A quarl of a burner for a gas turbine engine is provided. Fuel and air is mixed and provided to the burner. The quarl is arranged to house a main flame. Stability is achieved by a quarl, which is formed from a plurality of quarl sections, wherein each quarl section includes the configuration of the
A quarl of a burner for a gas turbine engine is provided. Fuel and air is mixed and provided to the burner. The quarl is arranged to house a main flame. Stability is achieved by a quarl, which is formed from a plurality of quarl sections, wherein each quarl section includes the configuration of the conical shell of a truncated cone and are distributed consecutively one after the other in the downstream direction of the burner, wherein a most narrow part of the shell of a downstream quarl section surrounds the widest part of the shell of the closest upstream quarl section and wherein an annular channel for premixed air and fuel is arranged between two consecutive quarl sections.
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1. A burner of a gas turbine engine, comprising: axially opposed upstream and downstream end portions arranged to receive mixed fuel and air to be burnt in a main flame of the burner,a quarl arranged to house the main flame, wherein the quarl comprises a plurality of quarl sections, wherein each qua
1. A burner of a gas turbine engine, comprising: axially opposed upstream and downstream end portions arranged to receive mixed fuel and air to be burnt in a main flame of the burner,a quarl arranged to house the main flame, wherein the quarl comprises a plurality of quarl sections, wherein each quarl section includes a configuration of a conical shell of a truncated cone, and wherein the quart sections are distributed consecutively one after the other in a downstream direction of the burner, andwherein a part of the second quarl section surrounds a part of the first quarl section, andwherein the main flame is formed as a conical rotational symmetric shear layer around a recirculation zone,a pilot combustor supplying a high concentration of free radicals directly to a forward stagnation point and to the main flame formed as the conical rotational symmetric shear layer around the recirculation zone, wherein the stagnation point is located within the quad and at an exit of the pilot combustor,an annular premixing channel for premixed air and fuel arranged between walls of the first and second quarl sections,wherein air is provided at an air inlet of the annular premixing channel, andwherein fuel is introduced through a tube located at the air inlet, whereby the fuel is distributed into the air flow as a spray and mixed with the air flow. 2. The burner as claimed in claim 1, wherein a length L of the quarl comprising the plurality of quarl sections corresponds to the equation 2*D>L>0.5*D, wherein D is a diameter of the quarl at a downstream end of the quarl. 3. The burner as claimed in claim 2, wherein the length L of the quarl corresponds to the equation L=D, wherein D is the diameter of the quarl at a downstream end of the quarl. 4. The burner as claimed in claim 1, wherein the second quarl section covers approximately ⅓ of the first quarl section, as seen along an axial direction of the quarl. 5. A method for substantially burning a fuel in a lean mix combustion process of a burner for a gas turbine provided with a quarl, comprising: providing a burner with a quarl arranged to house a main flame, wherein the quarl comprises a first and a second quarl section;providing an annular premixing channel for premixed air and fuel arranged between walls of the first and second quarl sections,providing air at an air inlet of the annular premixing channel,introducing fuel through a tube located at the air inlet, whereby the fuel is distributed into the air flow as a spray,mixing the fuel spray with the air flow,burning a main part of the fuel in a main flame housed in the quarl;anchoring the main flame in a defined position in space by using the quarl divided into a plurality of quarl sections;wherein the burner comprises: axially opposed upstream and downstream end portions arranged to receive the mixed fuel and air which is burnt in the main flame of the burner, wherein each quarl section includes a configuration of a conical shell of a truncated cone, and wherein the quail sections are distributed consecutively one after the other in a downstream direction of the burner, andwherein a part of the second quarl section surrounds a part of the first quarl section,wherein the main flame is formed as a conical rotational symmetric shear layer around a recirculation zone, anda pilot combustor supplying a high concentration of free radicals directly to a forward stagnation point P and to the main flame formed as the conical rotational symmetric shear layer around the recirculation zone,wherein the stagnation point is located within the quarl and at an exit of the pilot combustor. 6. A burner of a gas turbine engine, comprising: a radial swirler,a multi quarl,a first lean premixing channel,a second lean premixing channel,a pilot combustor with an exhaust,wherein heat and a high concentration of free radials is supplied from the exhaust of the pilot combustor to a main flame burning a lean premixed air/fuel swirl emerging from a first exit of the first lean premixing channel and from a second exit of the second lean premixing channel,wherein the first and second lean premixing channels comprise swirler wings forming the radial swirler to impart rotation to the air/fuel mixture,wherein the main flame is formed as a conical rotational symmetric shear layer around a main recirculation zone within the multi quarl,wherein the lean premixed air/fuel swirl comprises a swirl number between 0.6 and 0.8 so that the main recirculation zone is stable,wherein, in a swirl stabilized combustion, the heat and the free radicals are transported from a combusted air/fuel mixture back towards a main flame front and towards a forward stagnation point of the main recirculation zone, the forward stagnation point being located at the exhaust of the pilot combustor, for mixing with a fresh air/fuel mixture such that a reversely circulating flow of the free radicals within the main recirculation zone is provided.
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이 특허에 인용된 특허 (5)
Willis Jeffrey D,GBX, Combustion chamber comprising mixing ducts with fuel injectors varying in number and cross-sectional area.
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