Combustor including a cyclone prechamber and combustion process for gas turbines fired with liquid fuel

Claim 2

A combustion apparatus for a gas turbine engine comprising, in combination: (a) a combustion liner defining a combustion chamber terminating at its upstream end in an inlet throat and termination downstream of said throat in an outlet for exhausting combustion gases, (b) a cyclonic prechamber assembly including (i) a cyclonic prechamber adapted to vaporize liquid fuel therein, said prechamber being substantially cylindrical through at least a portion of its axial extent, terminating at its downstream end in said throat, and opening to said combustion chamber through the throat; (ii) a plurality of converging, spaced-apart highly-angled vanes disposed circumferentially about the cylindrical portion of said prechamber such that the ratio of "total chamber flow area" to the cylindrical area of said prechamber is from about 0.05:1 to about 0.5:1, with opposing faces of each pair of adjacent vanes defining inwardly converging airflow channels adapted to introduce air therethrough with a high tangential component of velocity into the prechamber; (c) means in flow communication with the upstream end of said prechamber for introducing liquid fuel with a spray pattern in the form of a substantially hollow cone coaxial with said prechamber and having a vertex angle sufficiently large such that the introduced fuel is directed toward an upstream portion of each vane and not toward said throat opening, and (d) an ignitor in said combustion chamber for igniting fuel vapor received in premixed form from said prechamber.

Claim 3

The apparatus of claim 1, wherein said plurality of vanes is free of airflow channel-defining members adjacent the outer envelope containing the leading edges of said vanes.

Claim 4

The apparatus of claim 1, wherein each pair of adjacent vanes defines a "vane angle" of from about 60° to 90°.

Claim 5

The apparatus of claim 1, wherein the number of said vanes per one inch of diameter of the prechamber is at least 2.

Claim 6

The apparatus of claim 1, wherein the ratio of the "total channel flow area" to the cylindrical area of said prechamber is from about 0.1:1 to about 0.4:1.

Claim 7

A process for generating combustion products from liquid fuel for operating a gas turbine comprising (a) heating and pressurizing air; (b) flowing the air resulting from step (a) through swirl-inducing members into a pre-chamber so as to impart substantial tangential velocity thereto during both start-up of combustion and during the continuous operating regime, (c) supplying liquid fuel in a spray pattern in the form of a substantially hollow cone coaxial with the pre-chamber, said cone having a vertex angle sufficiently large such that the introduced fuel is directed toward the swirl-inducing members, (d) mixing the liquid fuel and air and vaporizing a portion of the liquid fuel in the pre-chamber while impinging liquid fuel droplets greater than a predetermined size upon the swirl-inducing members, returning the deposited liquid fuel to the swirling mixture to effect additional vaporization of the returned liquid fuel, (e) intimately mixing the vaporized fuel with the swirling air, (f) discharging the intimately mixed vaporized fuel mixture through a throat into a combustion chamber, (g) burning the fuel in the combustion chamber and controlling the relative proportions of supplied fuel and flowed air so as to maintain a constantly lean overall ratio of fuel to air throughout the operating regime, and (h) concurrently controlling the tangential velocity of the air entering into the pre-chamber so as to insure vaporization and substantially homogeneous mixing of the fuel vapor with the air and to insure a sufficiently short elapsed time from formation of the fuel vapor to discharge of the mixture thereof with air into the combustion chamber such that auto ignition of the fuel is substantially prevented in the pre-chamber and formation of NOX during combustion is substantially reduced.

Claim 8

A process for generating combustion products from liquid fuel for operating a gas turbine comprising (a) heating and pressurizing air; (b) flowing the air resulting from step (a) through swirl-inducing members into a pre-chamber so as to impart substantial tangential velocity thereto during both start-up of combustion and during the continuous operating regime, (c) supplying liquid fuel in a spray pattern in the form of a substantially hollow cone coaxial with the pre-chamber, said cone having a vertex angle sufficiently large such that the introduced fuel is directed toward the swirl-inducing members, (d) mixing the liquid fuel and air and vaporizing a portion of the liquid fuel in the pre-chamber while impinging liquid fuel droplets greater than a predetermined size upon the swirl-inducing members, returning the deposited liquid fuel to the swirling mixture to effect additional vaporization of the returned liquid fuel, (e) intimately mixing the vaporized fuel with the swirling air, (f) discharging the intimately mixed vaporized fuel mixture through a throat into a combustion chamber, (g) burning the fuel in the combustion chamber and controlling the relative proportions of supplied fuel and flowed air so as to maintain a constantly lean overall ratio of fuel to air throughout the operating regime, and (h) concurrently controlling the tangential velocity of the air entering into the pre-chamber so as to insure vaporization and substantially homogeneous mixing of the fuel vapor with the air and to insure a sufficiently short elapsed time from formation of the fuel vapor to discharge of the mixture thereof with air into the combustion chamber such that auto ignition of the fuel is substantially prevented in the pre-chamber and formation of NOX during combustion is substantially reduced.

Claim 9

The process of claim 6 wherein the liquid fuel is supplied to the pre-chamber in atomized condition.

Claim 10

The process of claim 6, wherein the fuel is supplied at a location in the pre-chamber substantially coaxial therewith and coplanar with an upstream end region of the swirl-inducing members wherein upstream refers to location on the axis which extends downstream axially from the location of fuel introduction, said cone having a vertex angle of at least 120° or more.