Size scaling of a burner
A burner, size technology, applied in the direction of combustion chamber, combustion method, combustion equipment, etc., can solve the problems of unstable fluid dynamic process, reduced premixed flame stability, 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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[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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The invention relates to a method for upscaling the size of a burner (1) of a gas turbine engine comprising a burner housing (2), in which burner (1) at an upstream end a mixture of fuel (14) and air (12) is provided from a premixing channel (10) for sustaining a main flame (7) at a downstream end of the burner (1), wherein the premixing channel (10) is defined at its exit (8) by a circular inner wall formed by an inner quarl section (4a) and a circular outer wall formed by an outer quarl section (4b). According to the invention the burner (1) can be increased in size by adding a quarl section (4c) outside and circumferenting said quarl section (4b) and forming an annular space between the added quarl section (4c) and the existing outer quarl section (4b) and by adding a premixing channel (11) defined at its exit (9) by a circular inner wall formed by said previously outmost quarl section (4b) and a circular outer wall formed by the added quarl section (4c), wherein said quarl sections (4a, 4b, 4c) are defining a combustion room for housing said main flame (7), wherein an outer quarl section (4c, 4b) has a greater diameter than a neighboring inner quarl section (4b, 4a) and extends a greater distance downstream than the neighboring inner quarl section (4b, 4a).
Description
technical field [0001] The present invention relates to the quarl of a combustor preferably used in a gas turbine engine, more particularly to a quarl in a combustor suitable for stabilizing engine combustion, and further to the use of a pilot combustor A burner that provides combustion products to stabilize the main lean premixed combustion. 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 related to nitr...
Claims
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IPC IPC(8): F23R3/28F23R3/34
CPCF23R3/346F23R3/286F23R2900/00016F23R2900/00017
Inventor V·米洛萨夫莱维克
Owner SIEMENS AG