Method of using segmented gas burner with gas turbines
AssigneeAlzeta Corporation
InventorsRobert M. Kendall, Scott H. Smith
Life of this patent
Estimating the term…
Abstract
A segmented radiant gas burner features wide modulation of thermal output simply by the independent control of fuel gas flow to each burner segment. The burner also features a porous fiber burner face, preferably having dual porosities, and a metal liner positioned to provide a compact combustion zone adjacent the burner face. The segmented radiant burner is ideally suited for use with gas turbines not only because of its compactness and broad thermal modulation but also because only the flow of fuel gas to each burner segment requires control while the flow of compressed air into all segments of the burner remains unchanged.
Claims15
A combustion method for gas turbines to suppress the formation of combustion air pollutants, which comprises passing compressed air through and around a segmented burner having at least two plenums with fixed inlet openings, said plenums having porous fiber burner faces, independently controlling the injection of fuel gas into each of said fixed openings, said injection of fuel gas being controlled to provide high excess air to maintain during firing of any burner face an adiabatic flame temperature for that burner face in the range of about 2600° F. to 3300° F., and confining combustion in a compact combustion zone adjacent said burner faces with a metal liner.
A combustion method for gas turbines to suppress the formation of combustion air pollutants which comprises passing air at a pressure of at least 3 atmospheres through and around a segmented burner having at least two segments, each having a plenum provided with a fixed inlet opening and a porous metal fiber mat with interspersed perforations as a burner face, independently controlling the injection of fuel gas to mix with high excess air to maintain during firing of each segment an adiabatic flame temperature in the range of about 2600° F. to 3300° F. and confining combustion in a compact combustion zone adjacent said burner faces with a louvered metal liner or backside-cooled liner.
A method of modulating the thermal input of a gas turbine, which comprises the steps of (1) using a segmented burner with at least two plenums, each having a fixed opening to compressed air flow and having a segment of a porous fiber burner face of said segmented burner, (2) directing a flow of compressed air simultaneously into all of said plenums and around said segmented burner, (3) injecting fuel gas into a first plenum at a rate to form therein a fuel gas-air mixture having about 40% to 150% excess air, (4) firing said fuel gas-air mixture exiting said first plenum to effect radiant surface combustion, and when increased thermal input is required, (5) injecting fuel gas into a second plenum at a rate specified in step (3) to form a fuel gas-air mixture that on exiting said second plenum will be fired as additional radiant surface combustion.
Dependencies are inferred from the claim text.