# US 2014/0360156 A1 · Asymmetric Baseplate Cooling with Alternating Swirl Main Burners > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0360156 A1 - Document ID: US20140360156A1 - Status: Published application - Kind: A1 - Application number: 14/140,599 - Filed: 2013-12-26 - Published: 2014-12-11 - Earliest claimed: 2013-06-05 - Assignees: Siemens Aktiengesellschaft - Inventors: Krishna C. Miduturi; David M. Ritland - Web page: https://patentgrep.com/patent/US20140360156A1 ## CPC - F23R 3/16: with devices inside the flame tube or the combustion chamber to influence the air or gas flow - F23R 3/005: {Combined with pressure or heat exchangers} - F23R 3/04: Air inlet arrangements - F23R 3/283: {Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances} - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/12: inducing a vortex - F23R 2900/03041: Effusion cooled combustion chamber walls or domes - F23R 2900/03042: Film cooled combustion chamber walls or domes - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) ## Abstract A combustor arrangement (10) including a pilot burner (22) having a pilot cone (62); a plurality of clockwise (130) main swirlers interposed among a plurality of counterclockwise (132) main swirlers and disposed concentrically about the pilot burner, and a base plate (40) transverse to the main swirlers Inbound-zones (134) exist where adjacent portions (106) of adjacent flows (108) through main swirlers flow toward the pilot cone, and interposed between the inbound zones outbound zones (136) exist where adjacent portions of adjacent flows flow away from the pilot cone The arrangement is configured to preferentially deliver more cooling fluid to the inbound zones than the outbound zones. ## Claims ### Claim 1 A combustor arrangement, comprising a pilot burner comprising a pilot cone, a plurality of clockwise main swirlers interposed among a plurality of counterclockwise main swirlers and disposed concentrically about the pilot burner; and a base plate transverse to the main swirlers, wherein inbound-zones exist where adjacent portions of adjacent flows through main swirlers flow toward the pilot cone, and interposed between the inbound zones, outbound zones exist where adjacent portions of adjacent flows flow away from the pilot cone, and wherein the arrangement is configured to preferentially deliver relatively more cooling fluid to the inbound-zones than the outbound zones via high flow regions disposed upstream of the inbound zones with respect to a longitudinal axis of the combustor arrangement. ### Claim 2 (depends on 1) The combustor arrangement of claim 1, wherein the pilot cone comprises an outer pilot cone surrounding an inner pilot cone and defining an annular gap there between effective to deliver annular gap cooling fluid to the inbound zones and outbound zones, wherein a width of the annular gap vanes to form respective high flow regions and low flow regions ### Claim 3 (depends on 1) The combustor arrangement of claim 1, wherein the pilot cone comprises an outer pilot cone surrounding an inner pilot cone and defining an annular gap there between effective to deliver annular gap cooling fluid to the inbound zones and outbound zones, and flow guides disposed in the annular gap effective to form the high-flow regions by preferentially guiding annular gap cooling fluid into the inbound zones ### Claim 4 (depends on 1) The combustor arrangement of claim 1, wherein the base plate comprises apertures that define the high-flow regions through each of which cooling fluid flows at a relatively higher flow-rate, and wherein the apertures further define a plurality of low-flow regions through each of which the cooling fluid flows at a relatively lower flow-rate ### Claim 5 (depends on 1) The combustor arrangement of claim 1, wherein a respective high-flow region is circumferentially aligned with each inbound-zone. ### Claim 6 (depends on 5) The combustor arrangement of claim 5, wherein high-flow region apertures permit the cooling fluid to flow through the base plate, and wherein in each high-flow region a majority of the high-flow region apertures are disposed radially outward of longitudinal axes of the respective adjacent main swirlers. ### Claim 7 A combustor arrangement, comprising a pilot burner, a plurality of premix main swirlers concentrically disposed about the pilot burner, the main swirlers alternate between a main swirler that imparts a clockwise swirl and a main swirler that imparts a counter-clockwise swirl; and a base plate through which the main swirlers extend, wherein the base plate comprises a plurality of high-flow regions through each of which cooling fluid flows at a relatively higher flow-rate and a plurality of low-flow regions through each of which the cooling fluid flows at a relatively lower flow-rate, wherein the high-flow regions are disposed at locations such that cooling fluid flowing there through will be delivered to a respective inbound-zone that is formed where adjacent portions of adjacent main swirler flows flow into the pilot burner ### Claim 8 (depends on 7) The combustor arrangement of claim 7, wherein the low-flow regions are circumferentially interposed between adjacent high-flow regions. ### Claim 9 (depends on 8) The combustor arrangement of claim 8, wherein a respective high-flow region is demarked by planes radial to a pilot burner longitudinal axis and which bisect respective adjacent main swirlers surrounding a respective inbound-zone ### Claim 10 (depends on 9) The combustor arrangement of claim 9, wherein low-flow regions are those portions of the base plate in between the high-flow regions ### Claim 11 (depends on 7) The combustor arrangement of claim 7, wherein a respective high-flow region is circumferentially aligned with each inbound-zone ### Claim 12 (depends on 7) The combustor arrangement of claim 7, wherein apertures through the base plate and associated with a respective high-flow region are positioned such the cooling fluid flowing through the respective high-flow region flows into a respective inbound-zone adjacent a pilot cone of the pilot burner ### Claim 13 (depends on 7) The combustor arrangement of claim 7, wherein the pilot burner comprises an inner cone, and an outer cone surrounding the inner cone and defining an annular gap there between, wherein the annular gap defines a passageway for cooling fluid to flow there through, and wherein cooling fluid exiting the annular gap enters the inbound-zones ### Claim 14 A combustor arrangement comprising a plurality of alternately rotating main swirlers disposed about a pilot burner comprising a pilot cone, wherein converging flows created by adjacent main swirlers create alternating inbound and outbound flow regions relative to the pilot cone, and a cooling fluid flow arrangement effective to preferentially deliver a higher flow rate of cooling fluid to the inbound flow regions than to the outbound flow regions ### Claim 15 (depends on 14) The combustor arrangement of claim 14, further comprising a base plate supporting the main swirlers, and a higher number of cooling fluid apertures formed in the base plate in regions upstream of the inbound flow regions than in regions upstream of the outbound flow regions ### Claim 16 (depends on 14) The combustor arrangement of claim 14, further comprising a base plate supporting the main swirlers, and relatively larger cooling fluid apertures formed in the base plate in regions upstream of the inbound flow regions than in regions upstream of the outbound flow regions. ### Claim 17 (depends on 14) The combustor arrangement of claim 14, wherein the pilot cone is configured to deliver the higher flow rate of cooling fluid to the inbound flow regions than to the outbound flow regions ### Claim 18 (depends on 17) The combustor arrangement of claim 17, wherein the pilot cone comprises an annular gap comprising a varying width about its circumference ### Claim 19 (depends on 17) The combustor arrangement of claim 17, wherein the pilot cone comprises an annular gap comprising a varying geometry about its circumference ### Claim 20 (depends on 17) The combustor arrangement of claim 17, wherein the pilot cone comprises a flow guide effective to direct the cooling fluid