An exhaust diffuser includes an outer shroud and an inner shroud radially separated from the outer shroud so as to define a fluid passage between the outer shroud and the inner shroud. A strut extends between the outer shroud and the inner shroud. The strut generally includes an outer surface, a lea
An exhaust diffuser includes an outer shroud and an inner shroud radially separated from the outer shroud so as to define a fluid passage between the outer shroud and the inner shroud. A strut extends between the outer shroud and the inner shroud. The strut generally includes an outer surface, a leading edge, a trailing edge, a first side and a second side. At least one turbulator may be positioned along a radial span of the strut. The at least one turbulator extends generally outwardly from the strut outer surface. The turbulator extends across the leading edge of the strut from the first side to the second side of the strut.
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1. An exhaust diffuser, comprising; a. an outer shroud, wherein the outer shroud comprises a double wall construction including an inner wall radially spaced from an outer wall so as to define an airspace therebetween;b. an inner shroud radially separated from the outer shroud to define a fluid pass
1. An exhaust diffuser, comprising; a. an outer shroud, wherein the outer shroud comprises a double wall construction including an inner wall radially spaced from an outer wall so as to define an airspace therebetween;b. an inner shroud radially separated from the outer shroud to define a fluid passage between the outer shroud and the inner shroud;c. a strut extending between the outer shroud and the inner shroud, the strut having an outer surface, a leading edge, a trailing edge, a first side and a second side, wherein the strut is stationary between the outer shroud and the inner shroud; andd. at least one turbulator positioned along a radial span of the strut and that extends outwardly from the strut outer surface, the at least one turbulator extending across the leading edge of the strut from the first side to the second side of the strut;e. wherein the at least one turbulator reduces aerodynamic losses across the strut, the inner shroud and the outer shroud resulting from flow separation of combustion exhaust gases flowing from a turbine section of a gas turbine and into the exhaust diffuser at tangential flow angles. 2. The exhaust diffuser as in claim 1, wherein the at least one turbulator extends outwardly from the strut first side at a first width, from the strut second side at a second width, and from the strut leading edge at a third width. 3. The exhaust diffuser as in claim 2, wherein the first width and the second width are asymmetrical. 4. The exhaust diffuser as in claim 2, wherein the third width is less than at least one of the first width or the second width. 5. The exhaust diffuser as in claim 1, wherein the at least one turbulator extends from the leading edge towards the trailing edge of the strut at a first distance across the first side of the strut and at a second distance across the second side of the strut. 6. The exhaust diffuser as in claim 1, wherein the at least one turbulator extends at least partially between the leading edge and the trailing edge of the strut at an angle that is perpendicular to the leading edge of the strut. 7. The exhaust diffuser as in claim 1, wherein the at least one turbulator extends at least partially between the leading edge and the trailing edge of the strut at an angle that is acute or obtuse to the leading edge of the strut. 8. An exhaust diffuser, comprising: a. an outer shroud, wherein the outer shroud comprises a double wall construction including an inner wall radially spaced from an outer wall so as to define an airspace therebetween;b. an inner shroud radially separated from the outer shroud to define a fluid passage between the outer shroud and the inner shroud;c. a strut extending between the outer shroud and the inner shroud, the strut having an outer surface, a leading edge, a trailing edge, a first side and a second side, wherein the strut is stationary between the outer shroud and the inner shroud; andd. at least one turbulator positioned along a radial span of the strut and that extends outwardly from the strut outer surface, the at least one turbulator having a first side portion disposed along the first side of the strut, a second side portion disposed along the second side of the strut, and a leading edge portion disposed along the leading edge of the strut, wherein the first side portion, the second side portion and the leading edge portion are continuous;e. wherein the at least one turbulator reduces aerodynamic losses across the strut and within the fluid passage resulting from flow separation of combustion exhaust gases flowing from a turbine section of a gas turbine and into the exhaust diffuser at tangential flow angles. 9. The exhaust diffuser as in claim 8, wherein the at least one turbulator extends outwardly front the strut first side at a first width, from the strut second side at a second width, and from the strut leading edge at a third width. 10. The exhaust diffuser as in claim 9, wherein the first width and the second width are asymmetrical. 11. The exhaust diffuser as in claim 9, wherein the third width is less than at least one of the first width or the second width. 12. The exhaust diffuser as in claim 8, wherein the at least one turbulator extends from the leading edge towards the trailing edge of the strut at a first distance across the first side of the strut and at a second distance across the second side of the strut. 13. The exhaust diffuser as in claim 8, wherein the at least one turbulator extends at least partially between the leading edge and the trailing edge of the strut at an angle that is perpendicular to the leading edge of the strut. 14. The exhaust diffuser as in claim 8, wherein the at least one turbulator extends at least partially between the leading edge and the trailing edge of the strut at an angle that is-acute or obtuse to the leading edge of the strut. 15. A gas turbine, comprising: a. a compressor section;b. at least one combustor downstream from the compressor section;c. a turbine section downstream from the at least one combustor;d. an exhaust diffuser downstream from the turbine section, the exhaust diffuser haying an inner shroud, an outer shroud at least partially surrounding the inner shroud, and a plurality of struts that extend between the inner and the outer shrouds, wherein the outer shroud comprises a double wall construction including an inner wall radially spaced from an outer wall so as to define an airspace therebetween, each of the plurality of struts having an outer surface, a leading edge, a trailing edge, a first side and a second side, wherein each strut of the plurality of struts is stationary between the outer shroud and the inner shroud; ande. wherein at least one strut of the plurality of struts includes at least one turbulator positioned along a radial span of the at least one strut, the at least one turbulator extending outwardly from the outer surface and extending across the leading edge from the first side to the second side of the at least one strut;f. wherein the at least one turbulator reduces aerodynamic losses across the at least one strut, the inner shroud and the outer shroud resulting from flow separation of combustion exhaust gases flowing from the turbine section into the exhaust diffuser at tangential flow angles. 16. The gas turbine as in claim 15, wherein the at least one turbulator extends at least partially between the :leading edge and the trailing edge of the at least one strut at an angle that is acute to the leading edge of the at least one strut. 17. The gas turbine as in claim 15, wherein the at least one turbulator extends at least partially between the leading edge and the trailing edge of the at least one strut at an angle that is perpendicular to the leading edge of the at least one strut. 18. The exhaust diffuser as in claim 15, wherein the at least one turbulator extends at least partially between the leading edge and the trailing edge of the at least one strut at an angle that is obtuse to the leading edge of the at least one strut.
Mirabella, Lucia; Musuvathy, Suraj; Prabhu, Bharat Sanjay, Designing the geometry of a gas turbine exhaust diffuser on the basis of fluid dynamics information.
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