[특허]Burner for a gas turbine engine

[미국특허] Burner for a gas turbine engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F23R-003/16
출원번호	US-0791490 (2004-03-02)
발명자 / 주소	Boardman, Gregory A.
출원인 / 주소	Caterpillar Inc.
인용정보	피인용 횟수 : 61 인용 특허 : 4

초록 ▼

To meet emissions standards, many gas turbine engines use some form of lean, pre-mixed combustion systems. These systems may lead to combustion oscillations or other instabilities. Jet combustion techniques provide a stable alternative lean, pre-mixed combustion system. The present invention presents a jet combustion system that includes a first cylinder having a first array of orifices. A second cylinder is positioned coaxially with the first cylinder. The second cylinder has a second array of orifices offset from the first array of orifices.

대표청구항 ▼

1. A fuel burner for a gas turbine engine disposed about a central axis, said fuel burner comprising:a first cylinder having a first upstream open end portion and a second downstream closed end portion, said first cylinder having first array of orifices disposed between said first end portion and said second end portion, said first cylinder being disposed about said central axis; anda second cylinder having a first end portion and a second closed end portion, substantially parallel to the closed end of said first cylinder, said second cylinder having a second array of orifices disposed between said first end portion and said second end portion, said second cylinder being coaxial with said first cylinder,said first cylinder being disposed between said second cylinder and said central axis,said first array of orifices being offset axially and/or tangentially from said second array of orifices.2. The fuel burner of claim 1 wherein said first array of orifices have a smaller diameter than said second array of orifices.3. The fuel burner of claim 1 wherein said first array of orifices have diameters varying as a function of an axial position along said central axis.4. The fuel burner of claim 3 wherein said function increases said diameters as said axial position moves along said central axis.5. The fuel burner of claim 1 wherein a gap between said first cylinder and said second cylinder changes along said central axis.6. The fuel burner of claim 1 including a mixing conduit having an entrance portion, said mixing conduit being connected with said first end portion of said first cylinder distal from said entrance portion.7. The fuel burner of claim 6 including a fuel supply line positioned proximate said entrance portion of said mixing conduit.8. The fuel burner of claim 7 including a plurality of vortex generator tabs intermediate said fuel supply tube and said first end portion of said first cylinder.9. The fuel burner of claim 7 including a second fuel supply line being positioned adjacent said first end portion of said second cylinder, said second cylinder being disposed between said second fuel supply line and said first cylinder.10. The fuel burner of claim 1 including a circulating device positioned in the first cylinder to circulate the mixture of fuel and air.11. A method of burning a fuel in a gas turbine engine, comprising:supplying a mixture of fuel and air to a first cylinder having an upstream open end and a downstream closed end;flowing said mixture of fuel and air through a first array of orifices in said first cylinder;reducing a pressure of said mixture of fuel and air;impinging a second cylinder positioned radially outward said first cylinder with said mixture of fuel and air; said second cylinder having a closed end substantially parallel to said closed end of said first cylinder;transferring heat from said second cylinder to said mixture of fuel and air during said impinging;mixing further said mixture of fuel and air after said transferring;passing said mixture of fuel and air through a second array of orifices in said second cylinder; said second array of orifices being axially and/or tangentially offset from said first array orifices; andigniting said mixture of fuel and air.12. The method of burning fuel of claim 11 wherein said further mixing includes increasing turbulent mixing in a gap between said first cylinder and said second cylinder.13. The method of burning fuel of claim 11 wherein said mixture of fuel and air impinging said second cylinder substantially perpendicular.14. The method of burning fuel of claim 11 wherein said igniting step is supplying a diffusion flame to said mixture of fuel and air.15. The method of burning fuel of claim 14 wherein a majority of a pressure reduction occurs through the first array of orifices.16. A combustion system for a gas turbine engine, said combustion system comprising:a combustor liner;a first cylinder having an upstream open end and a downstream closed end, and positioned inside the combustor liner;a second closed end cylinder positioned between said first cylinder and said combustion liner, said second cylinder being coaxial with said first cylinder, and the closed end of said second cylinder being substantially parallel to the close end of said first cylinder;a first array of orifices disposed through said first cylinder;a second array of orifices disposed through said second cylinder, said second array of orifices being substantially axially and/or tangentially offset from said first array of orifices;a mixing conduit fluidly connecting with said first cylinder; anda fuel supply conduit positioned proximate an entrance portion of said mixing conduit.17. The combustion system of claim 16 including a fluid mixing means for mixing the fuel and air in said mixing conduit.18. The combustion system of claim 17 wherein said mixing means includes vortex generator tabs.19. The combustion system of claim 16 including a slot adjacent a first end portion of said second cylinder, said slot containing a plurality of fuel supply orifices, said pilot fuel supply orifices being connected with a fuel gallery.20. The combustion system of claim 16 including a circulating device positioned proximate a second end portion of said second cylinder.

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[미국특허] Burner for a gas turbine engine 원문보기

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