US4012904A — Gas turbine burner

Claim 1

Independent Claim 355 words

In combination, a combustion system for minimizing localized concentrations of fuel and regions of high temperature combustion in lean combustible fuel-air mixtures for a gas turbine engine comprising first stage supply means for supplying first stage fuel and air at predetermined temperatures and rates to effect a lean preheated combustible first stage mixture when thoroughly mixed, first stage premixing means for receiving and thoroughly mixing said first stage fuel and air, a first stage combustion chamber for receiving the first stage fuel and air mixture from said premixing means, igniter means for igniting said mixture in said combustion chamber, ssecond stage supply means for supplying second stage fuel and air at predetermined temperatures and rates to effect a lean preheated mixture when thoroughly mixed that is comparatively cool with respect to the combustion products from said combustion chamber, second stage premixing means for receiving and thoroughly mixing said second stage fuel and air mixture, a second stage combustion chamber for receiving the combustion products from said first stage combustion chamber and also for receiving and burning therein said thoroughly mixed second stage fuel and air mixture, said second stage combustion chamber having upstream and downstream ends and a circular section transverse to the direction between said ends, said first and second stage supply means comprising a source of preheated air and a plurality of air ports in communication with said preheated air and extending angularly through the walls of said first and second stage premixing means to discharge said preheated air thereinto and to effect said thorough mixing of said fuel and preheated air within the corresponding premixing means, means for igniting said second stage mixture and for appreciably inhibiting the rate of NOx formation in said combustion products by quenching the temperature thereof comprising means for comingling said second stage mixture with said combustion products, the last named means comprising means for discharging said second stage mixture and combustion products into said second stage combustion chamber adjacent said upstream end and generally tangentially to the circular section of said second stage combustion chamber to impart a swirl to gas flow in the latter chamber.

Claim 2

Dependent Claim 355 words

In combination, a combustion system for minimizing localized concentrations of fuel and regions of high temperature combustion in lean combustible fuel-air mixtures for a gas turbine engine comprising first stage supply means for supplying first stage fuel and air at predetermined temperatures and rates to effect a lean preheated combustible first stage mixture when thoroughly mixed, first stage premixing means for receiving and thoroughly mixing said first stage fuel and air, a first stage combustion chamber for receiving the first stage fuel and air mixture from said premixing means, igniter means for igniting said mixture in said combustion chamber, ssecond stage supply means for supplying second stage fuel and air at predetermined temperatures and rates to effect a lean preheated mixture when thoroughly mixed that is comparatively cool with respect to the combustion products from said combustion chamber, second stage premixing means for receiving and thoroughly mixing said second stage fuel and air mixture, a second stage combustion chamber for receiving the combustion products from said first stage combustion chamber and also for receiving and burning therein said thoroughly mixed second stage fuel and air mixture, said second stage combustion chamber having upstream and downstream ends and a circular section transverse to the direction between said ends, said first and second stage supply means comprising a source of preheated air and a plurality of air ports in communication with said preheated air and extending angularly through the walls of said first and second stage premixing means to discharge said preheated air thereinto and to effect said thorough mixing of said fuel and preheated air within the corresponding premixing means, means for igniting said second stage mixture and for appreciably inhibiting the rate of NOx formation in said combustion products by quenching the temperature thereof comprising means for comingling said second stage mixture with said combustion products, the last named means comprising means for discharging said second stage mixture and combustion products into said second stage combustion chamber adjacent said upstream end and generally tangentially to the circular section of said second stage combustion chamber to impart a swirl to gas flow in the latter chamber.

Claim 3

Dependent Claim 37 words

In the combination according to claim 1, said first stage combustion chamber being dimensioned for combustion therein of a first stage mixture containing less than the quantity of fuel required for curb idle operation of said engine.

Claim 4

Dependent Claim 38 words

In the combination according to claim 1, said first stage combustion chamber being dimensioned to effect substantially complete combustion of the fuel therein in a limited short time interval determined by the tolerable NOx formation during said combustion.

Claim 5

Dependent Claim 80 words

In the combination according to claim 1, each supply means comprising means for supplying liquid fuel to its respective premixing means in a fine dispersion, each premixing means being dimensioned and the quantity and temperature of the air supplied thereto being predetermined for evaporating said fuel substantially completely therein prior to igniting the latter fuel, and each combustion chamber being dimensioned for substantially completing the combustion of the fuel therein prior to quenching the temperature of the combustion products thereof.

Claim 6

Dependent Claim 56 words

In the combination according to claim 1, second quenching means for appreciably inhibiting the rate of NOx formation in said second stage combustion chamber by quenching the temperature of the combustion products therein comprising means for comingling cooler third stage gases with the latter combustion products adjacent a downstream end of said second stage combustion chamber.

Claim 7

Dependent Claim 39 words

In the combination according to claim 5, said second stage air comprising approximately twice the first stage air, the third stage gases comprising the remaining air to said engine and amounting to approximately three times the second stage air.

Claim 8

Dependent Claim 82 words

In the combination according to claim 1, shroud means enclosing said premixing and reactor means and spaced therefrom to define a passage for said preheated air around said premixing and reactor means in heat exchange and thermal insulating relationship, said passage having an upstream end in communication with said preheated air adjacent the downstream end of said second stage combustion chamber to effect a counter flow of said preheated air around the latter with respect to the flow of combustion products therein.

Claim 9

Dependent Claim 229 words

In combination, a fixed geometry combustion system for minimizing localized concentrations of fuel and regions of high temperature combustion in lean combustible fuel-air mixtures for a gas turbine engine comprising a first stage premixer for receiving and thoroughly mixing therein a first stage supply of fuel and air, a first stage reactor for receiving and burning therein the first stage fuel and air mixture from said premixer, igniter means for igniting said mixture in said reactor, and first stage supply means for supplying first stage fuel and preheated air to said first stage premixer to effect a lean fuel to air ratio therein, said supply means comprising a plurality of air ports in communication with said preheated air and extending into said premixer for discharging the preheated air therein to swirl and shear said mixture therein, means for preventing upstream propagation of the combustion flame in said reactor comprising flame arresting means upstream of said igniter means, said flame arresting means comprising a tubular baffle of heat conducting material cooled with respect to the temperature of said combustion flame by conducting said preheated air therethrough, said tubular baffle having an inlet in communication with said preheated air to receive the same and having an outlet in communication with said premixer at a location upstream of said igniter means for discharging said preheated air into said premixer at said location.

Claim 10

Dependent Claim 229 words

In combination, a fixed geometry combustion system for minimizing localized concentrations of fuel and regions of high temperature combustion in lean combustible fuel-air mixtures for a gas turbine engine comprising a first stage premixer for receiving and thoroughly mixing therein a first stage supply of fuel and air, a first stage reactor for receiving and burning therein the first stage fuel and air mixture from said premixer, igniter means for igniting said mixture in said reactor, and first stage supply means for supplying first stage fuel and preheated air to said first stage premixer to effect a lean fuel to air ratio therein, said supply means comprising a plurality of air ports in communication with said preheated air and extending into said premixer for discharging the preheated air therein to swirl and shear said mixture therein, means for preventing upstream propagation of the combustion flame in said reactor comprising flame arresting means upstream of said igniter means, said flame arresting means comprising a tubular baffle of heat conducting material cooled with respect to the temperature of said combustion flame by conducting said preheated air therethrough, said tubular baffle having an inlet in communication with said preheated air to receive the same and having an outlet in communication with said premixer at a location upstream of said igniter means for discharging said preheated air into said premixer at said location.

Claim 11

Dependent Claim 288 words

In combination, a fixed geometry combustion system for minimizing localized concentrations of fuel and regions of high temperature combustion in lean combustible fuel-air mixtures for a gas turbine engine comprising first stage supply means for supplying first stage fuel and air to effect a combustible first stage mixture, a first stage reactor for receiving and substantially completely burning said first stage mixture therein, igniter means for igniting said mixture in said reactor, second stage supply means for supplying fuel and air at predetermined temperatures and rates to effect a lean preheated second stage mixture, premixing means for receiving said second stage mixture, said second stage supply means comprising a source of preheated air and a plurality of air ports of fixed dimensions in communication with said preheated air and extending angularly through the walls of said premixing means for discharging said preheated air thereinto for evaporating the fuel in said second stage mixture and thoroughly mixing the same with said preheated air within said premixing means, a combustion chamber for receiving the combustion products from said first stage reactor and also for receiving and burning therein the thoroughly mixed second stage mixture of air and evaporated fuel from said premixing means, said combustion chamber having an upstream inlet end and a downstream outlet end and a circular section transverse to the direction between said ends, and means for igniting said second stage mixture within said combustion chamber comprising means for discharging the latter mixture and combustion products into said combustion chamber for comingling therein, the last named means comprising means for discharging said second stage mixture into said combustion chamber generally tangentially to its circular section adjacent said upstream end for imparting a swirl to gas flow therein.

Claim 12

Dependent Claim 288 words

In combination, a fixed geometry combustion system for minimizing localized concentrations of fuel and regions of high temperature combustion in lean combustible fuel-air mixtures for a gas turbine engine comprising first stage supply means for supplying first stage fuel and air to effect a combustible first stage mixture, a first stage reactor for receiving and substantially completely burning said first stage mixture therein, igniter means for igniting said mixture in said reactor, second stage supply means for supplying fuel and air at predetermined temperatures and rates to effect a lean preheated second stage mixture, premixing means for receiving said second stage mixture, said second stage supply means comprising a source of preheated air and a plurality of air ports of fixed dimensions in communication with said preheated air and extending angularly through the walls of said premixing means for discharging said preheated air thereinto for evaporating the fuel in said second stage mixture and thoroughly mixing the same with said preheated air within said premixing means, a combustion chamber for receiving the combustion products from said first stage reactor and also for receiving and burning therein the thoroughly mixed second stage mixture of air and evaporated fuel from said premixing means, said combustion chamber having an upstream inlet end and a downstream outlet end and a circular section transverse to the direction between said ends, and means for igniting said second stage mixture within said combustion chamber comprising means for discharging the latter mixture and combustion products into said combustion chamber for comingling therein, the last named means comprising means for discharging said second stage mixture into said combustion chamber generally tangentially to its circular section adjacent said upstream end for imparting a swirl to gas flow therein.

Claim 13

Dependent Claim 38 words

In the combination according to claim 9, said first stage supply means comprising means for supplying said second stage mixture at temperatures and at fuel to air ratios proximate the minimum required for ignition in said combustion chamber.

Claim 14

Dependent Claim 42 words

In the combination according to claim 9, said reactor being dimensioned and said fuel to air ratio and the temperature of said first stage air being predetermined to effect substantially complete combustion in said reactor prior to igniting said second stage mixture.

Claim 15

Dependent Claim 94 words

In the combination according to claim 9, said first and second stage supply means cooperating with said first stage reactor and premixing means for swirling the mixtures therein and discharging the same in spiral swirls into said combustion chamber, the direction of the spiral swirls in said premixing means being predetermined to cooperate with the first named swirl in said combustion chamber for accelerating an axial downstream flow of said mixtures adjacent the periphery of said first named swirl and for inhibiting said axial downward flow adjacent the axial center of the latter swirl.

Claim 16

Dependent Claim 45 words

In the combination according to claim 9, means for appreciably inhibiting the rate of NOx formation in said combustion chamber comprising temperature quenching means for comingling cooler third stage gases with the combustion products in said combustion chamber adjacent a downstream end of the latter.

Claim 17

Dependent Claim 25 words

In the combination according to claim 13, said combustion chamber being dimensioned to effect substantially complete combustion of the fuel therein prior to said quenching.

Claim 18

Dependent Claim 54 words

In the combination according to claim 14, said second stage supply means comprising means for discharging a fine dispersion of second stage liquid fuel droplets into said premixing means, said premixing means being dimensioned to effect substantially complete evaporation of said droplets therein prior to discharging said second stage mixture into said combustion chamber.

Claim 19

Dependent Claim 33 words

In the combination according to claim 8, said baffle extending generally diametrically across the flow of said fuel and air mixture from said premixer to said reactor to impart turbulence to said flow.

Claim 20

Dependent Claim 21 words

In the combination according to claim 14, said third stage gases comprising the major portion of the total engine inlet air.

Claim 21

Dependent Claim 21 words

In the combination according to claim 14, said third stage gases comprising more than 70% of the total engine inlet air.

Claim 22

Dependent Claim 21 words

In the combination according to claim 13, said third stage gases comprising more than 70% of the total engine inlet air.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1980-03-21	1980-09-20	1981-03-22	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1984-03-21	1984-09-20	1985-03-22	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1988-03-21	1988-09-20	1989-03-22	$7700.00	Window Closed / Lapsed

Gas turbine burner

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