Dilution pole combustor and method

• US 5,239,818 A
• Filed: 03/30/1992
• Issued: 08/31/1993
• Est. Priority Date: 03/30/1992
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: MacHolloway, Gary, Loconti, Craig L., Stickles, Richard W., Dodds, Willard J., Cook, George E., Sabla, Paul E.
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): Thorpe, Timothy S.
• Application Number:
  US07/860,635
• Time in Patent Office: 519 Days
• Field of Search: 60/39.36, 60/732, 60/747, 60/759, 60/738
• US Class Current: 60/804
• CPC Class Codes: F23R 3/04 Air inlet arrangements
• CPC Class Codes: F23R 3/16 with devices inside the flame tube or the combustion chamber to influence the air or gas flow
• CPC Class Codes: F23R 3/34 Feeding into different combustion zones
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An annular combustor includes a plurality of circumferentially spaced, radially extending dilution poles disposed in an intermediate zone thereof between a forward combustion zone and an aft combustion zone. Adjacent ones of the dilution poles define therebetween a throat for receiving the combustion gases from the forward zone. The dilution poles include circumferentially facing dilution holes for injecting dilution air into the throats for mixing with the combustion gases being channeled therethrough. The dilution poles are effective for blocking the combustion gases at a plurality of circumferentially spaced apart locations and accelerating the combustion gases through the throats for reducing residence time in the throat. The dilution air is injected through the dilution holes for improved penetration into the combustion gases in the throats for mixing therewith to form lean combustion gases which undergo final combustion in the aft zone for reducing NO_x emissions.

Claims

1. In a gas turbine engine annular combustor having a longitudinal centerline axis, outer and inner annular liners spaced radially apart coaxially about said centerline axis to define an annular combustion chamber therebetween, an annular dome at upstream ends of said liners having a plurality of circumferentially spaced apart carburetors for providing a fuel/air mixture into said combustion chamber to generate combustion gases therein, and an annular outlet defined at downstream ends of said liners for discharging said combustion gases, a method comprising:

channeling said fuel/air mixture axially through said dome into said combustion chamber to generate said combustion gases;

blocking flow of said combustion gases at a plurality of circumferentially spaced apart locations at an axial position spaced axially downstream from said dome and spaced axially upstream from said outlet to define an intermediate zone disposed axially between a forward zone extending upstream therefrom to said dome, and an aft zone extending downstream therefrom to said outlet, and radially between said outer and inner liners to accelerate said combustion gases between said blocking locations in a plurality of circumferentially spaced apart throats;

injecting dilution air into said combustion gases being channeled through said throats and radially between said outer and inner liners

channeling said combustion gased through said forward zone with a rich equivalence ratio; and

wherein said injecting step mixes said dilution air with said combustion gases being channeled through said throats to quench said combustion gases channeled to said aft zone to a lean equivalence ratio.

2. A method according to claim 1 wherein said blocking step provides a plurality of circumferentially spaced apart flame stabilization zones in said aft zone.

3. A method according to claim 2 wherein said combustion gases are accelerated in velocity in said intermediate zone to about twice the velocity of said combustion gases in said forward zone.

4. A gas turbine engine annular combustor having a longitudinal centerline axis comprising:

outer and inner annular liners disposed coaxially about said centerline axis and spaced radially apart to define an annular combustion chamber therebetween;

an annular, axially aft facing dome fixedly joined to upstream ends of said outer and inner liners, and downstream ends of said outer and inner liners defining therebetween an annular outlet;

a plurality of circumferentially spaced apart carburetors disposed in said dome for providing a fuel/air mixture axially through said dome into said combustion chamber to generate combustion gases flowable axially therethrough from said dome to said outlet and dischargeable through said outlet;

a plurality of circumferentially spaced apart dilution poles extending radially between said outer and inner liners at an axial position spaced axially downstream from said dome and spaced axially upstream from said outlet to define an intermediate zone disposed axially between a forward combustion zone extending upstream therefrom to said dome, and an aft combustion zone extending downstream therefrom to said outlet, said poles also defining circumferentially between adjacent ones thereof radially extending throats for axially accelerating said combustion gases from said forward zone and into said intermediate zone;

each of said poles including circumferentially opposite sides and at least one dilution hole in each of said sides for injecting dilution air circumferentially into said combustion gases being channeled through said throats and radially between said outer and inner liners and

said carburetors being sized for providing said fuel/air mixture into said forward combustion zone with a rich equivalence ratio, and said dilution hole being effective to inject said dilution air to quench said combustion gases to a lean equivalence ratio.

5. A combustor according to claim 4 wherein each of said dilution poles includes:

radially extending leading and trailing edges joining together said pole opposite sides, and an inlet aperture at a proximal end thereof for first receiving said dilution air, and being disposed in flow communication with said dilution holes; and

said pole opposite sides being substantially planar between said leading and trailing edges, and said dilution holes being disposed in said pole opposite sides between said leading and trailing edges for injecting said dilution air circumferentially toward adjacent ones of said dilution poles.

6. A combustor according to claim 5 further including:

a plurality of said dilution holes spaced radially apart in each of said dilution pole opposite sides; and

said dilution holes of adjacent ones of said poles being radially aligned at least in part with each other for collectively injecting said dilution air into said throats without radial interruption therebetween.

7. A combustor according to claim 6 wherein said dilution poles are equiangularly spaced apart from each other.

8. A combustor according to claim 7 wherein each of said carburetors includes a fuel injector axially aligned between adjacent ones of said dilution poles and spaced upstream therefrom.

9. A combustor according to claim 6 wherein each of said dilution poles includes a hollow impingement baffle therein spaced from an inside surface of said dilution pole and disposed in flow communication with said pole inlet aperture, said baffle including a plurality of impingement holes for injecting said dilution air received from said inlet aperture in impingement against said pole inside surface, said dilution holes being disposed in flow communication with said impingement holes for discharging into said throats said dilution air first used for impingement cooling of said dilution pole.

10. A combustor according to claim 6 wherein said dilution poles are disposed in pairs, with a first one thereof extending radially inwardly from said outer liner to terminate at said inner liner with said proximal end thereof being joined to said outer liner, and a second one thereof extending radially outwardly from said inner liner to terminate at said outer liner with said proximal end thereof being joined to said inner liner.