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Fuel staging in burner

By guiding the combustion chamber to provide heat and free radicals, combined with the swirler and multi-burner layout, it solves the problems of unstable flame and high NOx emissions in the lean-oil premixed combustion process in gas turbine engines, achieving stable combustion and low Emission burner design.

Inactive Publication Date: 2014-02-05
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008]3. Equivalence ratio fluctuations are probably the most common coupling mechanism linking unstable heat release with unstable pressure oscillations
[0011]6. Another very important reason for the reduction of premixed flame stability is that the steep gradient of fuel and air mixing will be eliminated from the combustion process
This results in temperature differences from burner to burner which can damage engine components

Method used

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  • Fuel staging in burner
  • Fuel staging in burner
  • Fuel staging in burner

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Embodiment Construction

[0051] Various embodiments will be described in more detail below with reference to the disclosed figures.

[0052] exist figure 1 In , the burner is described with a burner 1 having a housing 2 enclosing the burner assembly.

[0053] For clarity, figure 2 A cross-sectional view of the burner on the axis of rotational symmetry is shown. The main parts of the burner are a radial swirler 3 , a plurality of combustion channels 4 a , 4 b , 4 c and a pilot combustion chamber 5 .

[0054] As previously stated, the burner 1 operates on the principle that heat and a high concentration of free radicals are "supplied" from the discharge port 6 of the pilot combustion chamber 5 into the lean premixed air / fuel swirl The main flame 7 that burns in the middle, so as to maintain the rapid and stable combustion of the main lean premixed flame 7, wherein the lean premixed air / fuel swirl flows out of the first outlet 8 of the first lean premixed channel 10 and the second leaned fuel The se...

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Abstract

The invention relates to a method for staging operation at start up of a burner for a gas turbine engine combustor. It is one object of the invention to stabilize the combustion of a lean-rich partially premixed low emission burner for a gas turbine combustor at all engine load conditions. The method includes the steps of: - adding fuel (23) mixed with air (24) to the pilot combustor (5); - igniting the mixture utilizing an ignitor (34) provided at an upstream end of the pilot combustor (5) for initiating a lean flame (35) inside the pilot combustor (5) and for providing a flow of said radicals (32) and heat; - imparting a swirl of fuel (30b) and air (27) at an outside at the exit (6) of the pilot combustor (5) at an upstream end of a combustion room for creating and sustaining a main lean flame (7); - gradually adding a swirl of air (12) and fuel (14) for establishing a full load stage to at least one channel (10, 11).

Description

technical field [0001] The present invention relates to combustors preferably used in gas turbine engines, more particularly to fuel staging of combustors suitable for stabilizing engine combustion, and further to the use of a pilot combustor to provide products of combustion so that the main Fuel staging in lean premixed combustion stabilized combustors. Background technique [0002] Gas turbine engines are used in a variety of applications including power generation, military and commercial aviation, pipeline transportation, and marine transportation. In a gas turbine engine operating in LPP mode, fuel and air are supplied to the combustion chamber where they are mixed and ignited by a flame to start combustion. In addition to thermal efficiency, proper mixing of fuel and air, the main issues related to the combustion process of gas turbine engines are related to flame stabilization, pulsation and noise cancellation, and control of polluting emissions, especially those re...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/34
CPCF23D2900/00015F23R3/343F23R3/346
Inventor V·米洛萨夫莱维克
Owner SIEMENS AG