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Mtu Motoren-und Turbinen-union Munchen Gmbh

Thomas Ripplinger

Nikolaos Zarzalis

Bernhard Glaeber

Burkhard Simon

Nikoloas Zarzalis

The invention relates to a burner for combustors of gas turbines, the burner having an atomizer nozzle for atomisation of fuel in the combustion air and having a primary and secondary flow channel. In the burners, mostly used in aircraft engines, an extensively homogenous distribution of the air-fuel mixture is to be achieved in the combustor to reduce emissions. The flow channels opening into the combustor are separated from a first component arranged concentrically in relation to the burner axis and having a sleeve-shaped atomizer lip extending cylindrically or conically, and the external secondary flow channel is bounded externally and radially by a second annular component arranged concentrically and having an internal wall extending to converge and diverge. The second component forms an area with the most narrow flow cross-section, and the first component is arranged radially inwards and ends with the atomizer lip at the axial height of the cross-section or upstream thereof. The air flow flows through the flow channels to twist in the same direction. By positioning the atomizer lip at the narrowest flow cross-section in the or just in front of the atomizer nozzle, the fuel can be atomized in a range of the maximum air shear forces with the result that there can be optimal atomization.

Burner with atomizer nozzle

A pre-mixing combustion chamber (,) for a gas turbine is disclosed which includes a main stage with at least one pre-mixing chamber and a combustion chamber fashioned at least partly dynamically balanced relative to its longitudinal axis with a main combustion zone (,) and an after-combustion zone (,) placed downstream, whereby the at least one pre-mixing chamber discharges into the combustion chamber in the region of the main combustion zone tangentially producing twisting action. The pre-mixing chamber also includes a pilot stage (,) with a pilot injection means, whereby the main combustion zone in the combustion chamber proceeds essentially coaxial to the after-combustion zone, and the pilot stage is arranged at that end of the combustion chamber remote from the after-combustion zone.

Tangentially aligned pre-mixing combustion chamber for a gas turbine

A combustion chamber apparatus 1 for a gas turbine has a pilot stage and a main stage for low-emission lean-burn operation. The pilot stage is separate from the main stage and is formed by a flame tube 2 with an upstream first fuel injector 3a and with a secondary combustion zone 7a. The main stage includes a vaporization chamber 4 and a combustion chamber 5, and a second fuel injector 3b is provided at an upstream end of the vaporization chamber 4. The vaporization chamber 4 produces a homogenous fuel-air mixture which will not burn until it is in the combustion chamber 5. In lean-burn operation of the apparatus, the separate arrangement of the two chambers 4, 5 significantly reduces the formation of nitrogen oxides. For use in aircraft gas turbine engines, the apparatus has an annular shape with several main and pilot stages.

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Vierkirchen, Germany

Thomas Ripplinger