# US 8,739,545 B2 · Burner for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,739,545 B2 - Document ID: US8739545B2 - Status: Granted - Kind: B2 - Application number: 12/768,078 - Filed: 2010-04-27 - Published: 2010-11-04 - Granted: 2014-06-03 - Earliest claimed: 2009-04-29 - Assignees: Siemens Aktiengesellschaft - Applicants: Andrew Cant; Paul Headland; Daniel Leggett - Inventors: Andrew Cant; Paul Headland; Daniel Leggett - Web page: https://patentgrep.com/patent/US8739545B2 ## CPC - F23C 7/004: {using vanes} - F23R 3/14: by using swirl vanes - F23R 3/286: {having fuel-air premixing devices (F23R3/30 takes precedence)} - F23R 3/36: Supply of different fuels - F23C 2900/07001: Air swirling vanes incorporating fuel injectors - F23C: METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN {A CARRIER GAS OR} AIR (burners F23D) - 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 burner for a gas turbine engine is provided. The burner includes a radial swirler for creating a swirling fuel/air mix, a combustion chamber where combustion of the swirling fuel/air mix occurs, and a pre-chamber located between the radial swirler and the combustion chamber. The radial swirler includes a plurality of vanes arranged in a circle, generally radially inwardly extending flow slots are defined between adjacent vanes in the circle, each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, and a base and top. A flow slot includes a first gas fuel injection hole in its base and a flow slot includes a second gas fuel injection hole in its first side wherein the amounts of gas fuel injected via the first and second gas fuel injection holes are independently variable. ## Claims ### Claim 1 A burner for a gas turbine engine, comprising: a radial swirler to create a swirling fuel/air mix, the radial swirler, comprising a plurality of vanes arranged in a circle, a plurality of radially inwardly extending flow slots defined between adjacent vanes in the circle; a combustion chamber in which combustion of the swirling fuel/air mix occurs; and a pre-chamber located between the radial swirler and the combustion chamber, wherein each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, a base and a top, wherein air travels along the plurality of flow slots from the inlet ends to the outlet ends and combines with gas fuel and creates the swirling fuel/air mix adjacent to the outlet ends, wherein each flow slot comprises a first gas fuel injection hole in the base and a second gas fuel injection hole in the first side, wherein an amount of gas fuel injected via the first and second gas fuel injection holes are independently variable, wherein a circular pilot face is located within the circle of the plurality of vanes, wherein a plurality of pilot gas fuel injection holes are spaced around a circumference of the circular pilot face, wherein the first gas fuel injection holes are supplied with gas fuel from a first gas fuel supply gallery, wherein the second gas fuel injection holes are supplied with gas fuel from a second gas fuel supply gallery independent of the first gas fuel supply gallery, wherein the burner further comprises an annular shaped gas fuel supply manifold which comprises the first and second gas fuel supply galleries, wherein the first gas fuel supply gallery supplies gas fuel to the first gas fuel injection holes by way of first passages within the gas fuel supply manifold that communicates with the first gas fuel injection holes, and wherein the second gas fuel supply gallery supplies gas fuel to the second gas fuel injection holes by way of second passages within the gas fuel supply manifold that communicate with the second gas fuel injection holes via third passages within the vanes of the radial swirler, the second passages being separate from the first passages. ### Claim 2 (depends on 1) A burner as claimed in claim 1, wherein each flow slot comprises the first gas fuel injection hole in the base and the second gas fuel injection hole in the first side. ### Claim 3 (depends on 2) A burner as claimed in claim 2, wherein each flow slot comprises two second gas fuel injection holes in the first side. ### Claim 4 (depends on 2) A burner as claimed in claim 2, wherein in each flow slot the first gas fuel injection hole is located at the inlet end of the flow slot and the second gas fuel injection hole is located adjacent to both the inlet end and the top. ### Claim 5 (depends on 3) A burner as claimed in claim 3, wherein in each flow slot the first gas fuel injection hole is located at the inlet end of the flow slot and the second gas fuel injection holes are located adjacent to both the inlet end and the top. ### Claim 6 (depends on 5) A burner as claim in claim 5, wherein in each flow slot the two second gas fuel injection holes are located one above the other. ### Claim 7 (depends on 1) A burner as claimed in claim 1, wherein the first and second gas fuel supply galleries are annular in form. ### Claim 8 (depends on 7) A burner as claimed in claim 7, wherein a plurality of gas fuel inlets to the annular first and second gas fuel supply galleries are substantially uniformly distributed around the first and second gas fuel supply galleries to ensure a uniform distribution of gas fuel around the galleries. ### Claim 9 (depends on 1) A burner as claimed in claim 1, wherein the plurality of bases of the plurality of flow slots and the circular pilot face lie substantially in the same plane.