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Fuel injection system for turbine engine

A turbine engine and fuel system technology, applied in the direction of turbine/propellant fuel delivery system, charging system, engine components, etc.

Inactive Publication Date: 2017-03-22
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The design's challenging assembly and disassembly process has been identified as a contributing factor in several important field issues leading to the failure of these components

Method used

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  • Fuel injection system for turbine engine
  • Fuel injection system for turbine engine
  • Fuel injection system for turbine engine

Examples

Experimental program
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Embodiment Construction

[0017] Such as Figure 1-3 As shown, a fuel system 10 for a gas turbine engine 12 is disclosed that improves efficiency by supplying fuel to a primary stage 14 and a secondary stage 16 via a common fuel source 18 . Fuel system 10 may be formed by first premix injector assembly stage 24 and first and second main injector assembly stages 20 , 22 positioned upstream of combustor chamber 26 whereby first premix injector assembly stage 24 It is the sub-injector system. The second main injector assembly stage 22 and the first premixing injector assembly stage 24 may be in fluid communication with the same fuel source 18, thereby eliminating the need to separately supply fuel to the second main injector assembly stage 22 and the first premixing injector assembly stage 24. Duplicate components occurring within the system of mixing injector assembly stage 24. The fuel system 10 may also be configured such that the first premixing injector assembly stage 24 need not be formed from cus...

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PUM

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Abstract

A fuel system (10) for a gas turbine engine that improves efficiency by supplying fuel to a primary stage (14) and secondary stage (16) via a common fuel source (18) is disclosed. The fuel system (10) may be formed from first and second primary injector assembly stages (20, 22) and a first premix injector assembly stage (24) positioned upstream from a combustor chamber (26), whereby the first premix injector assembly stage (24) is a secondary injector system. The second primary stage (22) and the first premix stage (24) may be in fluid communication with the same fuel source (18) to eliminate duplicative components found within systems where fuel is supplied individually to the second primary stage and the first premix stage. In at least one embodiment, the second primary injector assembly stage (22) and the first premix injector assembly stage (24) may each be in communication with a fuel manifold (28) configured to supply more fuel to the second primary stage (22) than the first premix stage (24).

Description

technical field [0001] The present invention relates generally to turbine engines, and more particularly to fuel systems for turbine engines. Background technique [0002] Typically, gas turbine engines include a plurality of injectors to inject fuel into the combustor to mix with air upstream of the flame region. The fuel injectors of a typical turbine engine can be arranged in one of at least three different schemes. The fuel injector may be positioned in a lean premixed flame system where the fuel is injected into the air stream far enough upstream from where the fuel / air mixture is ignited so that the air and fuel are burnt as they burn in the flame region. Mix thoroughly. Fuel injectors can also be configured in diffusion flame systems to allow simultaneous mixing and combustion of fuel and air. In another configuration, often referred to as a partial premix system, a fuel injector may inject fuel a sufficient distance upstream of the flame region so that some of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28F23R3/34F23K5/00F23K5/06
CPCF23D2900/00008F23K5/005F23K5/06F23R3/286F23R3/346F02C7/22
Inventor J.贝尔通塞罗R.施尔普T.A.福克斯J.W.哈德斯
Owner SIEMENS AG