Burner for a gas turbine engine
AssigneeCaterpillar Inc.
InventorGregory A. Boardman
Life of this patent
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Abstract
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.
Claims20
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;
- and
- a 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.
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;
- and
- igniting said mixture of fuel and air.
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;
- and
- a fuel supply conduit positioned proximate an entrance portion of said mixing conduit.
Dependencies are inferred from the claim text.