# US 8,739,513 B2 · Gas turbine engine exhaust mixer > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,739,513 B2 - Document ID: US8739513B2 - Status: Granted - Kind: B2 - Application number: 12/858,313 - Filed: 2010-08-17 - Published: 2011-02-17 - Granted: 2014-06-03 - Earliest claimed: 2009-08-17 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Guy Lefebvre; Nicolas Grivas; Richard Bouchard; Denis Leclair; Eric Durocher - Inventors: Guy Lefebvre; Nicolas Grivas; Richard Bouchard; Denis Leclair; Eric Durocher - Web page: https://patentgrep.com/patent/US8739513B2 ## CPC - F02K 1/386: {mixing devices in the jet pipe, e.g. for mixing primary and secondary flow} - F01D 9/04: forming ring or sector - F02K 1/48: Corrugated nozzles - F02K 1/80: Couplings or connections - F05D 2220/32: in gas turbines - F05D 2230/642: using maintaining alignment while permitting differential dilatation - F05D 2240/10: Stators - F05D 2240/127: Vortex generators, turbulators, or the like, for mixing - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An exhaust mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of inner and outer mixer lobes. A support member interconnects at least a number of the inner lobes, and includes a circumferentially extending stiffener ring located radially inwardly from the inner lobes and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring. The mixer struts have a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path. The stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween. ## Claims ### Claim 1 A gas turbine engine having an engine casing enclosing a compressor section, a combustor and a turbine section defining a main gas path serially extending therethrough, and comprising: an exhaust cone disposed downstream of the turbine section; and an exhaust mixer connected solely to an aft end of the engine casing such as to be cantilevered therefrom, the exhaust mixer at least partially surrounding the exhaust cone such as to define a portion of the main gas path between an outer surface of the exhaust cone and an annular wall defining a plurality of circumferentially distributed alternating inner and outer lobes of the exhaust mixer, the exhaust mixer including a support member connected to at least a number of the lobes, the support member including a circumferentially extending stiffener ring located radially inward from the lobes and a series of circumferentially spaced apart mixer struts which radially extend through the main gas path between the lobes and the stiffener ring, the mixer struts extending though at least one opening formed in the outer surface of the exhaust cone such that the stiffener ring is located radially inward of the outer surface of the exhaust cone, the stiffener ring being connected only to the support struts such as to be free to move relative to the exhaust cone. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the mixer struts extend a radial distance which is at least substantially equal to a width of said portion of the main gas path, such that the stiffener ring is located radially inward of the main gas path. ### Claim 3 (depends on 1) The gas turbine engine according to claim 1, wherein the at least one opening forms a circumferentially continuous open-toped channel in the outer surface of the exhaust cone, the stiffener ring being located within said channel without contacting the exhaust cone during normal operation, the stiffener ring being radially inward of a predicted gas path profile flowing along the outer surface of the exhaust cone. ### Claim 4 (depends on 3) The gas turbine engine according to claim 3, wherein the stiffener ring is substantially flush with the predicted gas path profile. ### Claim 5 (depends on 4) The gas turbine engine according to claim 4, wherein a circumferential ledge is disposed on the outer surface of the exhaust cone at an edge of the channel formed therein, the circumferential ledge overhanging a portion of the channel to direct gas flow over said channel. ### Claim 6 (depends on 5) The gas turbine engine according to claim 5, wherein the ledge and the stiffener ring are substantially aligned such as to form a discontinuous gas path surface over at least a portion of the channel. ### Claim 7 (depends on 1) The gas turbine engine according to claim 1, wherein the at least one opening formed in the outer surface of the exhaust cone comprises a plurality of individual closed-perimeter openings which are circumferentially distributed thereabout, each said mixer strut extending through one of the openings, and the stiffener ring being located inside the exhaust cone. ### Claim 8 (depends on 7) The gas turbine engine according to claim 7, wherein a circumferential dampening cord extends from an inner radial surface of the exhaust cone to the stiffener ring, the dampening cord being operably connected to the stiffener ring. ### Claim 9 (depends on 1) The gas turbine engine according to claim 1, wherein the mixer struts include hollow tubes which are substantially seamless along their length. ### Claim 10 (depends on 1) The gas turbine engine according to claim 1, wherein the mixer struts are formed of extruded standard seamless tube and have an aerodynamic profile. ### Claim 11 (depends on 1) The gas turbine engine according to claim 1, wherein the stiffener ring has a substantially U-shaped cross-sectional profile, including an annular longitudinal portion and radially inwardly curved circumferential edges on either side of the longitudinal portion. ### Claim 12 (depends on 1) The gas turbine engine according to claim 1, wherein the mixer struts are connected to the lobes by a reinforced sole, the reinforced sole having a thickness greater than that of a wall thickness of the lobes. ### Claim 13 (depends on 1) The gas turbine engine according to claim 1, wherein each of inner lobes has a mixer strut fixed thereto. ### Claim 14 An exhaust mixer of a gas turbine engine mounted at an exhaust of the gas turbine engine such as to at least partially surround an exhaust cone, the exhaust mixer comprising: an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of circumferentially distributed alternating inner and outer mixer lobes; and a support member disposed proximate the downstream end of the annular wall and interconnecting at least a number of the inner lobes, the support member including a circumferentially extending stiffener ring located radially inwardly from the inner lobes, and a series of circumferentially spaced apart mixer struts radially extending from the inner lobes to the stiffener ring, the mixer struts having a radial length at least equal to a width of a main gas path defined between the inner lobes and the exhaust cone such that the mixer struts extend entirely through the main gas path, the stiffener ring being fixed solely to the mixer struts such as to float with respect to the exhaust cone and permit relative movement therebetween. ### Claim 15 (depends on 14) The exhaust mixer according to claim 14, wherein at least radially displacement between the stiffening ring and the exhaust cone is possible without the stiffening ring and the exhaust cone coming into contact with each other. ### Claim 16 (depends on 14) The exhaust mixer according to claim 14, wherein the mixer struts are substantially seamless hollow tubes. ### Claim 17 (depends on 14) The exhaust mixer according to claim 14, wherein the stiffener ring includes an annular longitudinally extending portion and radially inwardly curved circumferential edges on opposite sides of the longitudinally extending portion, the stiffener ring defining a substantially U-shaped cross-section. ### Claim 18 (depends on 14) The exhaust mixer according to claim 14, wherein the mixer struts are connected to the inner lobes by a reinforced sole, the reinforced sole having a thickness greater than a wall thickness of the annular wall at the inner lobes. ### Claim 19 (depends on 14) The exhaust mixer according to claim 14, wherein the stiffener ring is located entirely radially inward of the main gas path. ### Claim 20 (depends on 19) The exhaust mixer according to claim 19, wherein a radially outer surface of the stiffener ring is substantially flush with an outer wall of the exhaust cone, such that the stiffener ring forms at least part of an inner surface of the main gas path along a portion thereof in the exhaust mixer.