Nested channel ducts for nozzle construction and the like

a technology of nozzle construction and ducting, which is applied in the direction of turbine/propulsion fuel flow conduit, combustion process, turbine/propulsion fuel valve, etc., can solve the problems of cumbersome multi-channel system, heavy, difficult to manufacture and maintain, etc., and achieves the effect of simple and more economical manufacturing

Inactive Publication Date: 2006-11-23
PRATT & WHITNEY CANADA CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0006] It is an object of the present invention to provide an improved fuel injection system that is simpler and more economical to manufacture.
[0007] It is a further object of the present invention to provide a fuel injection system that, among other things, eliminates the need for multiple independent fuel manifolds and for complex fuel nozzle stems.

Problems solved by technology

Prior art multiple channel systems are cumbersome, difficult to manufacture and maintain, and heavy.

Method used

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  • Nested channel ducts for nozzle construction and the like
  • Nested channel ducts for nozzle construction and the like
  • Nested channel ducts for nozzle construction and the like

Examples

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Embodiment Construction

[0017]FIG. 1 illustrates a gas turbine engine 10 generally comprising, in serial flow communication, a fan 12 through which ambient air is propelled, a multistage compressor section 14 for pressurizing the air, a combustion section 16 in which the compressed air is mixed with fuel atomized into a combustion chamber 17 by a fuel injection system comprising a fuel injection nozzle assembly 20, the mixture being subsequently ignited for generating hot combustion gases before passing through a turbine section 18 for extracting energy from the combustion gases.

[0018] Referring to FIG. 2, the fuel injection nozzle assembly 20 comprises an annular fuel manifold ring 22 generally disposed within the combustion chamber 17 of the engine, and mounted via several integral attachment lugs 28 for fixing the annular ring 22 to an appropriate support structure. The annular fuel manifold ring 22 comprises a plurality of fuel injector spray tip assemblies 24 thereon, which atomize the fuel for combu...

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PUM

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Abstract

A multiple conduit system for a gas turbine engine, the multiple conduit system extending between a plurality of conduit inlet and outlets. A channel, adapted for conveying fuel flow, is formed in a surface of a gas turbine engine component. The channel includes at least a first discrete conduit and a second discrete conduit. The first and second discrete conduits are each adapted to direct an independent fluid flow from respective inlets to respective outlets.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS [0001] This application is a continuation of U.S. patent application Ser. No. 10 / 231,334 filed Aug. 30, 2002, which was allowed on Oct. 25, 2005, and the specification of which is incorporated herein by reference.TECHNICAL FIELD [0002] The present invention relates generally to gas turbine engines, and more particularly to a nested channel configuration for use in fuel manifolds, nozzle stems and the like. BACKGROUND OF THE INVENTION [0003] Fuel nozzles which supply fuel to a combustion chamber in a gas turbine engine are well known in the art. Generally, a plurality of circumferentially distributed fuel nozzles forming a nozzle array in the combustion chamber are used to ensure sufficient distribution of the fuel. The fuel nozzle array typically comprises a plurality of injector tip assemblies for atomizing fuel into the combustion chamber, the injector tips being connected to an outer fuel manifold via nozzle stems. [0004] Some conventional ...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F02C7/22F23K5/06F02C7/232F23R3/28
CPCF02C7/222F23R3/283F23K5/06
Inventor PROCIW, LEV ALEXANDERSHAFIQUE, HARRISSOKALSKI, JOHNPELLETIER, CLAUDE RAYMOND
Owner PRATT & WHITNEY CANADA CORP
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