IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0188596
(2005-07-25)
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등록번호 |
US-7581396
(2009-09-16)
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발명자
/ 주소 |
- Hsieh, Shih Yang
- Hsiao, George Chia Chun
- Li, Shui Chi
- Mongia, Hukam Chand
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출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
21 인용 특허 :
9 |
초록
▼
A mixer assembly for use in a combustor of a gas turbine engine, including a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and the main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the
A mixer assembly for use in a combustor of a gas turbine engine, including a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and the main mixer. The pilot mixer further includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the pilot housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing. The main mixer further includes a main housing surrounding the pilot housing and defining an annular cavity, a plurality of fuel injection ports for introducing fuel into the cavity, and a swirler arrangement including at least three swirlers positioned upstream from the plurality of fuel injection ports, wherein each swirler of the swirler arrangement has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the fuel injection ports. The swirlers are oriented substantially radially to a centerline axis through the mixer assembly or at an acute angle to the centerline axis through the mixer assembly. Alternatively, at least two swirlers are included substantially parallel to the centerline axis through the mixer assembly along with one or more radial or conical swirlers. In another alternative, the swirler arrangement includes a first swirler oriented substantially parallel to a centerline axis through the mixer assembly, a second swirler oriented at an acute angle to the centerline axis through the mixer assembly, and a third swirler oriented substantially radially to the centerline axis through the mixer assembly.
대표청구항
▼
What is claimed is: 1. A mixer assembly for use in a combustion chamber of a gas turbine engine, comprising: (a) a pilot mixer including an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in said pilot housing and adapted for dispensing droplets of fuel to said hollow
What is claimed is: 1. A mixer assembly for use in a combustion chamber of a gas turbine engine, comprising: (a) a pilot mixer including an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in said pilot housing and adapted for dispensing droplets of fuel to said hollow interior of said pilot housing; (b) a main mixer including: (1) a main housing surrounding said pilot housing and defining an annular cavity; (2) a plurality of fuel injection ports for introducing fuel into said cavity; (3) a swirler arrangement including at least first, second, and third swirlers positioned upstream from said fuel injection ports, said first swirler positioned axially upstream of said second swirler and said third swirler positioned axially downstream of said second swirler, wherein each swirler of said swirler arrangement is oriented substantially radially to a centerline axis through said mixer assembly and has a plurality of vanes for swirling air traveling through such swirler to mix air and said droplets of fuel dispensed by said fuel injection ports; and, (c) a fuel manifold positioned between said pilot mixer and said main mixer, wherein said plurality of fuel injection ports for introducing fuel into said main mixer cavity are in flow communication with said fuel manifold. 2. The mixer assembly of claim 1, wherein said first and third swirlers swirl air in a first direction and said second swirler swirls air in a direction opposite said first direction. 3. The mixer assembly of claim 1, wherein vanes of said third swirler have a length greater than vanes of said second swirler. 4. The mixer assembly of claim 1, wherein vanes of said first swirler have a length grater than vanes of said second swirler. 5. The mixer assembly of claim 1, wherein vanes of said first swirler are oriented at an angle of approximately 20-70° with respect to a centerline axis through said swirler arrangement, vanes of said second swirler are oriented at an angle of approximately 0-60° with respect to said centerline axis through said swirler arrangement, and vanes of said third swirler are oriented at an angle of approximately 20-70° with respect to said centerline axis through said swirler arrangement. 6. The mixer assembly of claim 1, wherein vanes of said first, second and third swirlers are substantially aligned circumferentially with respect to a centerline axis through said swirler arrangement. 7. The mixer assembly of claim 1, wherein vanes of said first, second and third swirlers are not substantially aligned circumferentially with respect to a centerline axis through said swirler arrangement. 8. The mixer assembly of claim 1, at least one swirler of said swirler arrangement further comprising: (a) a first plurality of vanes oriented at a first angle with respect to a centerline axis through said swirler arrangement; and, (b) a second plurality of vanes oriented at a second angle with respect to said swirler arrangement centerline axis; wherein a first type of passage is defined between adjacent vanes having a first configuration and a second type of passage is defined between adjacent vanes having a second configuration. 9. The mixer assembly of claim 8, wherein each of said first plurality of vanes is oriented at an angle of approximately 0-60° with respect to said swirler arrangement centerline axis. 10. The mixer assembly of claim 8, wherein each of said second plurality of vanes is oriented at an angle of approximately 0-60° with respect to said swirler arrangement centerline axis. 11. The mixer assembly of claim 1, wherein an intense mixing region is created which is substantially centered radially within said annular cavity of said main mixer. 12. The mixer assembley of claim 11, wherein said intense mixing region is located axially adjacent said fuel injection ports. 13. A method of operating a gas turbine engine combustor with reduced emissions, wherein said combustor includes a plurality of mixer assemblies having a pilot mixer and a main mixer, comprising the following steps: (a) providing a plurality of fuel injection ports in flow communication with an annular cavity of each said main mixer; (b) providing a swirler arrangement in flow communication with said annular cavity of each said main mixer, said swirler arrangement including at least first, second, and third swirlers positioned upstream of said fuel injection ports and oriented substantially radially to a centerline axis through each said mixer assembly, said first swirler positioned axially upstream of said second swirler and said third swirler positioned axially downstream of said second swirler, wherein an intense mixing region is created adjacent a said plurality of fuel injection ports to said annular cavity; (c) causing air supplied to each said swirler arrangement to swirl in a counter-rotating manner in said annular cavity; (d) allocating air supplied to each said swirler arrangement among each swirler thereof in a predetermined amount, and, (e) providing fuel from said fuel injection ports into said intense mixing region.
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