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Turbine combustor and method for temperature control and damping a portion of a combustor

A technology for temperature control and burners, applied in combustion methods, combustion chambers, combustion equipment, etc., to solve problems such as engine hardware life and operability limitations

Inactive Publication Date: 2013-05-01
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

High dynamics can place limits on engine hardware life and operability due to factors such as mechanical and thermal fatigue

Method used

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  • Turbine combustor and method for temperature control and damping a portion of a combustor
  • Turbine combustor and method for temperature control and damping a portion of a combustor
  • Turbine combustor and method for temperature control and damping a portion of a combustor

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Embodiment Construction

[0016] figure 1 is a schematic diagram of one embodiment of a gas turbine system 100 . System 100 includes compressor 102 , combustor 104 , turbine 106 , shaft 108 , and fuel nozzles 110 . In one embodiment, system 100 may include a plurality of compressors 102 , combustors 104 , turbines 106 , shafts 108 , and fuel nozzles 110 . As shown, compressor 102 and turbine 106 are coupled by shaft 108 . The shaft 108 may be a single shaft or multiple shaft segments coupled together to form the shaft 108 .

[0017] In one aspect, combustor 104 operates the turbine engine using liquid fuel and / or gaseous fuel, such as natural gas or hydrogen-enriched syngas. For example, fuel nozzles 110 are in fluid communication with a fuel supply and pressurized air from compressor 102 . Fuel nozzles 110 generate an air-fuel mixture and discharge the air-fuel mixture into combustor 104 , thereby causing combustion capable of producing hot pressurized exhaust gases. Combustors 104 direct hot pre...

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PUM

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Abstract

According to one aspect of the invention, a turbine combustor (200) includes an outer member (202) coupled to a wall (204) of the combustor, wherein there is at least one damping hole (206) formed in outer member (202). The turbine combustor further includes at least one temperature control hole (214) formed in the wall (204) wherein the at least one temperature control hole (214) is formed at an angle (220) with respect to a line perpendicular to a hot gas path in the combustor.

Description

technical field [0001] The subject matter disclosed in this specification relates to turbomachines. More specifically, the subject matter relates to combustion dynamics control and temperature control of turbines. Background technique [0002] In a gas turbine engine, the combustor converts the chemical energy of the fuel or air-fuel mixture into heat energy. Thermal energy is delivered by a fluid (usually air from a compressor) to a turbine where it is converted into mechanical energy. Several factors affect the efficiency with which thermal energy is converted to mechanical energy. Such factors may include vane pass frequency, fuel supply fluctuations, fuel type and reactivity, combustor facing volume, fuel nozzle design, air-fuel distribution, flame shape, air-fuel mixing, flame hold, combustion temperature, turbine components design, hot gas path temperature dilution, and discharge temperature. [0003] For example, high combustion temperatures in selected locations ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/02
CPCF23R2900/03044F23R2900/03042F23R3/06F23R2900/00014
Inventor A.R.罕D.W.奇拉
Owner GENERAL ELECTRIC CO