Gas turbine engine with alternating patterns of active burners and method of controlling a gas turbine engine

A gas turbine and burner technology, which is applied in engine control, machine/engine, gas turbine installations, etc., and can solve the problems of shortened component life, impact of engine maintenance cycle, serious thermal stress, etc.

Pending Publication Date: 2021-05-18
ANSALDO ENERGIA SWITZERLAND AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Another limitation of the known gas turbine engines is that the thermal stresses are still severe and the lifetime of the components that remain always in the area where the burner is activated is significantly shortened compared to other components in cold regions
As a result, the maintenance interval of the engine is affected by the aging of certain components and requires relatively frequent maintenance

Method used

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  • Gas turbine engine with alternating patterns of active burners and method of controlling a gas turbine engine
  • Gas turbine engine with alternating patterns of active burners and method of controlling a gas turbine engine
  • Gas turbine engine with alternating patterns of active burners and method of controlling a gas turbine engine

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Experimental program
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Embodiment Construction

[0027] figure 1 A simplified view of a gas turbine engine generally designated by the numeral 1 is shown. The gas turbine engine 1 comprises a compressor 2 , a first stage combustor 3 , a high pressure turbine 5 , a second stage combustor 7 (also called sequential combustor) and a low pressure turbine 8 .

[0028] The fuel supply system 9 delivers fuel flow to operate the first stage burner 3 and the second stage burner 7 .

[0029] A controller 10 receives status signals from system sensors 11 and operates the gas turbine through actuators to provide a controlled power output. The actuators comprise an orientable inlet guide vane 12 of the compressor 2 and a first stage fuel valve system 13 and a second stage fuel valve system 15 of the fuel supply system 9 .

[0030] The compressed air flow supplied by the compressor 2 is increased by a first fuel flow M1 and the air / fuel mixture thus obtained is combusted in a first stage burner 3 . The exhaust gas of the first stage com...

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Abstract

Disclosed is a gas turbine engine comprising a combustor assembly (7) with a plurality of burners (18) circumferentially arranged about an axis (A); a fuel supply system (9), supplying a fuel flowrate (M2) to the burners (18); and a control unit (10), configured to control the fuel flowrate (M2). An equal number of adjacent burners (18) is maintained active in a first partial load condition and in a second partial load condition, and at least one of the burners (18) which are active in the first partial load condition is deactivated in the second partial load condition and at least one of the burners (18) which are inactive in the first partial load condition is activated in the second partial load condition.

Description

[0001] Cross References to Related Applications [0002] This patent application claims priority from European Patent Application No. 19209838.2 filed on November 18, 2019, the entire disclosure of which is hereby incorporated by reference. technical field [0003] The present invention relates to a gas turbine engine with an alternate mode of activating the burner and to a method of controlling the gas turbine engine. Background technique [0004] It is well known that controlling pollutant emissions is a first and foremost objective in the design of any type of heat engine and especially gas turbines for power plants. In fact, awareness of environmental risks has prompted regulations with increasingly stringent requirements. On the other hand, the organization and changing demands of modern electricity markets do not allow power stations to be operated under constant load conditions. In contrast, very flexible operation is required to meet demand fluctuations (including ...

Claims

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Application Information

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IPC IPC(8): F02C9/26F02C7/22F23R3/28
CPCF02C9/26F02C7/22F23R3/28F02C9/34F02C7/228F05D2270/11F23R2900/03341
Inventor R·雅科比R·凯勒尔C·阿佩尔J·里恩A·斯图德鲁斯
Owner ANSALDO ENERGIA SWITZERLAND AG
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