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 circumferential
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.
대표청구항▼
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; andan exhaust mixer cantilevered from the engine cas
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; andan exhaust mixer cantilevered from the engine casing and cooperating with the exhaust cone such as to define a portion of the main gas path between them, the exhaust mixer having lobes which are circumferentially distributed and connected at a radially innermost side by a stiffener ring disposed radially inward from the lobes, the stiffener ring disposed radially within the exhaust cone, the stiffener ring being unconnected to the exhaust cone and free to move relative thereto. 2. The gas turbine engine according to claim 1, wherein the exhaust mixer has a series of circumferentially spaced apart mixer struts which radially extend through the portion of the main gas path between the lobes and the stiffener ring, the mixer struts extending 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. 3. The gas turbine engine according to claim 2, wherein the mixer struts extend though at least one opening formed in an outer surface of the exhaust cone, the at least one opening comprising a plurality of individual closed-perimeter openings which are circumferentially distributed thereabout, each said mixer strut extending through one of the openings. 4. The gas turbine engine according to claim 1, wherein the exhaust mixer has a series of circumferentially spaced apart mixer struts which radially extend through the portion of the main gas path between the lobes and the stiffener ring, the mixer struts including hollow tubes which are substantially seamless along their length. 5. The gas turbine engine according to claim 1, wherein the exhaust mixer has a series of circumferentially spaced apart mixer struts which radially extend through the portion of the main gas path between the lobes and the stiffener ring, the mixer struts formed of extruded standard seamless tube and having an aerodynamic profile. 6. 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. 7. The gas turbine engine according to claim 1, wherein the exhaust mixer has a series of circumferentially spaced apart mixer struts which radially extend through the portion of the main gas path between the lobes and the stiffener ring, the mixer struts being connected to the lobes by a reinforced sole, the reinforced sole having a thickness greater than that of a wall thickness of the lobes. 8. The gas turbine engine according to claim 1, wherein the lobes comprise a plurality of alternating inner and outer lobes, each of the inner lobes having a mixer strut fixed thereto. 9. 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;an exhaust mixer cantilevered from the engine casing and cooperating with the exhaust cone such as to define a portion of the main gas path between them, the exhaust mixer having a plurality of circumferentially distributed lobes connected at a radially innermost side by a stiffener ring disposed radially within the exhaust mixer, the stiffener ring disposed radially within the exhaust cone; and an annular dampening cord extending from an inner radial surface of the exhaust cone to the stiffener ring, the dampening cord forming a compliant connection between the exhaust cone and stiffener ring. 10. 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 an upstream end fastened to an engine case of the gas turbine engine and a downstream end forming mixer lobes which are circumferentially distributed;the exhaust cone having a circumferential radial depression; anda circumferentially extending stiffener ring connected to the mixer lobes at a radially innermost side thereof, the stiffener ring disposed within the circumferential radial depression and being unconnected to the exhaust cone such as to move relative thereto. 11. The exhaust mixer according to claim 10, wherein at least radial 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. 12. The exhaust mixer according to claim 10, further comprising circumferentially spaced apart mixer struts which radially extend between the mixer lobes and the stiffener ring, the mixer struts being substantially seamless hollow tubes. 13. The exhaust mixer according to claim 10, 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. 14. The exhaust mixer according to claim 10, wherein the lobes comprise a plurality of alternating inner and outer lobes, the exhaust mixer further comprising circumferentially spaced apart mixer struts which radially extend between the mixer lobes and the stiffener ring, the mixer struts being 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. 15. The exhaust mixer according to claim 10, wherein the exhaust mixer and the exhaust cone define a portion of a main gas path therebetween, the stiffener ring being located entirely radially inward of the portion. 16. The exhaust mixer according to claim 15, 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 portion of the main gas path. 17. The exhaust mixer according to claim 10, wherein a circumferential ledge is disposed on an outer surface of the exhaust cone at an edge of the circumferential radial depression, the circumferential ledge overhanging a portion of the circumferential radial depression to direct gas flow thereover. 18. The exhaust mixer according to claim 17, 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 circumferential radial depression.
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이 특허에 인용된 특허 (13)
Steckbeck James F. (San Diego CA) Naik Sharad (Chula Vista CA), Aerodynamic stiffening ring for an aircraft turbine engine mixer.
Torkelson Delbert W. (Catoosa OK) Jannetta Thomas J. (Tulsa OK) Nikkanen John P. (West Hartford CT) Webb Daniel E. (Wethersfield CT) Zysman Steven H. (Middletown CT) Colletti William D. (Cromwell CT), Fixed geometry mixer/ejector suppression system for turbofan aircraft engines.
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