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Methods and apparatus for fabricating gas turbine engine combustors

a gas turbine engine and combustion chamber technology, applied in the direction of combustion process, hot gas positive displacement engine plant, burner, etc., can solve the problems of material degradation and/or erosion of the combustor venturi, increase the fabrication time and cost, and increase the cost of coatings

Inactive Publication Date: 2005-10-20
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, continued operation with water injection may cause material degradation and / or erosion of the combustor venturi.
Over time, such explosive boiling may lead to material degradation and / or removal at the point of impact between the water and the venturi.
Although such coatings may decrease the effect of the water injection, such coatings also increase the fabrication time and costs.

Method used

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  • Methods and apparatus for fabricating gas turbine engine combustors
  • Methods and apparatus for fabricating gas turbine engine combustors
  • Methods and apparatus for fabricating gas turbine engine combustors

Examples

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Embodiment Construction

[0011]FIG. 1 is a schematic illustration of a gas turbine engine 10 including a low pressure compressor 12, a high pressure compressor 14, and a combustor 16. Engine 10 also includes a high pressure turbine 18 and a low pressure turbine 20. Combustor 16 includes an upstream side 22, and at least one dome (not shown). In one embodiment, the gas turbine engine is a LMS 100 engine commercially available from General Electric Company, Cincinnati, Ohio.

[0012] In operation, air flows through low pressure compressor 12 and compressed air is supplied from low pressure compressor 12 to high pressure compressor 14. The highly compressed air is delivered to combustor 16. Airflow (not shown in FIG. 1) from combustor 16 drives turbines 18 and 20.

[0013]FIG. 2 is a cross-sectional view of a portion of a combustor, such as combustor 16, that may be used with gas turbine engine 10. Combustor 16 includes a plurality of swirler assemblies 30, each of which includes a primary swirler 32, a secondary ...

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PUM

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Abstract

A method facilitates fabricating a gas turbine engine combustor. The method comprises coupling a venturi to a primary swirler, and coupling the venturi to a secondary swirler such that a gap is defined between a portion of the venturi and a portion of one of the primary swirler and the secondary swirler.

Description

BACKGROUND OF THE INVENTION [0001] This application relates generally to gas turbine engines and, more particularly, to combustors for gas turbine engine. [0002] Combustors are used to ignite fuel and air mixtures in gas turbine engines. Known combustors include at least one dome attached to a combustor liner that defines a combustion zone. Fuel injectors are attached to the combustor in flow communication with the dome and supply fuel to the combustion zone. Fuel enters the combustor through a dome assembly attached to a spectacle or dome plate. [0003] At least some known dome assemblies include an air swirler that is secured to the dome plate, and is radially outward from a venturi. The venturi is divergent and facilitates mixing the air and fuel, and spreading the mixture radially outwardly into the combustion zone. [0004] To facilitate nitrous oxide (NOx) abatement, water is injected into at least some known gas turbine engine combustors. However, continued operation with water ...

Claims

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Application Information

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IPC IPC(8): F23R3/14F23R3/22
CPCF23R3/14F23D2211/00
Inventor KASTRUP, DAVID ALLENMARTINI, JEFFREY MICHAELFORTUNA, DOUGLAS MARTIHELD, TIMOTHY JAMESDE VANE, SHAUN MICHAELCOOPER, JAMES NEIL
Owner GENERAL ELECTRIC CO