Multiannular swirl combustor providing particulate separation

• US 4,539,918 A
• Filed: 10/22/1984
• Issued: 09/10/1985
• Est. Priority Date: 10/22/1984
• Status: Expired due to Term

• Current Assignee: Westinghouse Electric Company LLC (Brookfield Asset Management Incorporated)
• Original Assignee: Westinghouse Electric Company LLC (Brookfield Asset Management Incorporated)
• Inventors: Beer, Janos M., Young, William E., Dilmore, James A., Vermes, Geza
• Primary Examiner(s): Dority, Jr., Carroll B.
• Application Number:
  US06/663,531
• Time in Patent Office: 323 Days
• Field of Search: 60/39.464, 110/216, 110/266, 110/263, 110/264, 110/265
• US Class Current: 110/266
• CPC Class Codes: F23C 6/045 with staged combustion in a single enclosure
• CPC Class Codes: F23D 1/02 Vortex burners, e.g. for cyclone-type combustion apparatus

Abstract

A multi-annular swirl burner includes a plurality of overlapping tubular wall members which form a rich combustion zone and a lean combustion zone with a throat section therebetween. Annular passages are located between adjacent wall members, and vanes located therein input a tangential velocity to entering air. The tangential velocity of the swirling flows increases with increasing radius to produce centrifugal separating force on particulates moving from the rich combustion zone to the throat section. A collection system scavenges particulates from the throat section for disposal.

Claims

1. A two-stage rich-lean combustor operable with reduced emission of fuel-bound and thermal nitrogen oxide products (NO_x), said combustor comprising:

(a) a plurality of tubular members having differing axial lengths and disposed to form a burner basket of sufficient size and axial length to contain axially spaced rich and lean combustion zones;

(b) means for supporting said tubular members substantially coaxially and telescopically relative to each other to provide a generally annular path for inlet pressurized gaseous reactant or pressurized air flowing into said combustor with predetermined axial velocity between each tubular member and the next radially outwardly disposed tubular member;

(c) means for imparting a tangential velocity to gaseous reactant entering said combustor through each annular flow path with the tangential velocity of at least the flows entering the rich combustion zone increasing with increasing flow radius;

(d) nozzle means for supplying fuel to said combustor in at least one predetermined location;

(e) said tubular members having respective axial lengths and being so disposed that the axial location of the tubular member outlet ends generally have increasing radii and respectively are located at successive downstream locations;

(f) said tangential velocity imparting means and the radial and axial geometry of at least two of said tubular members being coordinated under operating inlet gas pressure and gas axial velocity conditions to;

(1) define said rich combustion zone in an upstream portion of said combustor, where high temperature oxygen deficient combustion occurs with flame stabilizing recirculation flow and substantially without net NO_x formation;

(2) produce a toroidal vortex in said rich combustion zone, with recirculating combustion air being recuperatively supplied substantially by the swirling inlet annular air flow after it has cooled the inner wall surfaces of said tubular members about said rich combustion zone; and

(3) provide sufficient fuel particulate residence time in the rich combustion zone to permit particulate burning prior to centrifugal separation of particulates toward the combustor wall surface;

(g) said tangential velocity imparting means and the radial and axial geometry of at least two of said tubular members located outwardly from said tubular members about said rich combustion zone being coordinated under operating inlet gas pressure and gas axial velocity conditions to define said lean combustion zone and to produce a toroidal vortex in said lean combustion zone;

(h) said tubular members being arranged to provide a throat section into which said rich combustion zone converges and from which said lean combustion zone diverges; and

(i) means for collecting and withdrawing from said combustor particulates separated from the flow as it passes through said throat section.

2. A combustor as set forth in claim 1 wherein said collecting means comprises an annular collector disposed about said throat section and extending inwardly into said throat section to shear off scavenge flow gas which contains particulate matter.

3. A combustor as set forth in claim 2 wherein a cyclone is provided for separating the particulates from the scavenge flow, means are provided for directing the scavenge flow from said collector to said cyclone.

4. A combustor as set forth in claim 3 wherein the combustor is a gas turbine combustor and means are provided for cleaning and cooling the separated gas flow from said cyclone to provide return gas flow for use in the turbine apparatus.

5. A combustor as set forth in claim 4 wherein the combustor is a gas turbine combustor and a manifold is provided for collecting scavenge flow from the annular collector of said combustor as well as from other combustors in the turbine, and means for coupling the total scavenge flow to said cyclone.

6. A combustor as set forth in claim 1 wherein said throat section has sufficient length to permit radially outward separation of particulates, and said annular collector being located near the downstream end of said throat section.