A burner for a gas turbine including a burner housing is provided. Provided is a lean-rich partially premixed low emission burner for a gas turbine combustor providing stable ignition and combustion process at all engine load conditions. At the upstream end of that burner a pilot combustor creates a
A burner for a gas turbine including a burner housing is provided. Provided is a lean-rich partially premixed low emission burner for a gas turbine combustor providing stable ignition and combustion process at all engine load conditions. At the upstream end of that burner a pilot combustor creates a flow of an unquenched concentration of radicals and heat. Respectively provided is a plurality of quarl sections surrounding the exit of the pilot combustor, a main combustion room defined downstream the pilot combustor and at least a first channel defined as an annular space between an upstream quarl section and the closest downstream quarl section providing air and fuel to a main flame in the combustion room.
대표청구항▼
1. A burner for a gas turbine engine, comprising: a burner housing in which the burner is enclosed, the burner having axially opposed upstream and downstream end portions;a pilot combustor disposed at the upstream end of the burner;a plurality of quarl sections surrounding an exit of the pilot combu
1. A burner for a gas turbine engine, comprising: a burner housing in which the burner is enclosed, the burner having axially opposed upstream and downstream end portions;a pilot combustor disposed at the upstream end of the burner;a plurality of quarl sections surrounding an exit of the pilot combustor and extend from the exit in a downstream direction;a main combustion room is defined downstream from the pilot combustor by end portions of the plurality of quarls; anda first channel defined as a substantially annular space between an upstream quarl section, first quarl section, and the closest downstream quarl section, second quarl section, providing air and fuel to a main flame in the main combustion room,wherein the pilot combustor is provided with fuel and air for burning the fuel and is sized to effect creation of a first flow of an unquenched concentration of radicals at non-equilibrium and heat from a pilot combustion zone directed downstream along a centre line of the pilot combustor through a throat at the exit of the pilot combustor, wherein less fuel is supplied to the pilot combustor than to the main combustion room,wherein an outer quarl section, second quarl section, includes a greater first diameter than an second diameter of an inner quarl section, first quarl section,wherein the outer quarl section, second quarl section, extends a greater distance downstream than the inner quarl, first quarl section, andwherein the main combustion room is arranged to house the main flame and a recirculation zone for directing a second flow of free radicals back to a forward stagnation point at the exit of the pilot combustor. 2. The burner as claimed in claim 1, wherein a first swirler is arranged at a first inlet of the first channel for generating a swirl of fuel and air in the first channel. 3. The burner as claimed in claim 2, wherein a second channel is defined as a substantially annular space between the second quarl section and a third quarl section. 4. The burner as claimed in claim 3, wherein the first swirler is arranged across both the first inlet of the first channel and a second inlet of the second channel, andwherein the first swirler generates a swirl of fuel and air in the first and second channels. 5. The burner as claimed in claim 3, wherein a third annular channel for providing premixed air and fuel to the main flame is the second channel and is located downstream of the first channel. 6. The burner as claimed in claim 5, wherein the pilot combustor is substantially surrounded by a perforated plate,wherein cooling air is provided through a cooling air inlet for penetrating the perforated plate and for cooling a plurality of side walls of the pilot combustor,wherein the cooling air is let through a second swirler arranged around a fourth quarl of the pilot combustor,wherein fuel is added through a fuel duct and directed through the second swirler, andwherein the cooling air and the added fuel is premixed in the second swirler and provided to the main flame at the exit of the pilot combustor. 7. The burner as claimed in claim 2, wherein an imparted level of swirl is arranged such that a swirl number is above 0.6 and not higher than 0.8. 8. The burner as claimed in claim 1, wherein a quarl half angle is above 20 degrees and below 25 degrees. 9. The burner as claimed in claim 8, wherein a length/diameter of the quarl is greater than 0.5, andwherein the length/diameter of the quarl is less than 2. 10. The burner as claimed in claim 9, wherein the length/diameter of the quarl equals 1. 11. The burner as claimed in claim 1, wherein premixed air and fuel is added to the main flame from a plurality of annular channels distributed along the downstream direction of the main flame. 12. The burner as claimed in claim 11, wherein a first annular channel of the plurality of annular channels for the provision of premixed air and fuel to the main flame is arranged around the exit of the pilot combustor at an upstream end of the main flame, andwherein a second annular channel is the first channel and is located further downstream. 13. The burner as claimed in claim 1, wherein the pilot combustor is substantially surrounded by a perforated plate,wherein cooling air is provided through a cooling air inlet for penetrating the perforated plate and for cooling a plurality of side walls of the pilot combustor,wherein the cooling air is in a heated state supplied to the main flame, andwherein the heated cooling air is released around a fourth quarl of the pilot combustor thereby supplying the heated cooling air to the main flame at the most upstream end of the main flame. 14. The burner as claimed in claim 1, wherein the pilot combustor is substantially surrounded by a perforated plate,wherein cooling air is provided through a cooling air inlet for penetrating the perforated plate and for cooling a plurality of side walls of the pilot combustor,wherein the cooling air is in a heated state supplied to the main flame, andwherein the heated cooling air is let out into the first channel thereby introduced to the main flame from the first channel running through one of the first quarl, the second quarl, or a third quarl defining a combustion room housing a combustion process. 15. The burner as claimed in claim 1, wherein the pilot combustor is substantially surrounded by a perforated plate,wherein cooling air is provided through a cooling air inlet for penetrating the perforated plate and for cooling a plurality of side walls of the pilot combustor,wherein the cooling air is in a heated state supplied to the main flame, andwherein the cooling air is provided to a main lean partially premixed combustion process whereby the cooling air is a mixture of: the heated cooling air that is released around the fourth quarl of the pilot combustor thereby supplying the heated cooling air to the main flame at the most upstream end of the main flame; andthe heated cooling air that is let out into the first channel thereby introduced to the main flame from the first channel running through one of the first quarl, the second quarl, or a third quarl defining a combustion room housing a combustion process. 16. The burner as claimed in claim 1, wherein the pilot combustor includes a fuel inlet for fuel and an air inlet for air, andwherein the fuel and the air is ignited with an igniter for creating a pilot combustor flame. 17. The burner as claimed in claim 1, wherein the pilot combustor has a surface area that is sized to provide flame quenching in the pilot combustor. 18. The burner as claimed in claim 1, wherein the pilot combustor is configured to burn up to 1% of a total fuel flow. 19. The burner as claimed in claim 1, wherein the main combustion room is configured to burn more than 90% of a total fuel flow.
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이 특허에 인용된 특허 (8)
Jorgensen Robert A. (Clifton Park NY) Farrell Roger A. (Schenectady NY) Gerhold Bruce W. (Rexford NY), Dual stage-dual mode low emission gas turbine combustion system.
Richard Sterling Tuthill ; William Theodore Bechtel, II ; Jeffrey Arthur Benoit ; Stephen Hugh Black ; Robert James Bland ; Guy Wayne DeLeonardo ; Stefan Martin Meyer ; Joseph Charles Taura ;, Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion.
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