Method for admixing combustion air in a burner

Claim 1

A method for admixing combustion air and oil in substantially stoichiometric proportions for combustion at a predetermined rate related to a specific rating R in 106 Btu/hr., said specific rating R corresponding to combustion air being supplied at a pressure of about 6 inches water column and at about 80*F, said method comprising the steps: passing said air tangentially through a plurality of overlapping vanes spaced around a hypothetical cylindrical surface coaxial with an oil atomizer and extending between first and second parallel walls perpendicular to the axis of said surface thereby to give the air an initial rotation, the diameter of said surface in inches being substantially equal to 4.23 (R + 1)1/2, the parallel walls being separated by a distance A in inches which is substantially equal to 2.69 (R + 1)1/2, the total minimum inlet area I between said vanes in square inches being substantially equal to 7.63 R, passing said rotating air spirally inwardly from said surface to the outer circular limit of a substantially 45* frusto-conical nozzle in said first wall coaxial with said surface, said outer circular limit in inches being substantially equal to 4.03 (R + 1)1/2, the inner circular limit of the frusto-conical nozzle being substantially equal to 2.45 R1/2, passing the spiralling air (a) radially inwardly adjacent said nozzle and (b) axially out through said nozzle into a substantially cylindrical combustion chamber coaxial with said nozzle and having a forward wall adjacent said nozzle and normal to the combustion chamber axis, and atomizing the oil at the said predetermined rate in the said atomizer centered within said nozzle, thereby to mix said air and said atomized oil in said combustion chamber.

Claim 2

A method for admixing combustion air and oil in substantially stoichiometric proportions for combustion at a predetermined rate related to a specific rating R in 106 Btu/hr., said specific rating R corresponding to combustion air being supplied at a pressure of about 6 inches water column and at about 80*F, said method comprising the steps: passing said air tangentially through a plurality of overlapping vanes spaced around a hypothetical cylindrical surface coaxial with an oil atomizer and extending between first and second parallel walls perpendicular to the axis of said surface thereby to give the air an initial rotation, the diameter of said surface in inches being substantially equal to 4.23 (R + 1)1/2, the parallel walls being separated by a distance A in inches which is substantially equal to 2.69 (R + 1)1/2, the total minimum inlet area I between said vanes in square inches being substantially equal to 7.63 R, passing said rotating air spirally inwardly from said surface to the outer circular limit of a substantially 45* frusto-conical nozzle in said first wall coaxial with said surface, said outer circular limit in inches being substantially equal to 4.03 (R + 1)1/2, the inner circular limit of the frusto-conical nozzle being substantially equal to 2.45 R1/2, passing the spiralling air (a) radially inwardly adjacent said nozzle and (b) axially out through said nozzle into a substantially cylindrical combustion chamber coaxial with said nozzle and having a forward wall adjacent said nozzle and normal to the combustion chamber axis, and atomizing the oil at the said predetermined rate in the said atomizer centered within said nozzle, thereby to mix said air and said atomized oil in said combustion chamber.

Claim 4

A method for admixing combustion air and fluid fuel in substantially stoichiometric proportions to permit stable combustion over a range of combustion air supply conditions including pressures above and below about 6 inches water column, there being a specific rating R in 106 Btu/hr. at a combustion air supply pressure of 6 inches water column and a combustion air supply temperature of 80*F which is related to a predetermined rating at the said supply conditions, said method comprising the steps: passing said combustion air, at a pressure and temperature in said range, tangentially through a plurality of overlapping vanes spaced around a hypothetical cylindrical surface coaxial with a fuel injector and extending between first and second parallel walls perpendicular to the axis of said surface thereby to give the air an initial rotation, the diameter of said surface in inches being substantially equal to 4.23 (R + 1)1/2, the parallel walls being separated by a distance A in inches whiCh is substantially equal to 2.69 (R + 1)1/2, the total minimum inlet area I between said vanes in square inches being substantially equal to 7.63 R, passing said rotating air spirally inwardly from said surface to the outer circular limit of a substantially 45* frusto-conical nozzle in said first wall coaxial with said surface, said outer circular limit in inches being substantially equal to 4.03 (R + 1)1/2, the inner circular limit of the frusto-conical nozzle being substantially equal to 2.45 R1/2, passing the spiralling air (a) radially inwardly adjacent said nozzle and (b) axially out through said nozzle into a substantially cylindrical combustion chamber coaxial with said nozzle and having a forward wall adjacent said nozzle and normal to the combustion chamber axis, and injecting the fluid fuel into the air at a rate which provides said substantially stoichiometric proportions, based on the quantity of combustion air entering the combustion chamber, said injection taking place centrally in said nozzle.

Claim 5

A method for admixing combustion air and fluid fuel in substantially stoichiometric proportions to permit stable combustion over a range of combustion air supply conditions including pressures above and below about 6 inches water column, there being a specific rating R in 106 Btu/hr. at a combustion air supply pressure of 6 inches water column and a combustion air supply temperature of 80*F which is related to a predetermined rating at the said supply conditions, said method comprising the steps: passing said combustion air, at a pressure and temperature in said range, tangentially through a plurality of overlapping vanes spaced around a hypothetical cylindrical surface coaxial with a fuel injector and extending between first and second parallel walls perpendicular to the axis of said surface thereby to give the air an initial rotation, the diameter of said surface in inches being substantially equal to 4.23 (R + 1)1/2, the parallel walls being separated by a distance A in inches whiCh is substantially equal to 2.69 (R + 1)1/2, the total minimum inlet area I between said vanes in square inches being substantially equal to 7.63 R, passing said rotating air spirally inwardly from said surface to the outer circular limit of a substantially 45* frusto-conical nozzle in said first wall coaxial with said surface, said outer circular limit in inches being substantially equal to 4.03 (R + 1)1/2, the inner circular limit of the frusto-conical nozzle being substantially equal to 2.45 R1/2, passing the spiralling air (a) radially inwardly adjacent said nozzle and (b) axially out through said nozzle into a substantially cylindrical combustion chamber coaxial with said nozzle and having a forward wall adjacent said nozzle and normal to the combustion chamber axis, and injecting the fluid fuel into the air at a rate which provides said substantially stoichiometric proportions, based on the quantity of combustion air entering the combustion chamber, said injection taking place centrally in said nozzle.

Claim 6

A method for admixing combustion air and fluid fuel in substantially stoichiometric proportions to permit stable combustion said method comprising the steps: passing said combustion air, at a maximum pressure of about 6 inches water column and at about 80*F, tangentially through a plurality of overlapping vanes spaced around a hypothetical cylindrical surface coaxial with a fuel injector and extending between first and second parallel walls perpendicular to the axis of said surface thereby to give the air an initial rotation, the diameter of said surface in inches being designated as a dimension D1, the parallel walls being separated by a distance A in inches which is substantially equal to 0.64 D1, the total minimum inlet area I between said vanes in square inches being substantially equal to 0.43 D12 -7.63, passing said rotating air spirally inwardly from said surface to an outer circular limit which is the largest circumference of a substantially 45* frusto-conical nozzle in said first wall coaxial with said surface, said nozzle having a largest circular diameter D2 in inches substantially equal to 0.95 D1, the smallest circular diameter D3 of the frusto-conical nozzle being substantially equal to (0.34 D12 - 6)1/2, passing the spiralling air (a) radially inwardly adjacent said nozzle and (b) axially out through said nozzle into a substantially cylindrical combustion chamber coaxial with said nozzle and having a forward wall adjacent said nozzle and normal to the combustion chamber axis, and injecting said fluid fuel through the said injector centered within said nozzle at a rate for stoichiometric combustion with the combustion air, based on the rate at which the air enters the combustion chamber.

Claim 7

A method for admixing combustion air and fluid fuel in substantially stoichiometric proportions to permit stable combustion said method comprising the steps: passing said combustion air, at a maximum pressure of about 6 inches water column and at about 80*F, tangentially through a plurality of overlapping vanes spaced around a hypothetical cylindrical surface coaxial with a fuel injector and extending between first and second parallel walls perpendicular to the axis of said surface thereby to give the air an initial rotation, the diameter of said surface in inches being designated as a dimension D1, the parallel walls being separated by a distance A in inches which is substantially equal to 0.64 D1, the total minimum inlet area I between said vanes in square inches being substantially equal to 0.43 D12 -7.63, passing said rotating air spirally inwardly from said surface to an outer circular limit which is the largest circumference of a substantially 45* frusto-conical nozzle in said first wall coaxial with said surface, said nozzle having a largest circular diameter D2 in inches substantially equal to 0.95 D1, the smallest circular diameter D3 of the frusto-conical nozzle being substantially equal to (0.34 D12 - 6)1/2, passing the spiralling air (a) radially inwardly adjacent said nozzle and (b) axially out through said nozzle into a substantially cylindrical combustion chamber coaxial with said nozzle and having a forward wall adjacent said nozzle and normal to the combustion chamber axis, and injecting said fluid fuel through the said injector centered within said nozzle at a rate for stoichiometric combustion with the combustion air, based on the rate at which the air enters the combustion chamber.