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Method for the start-up of a gas turbine

A technology of gas turbines and turbines, which is applied in the direction of gas turbine devices, engine start-up, turbine/propulsion device start-up, etc., and can solve problems such as ignition failure of turbines with difficult flammability conditions, mechanical parts damage to operator safety, etc.

Inactive Publication Date: 2009-08-12
NUOVO PIGNONE SPA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0015] ignition failure of the turbine due to difficulties in controlling the flammability conditions of the air / fuel mixture inside the combustion chamber;
[0016] Damage to the mechanical parts of the turbine and / or safety to the operator due to the possibility, even if rare, of an explosion within the electric motor and / or the exhaust duct as a result of the heat generated during the ignition phase problem in terms of

Method used

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  • Method for the start-up of a gas turbine
  • Method for the start-up of a gas turbine
  • Method for the start-up of a gas turbine

Examples

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Embodiment Construction

[0030] especially with reference to figure 1 , which schematically shows a general gas turbine comprising a compressor 10 capable of compressing air introduced through an introduction pipe 12 . The compressed air is then sent to the combustor 14 to mix with the gaseous fuel from the delivery pipe 16 selected from a range of gaseous fuels having different Wobbe indices. Combustion increases the temperature, velocity and flow of the gas and thus increases the energy contained within it. Said flow of combustion gases is directed through ducts 18 towards a turbine 20 that converts energy into working energy that can be used to start a running machine, such as for example a generator 22 itself connected to the turbine 20 by means of a shaft 24 . The turbine 20 also supplies the necessary energy to start the compressor 10 through an associated shaft 26 , while the exhaust gases exit the turbine 20 through an exhaust pipe 28 .

[0031] According to the invention, the method for the...

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Abstract

A method is described for the start-up of a gas turbine comprising the phases of effecting a preliminary purging cycle of the discharge duct (28) of the turbine (20), establishing a predetermined minimum value (FSR 1 ) for the flow of gaseous fuel entering the combustor (14) for a period of time which is adequate for effecting a first attempt at ignition and effecting a first attempt at ignition, effecting an intermediate purging cycle of the discharge duct (28), interrupting the flow of gaseous fuel to the combustor (14), and progressively increasing the value (FSR n ) of the flow of gaseous fuel entering the combustor (14), effecting further attempts at ignition until the mixture of air / gaseous fuel has been ignited and the consequent start-up of the turbine (20), or until a predetermined maximum value (FSR max ) of the flow of gaseous fuel has been reached.

Description

technical field [0001] The invention relates to a method for the start-up of a gas turbine. Background technique [0002] In many industrial applications, such as for example in the production of electrical energy, the use of gas turbines is known. Gas turbines generally include a multiphase compressor, a combustor, and a turbine or expander. The compression takes place, and the gaseous fuel added to the compressed air is combusted in a combustor, and the gas from the combustor is expanded in a turbine or expander. The turbine is thus able to generate mechanical energy, which can be used to drive a machine in motion or to charge a generator. [0003] As is known, the start-up or commissioning phase of a gas turbine is a relatively complex operation. Before a gas turbine can operate at full regime, it is generally necessary to bring the compressor up to a rotational speed sufficient to provide a certain compression ratio. This operation is generally achieved by means of a ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/26
CPCF02C7/26F01D19/00F02C9/26F02C7/057F02C7/264F02C9/00
Inventor C·博塔雷利
Owner NUOVO PIGNONE SPA
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