Faceted dome assemblies for gas turbine engine combustors

a technology of combustor and combustible components, which is applied in the direction of machines/engines, efficient propulsion technologies, lighting and heating apparatus, etc., can solve the problems of hot spots, wear on combustor and/or components, and gaps that are typically not uniform throughout the protective dom

Inactive Publication Date: 2009-04-09
HONEYWELL INT INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As a result, the gaps are typically not uniform throughout the protective dome.
This may cause uneven heat distribution and resulting “hot spots”, and / or wear on the combustor and / or components thereof.

Method used

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  • Faceted dome assemblies for gas turbine engine combustors
  • Faceted dome assemblies for gas turbine engine combustors
  • Faceted dome assemblies for gas turbine engine combustors

Examples

Experimental program
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Embodiment Construction

[0016]Before proceeding with the detailed description, it is to be appreciated that the described embodiment is not limited to use in conjunction with a particular type of turbine engine. Thus, although the present embodiment is, for convenience of explanation, depicted and described as being implemented in a multi-spool turbofan gas turbine jet engine, it will be appreciated that it can be implemented in various other types of turbines engines, and in various other systems and environments.

[0017]An exemplary embodiment of an upper portion of an annular multi-spool turbofan gas turbine jet engine 100 is depicted in FIG. 1. The engine 100 includes an intake section 102, a compressor section 104, a combustor section 106, a turbine section 108, and an exhaust section 110. The intake section 102 includes a fan 112, which is mounted in a fan case 114. The fan 112 draws air into the intake section 102 and accelerates it. A fraction of the accelerated air exhausted from the fan 112 is dire...

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PUM

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Abstract

A dome assembly for a gas turbine engine includes a plurality of faceted segments and a plurality of openings. The plurality of faceted segments are coupled together to form a dome structure that is configured to be disposed between an inner liner and an outer liner that circumscribes the inner liner. The plurality of openings are each opening formed within a respective faceted segment, and are configured to at least partially house an atomizer therein. Each faceted segment is at least substantially flat.

Description

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT[0001]This invention was made with Government support under contract number F33615-03-D-2355-D006 awarded by the United States Air Force. The Government has certain rights in this invention.TECHNICAL FIELD[0002]The present invention generally relates to gas turbine engines, and more particularly relates to combustors for gas turbine engines.BACKGROUND OF THE INVENTION[0003]A gas turbine engine may be used to power various types of vehicles and systems. A particular type of gas turbine engine that may be used to power aircraft is a turbofan gas turbine engine. A turbofan gas turbine engine may include, for example, five major sections: a fan section, a compressor section, a combustor section, a turbine section, and an exhaust section.[0004]The fan section typically is positioned at the front or “inlet” section of the engine and includes a fan that induces air from the surrounding environment into the engine and accelerate...

Claims

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Application Information

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IPC IPC(8): F23R3/42
CPCY02T50/675F23R3/10Y02T50/60
InventorPARDINGTON, RONALD B.KETTINGER, JONATHAN N.
OwnerHONEYWELL INT INC