim 1 . Background technique [0002] Because of the high thermal and mechanical stresses that occur in gas turbines, cooling air must be supplied to most of the rotor blades and stator blades of said turbines. In order to ensure proper cooling of the blades, a sufficiently high pressure ratio must exist between the cooling air and the hot gas in the hot gas channel. As cooling air, most of the air is discharged at the discharge point of the axial compressor of the gas turbine provided for this purpose. Cooling air is fed to individual turbine blades using various duct systems. In this case, an important point in gas turbine design is to properly select the pressure rating of the relief point to match the pressure rating required by the turbine at the point where cooling is required. [0003] figure 1 A greatly simpli...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C3/08
CPCF01D5/082F01D5/081F02C3/08F02C7/18F02C3/04F01D25/12
Inventor B·法伊特C·西蒙-德尔加多D·森A·豪比茨
Owner ANSALDO ENERGIA IP UK LTD