Pilot combustor in a burner
A combustion chamber, burner technology, applied in the direction of burners, combustion chambers, continuous combustion chambers, etc., can solve problems such as instability, unstable fluid dynamic process, thermodynamic-acoustic instability, etc.
Inactive Publication Date: 2011-02-23
SIEMENS AG
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Problems solved by technology
The less stable, easily moving flame front of premixed flames leads to periodic heat release rates, which in turn lead to flame motion, unstable fluid dynamics, and the development of thermodynamic-acoustic instabilities
[0007] 3. Equivalence ratio fluctuations are probably the most common coupling mechanism linking unstable heat release with unstable pressure oscillations
[0010] 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
Becomes more erratic as fire can more easily appear in multiple locations
Method used
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Embodiment Construction
[0054] Various embodiments will be described in more detail below with reference to the disclosed figures.
[0055] exist figure 1 In , a burner equipped with a pilot combustion chamber according to an aspect of the invention is described with a burner 1 having a casing 2 enclosing the burner assembly.
[0056] 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 .
[0057] 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 out...
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The invention relates to a pilot combustor particularly for use in a burner (1) of a gas turbine engine and a method for burning a fuel in a pilot combustor zone (22) of a pilot combustor (5). It is one object of the invention to stabilze combustion under all load conditions. According to the invention a pilot combustor having rotationally symmetric walls (21) defining a combustion room with an exit (6) is provided with a rich concentration of fuel in air for buring said fuel for the creation of a flow of an non equilibrium unquenched concentration of radicals (32) elevated to a temperature above 2000 K in the combustion room and directed along a centre line of the pilot combustor (5) through a throat (33) at the exit (6) of the pilot combustor (5), wherein a quarl (29) is located downstream of the throat (33) of the pilot combustor (5). According to the method the pilot combustor (5) is arranged upstream of a burner (1) for providing a main lean partially premixed combustion process occurring in a shear layer (18) of a main flame (7) surrounding a main recirculation zone (20) of said burner (1) downstream of the pilot combustor (5) with a flow of an unquenched concentration of radicals (32) at non equilibrium level and elevated to a temperature above 2000 K.
Description
technical field [0001] The present invention relates to combustors preferably used in gas turbine engines, more particularly to combustors suitable for stabilizing the engine's lean partially premixed (LPP) combustion process and engine turndown requirements, and furthermore, Concerns the use of a pilot combustion chamber to provide combustion products (free radicals and heat) to stabilize the main lean premixed combustion process. 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 a...
Claims
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IPC IPC(8): F23R3/34
CPCF23R3/343F23D2900/00014
Inventor V·米洛萨夫莱维克
Owner SIEMENS AG