A turbine exhaust section comprises a turbine exhaust case having radially outer and inner ducts defining therebetween an annular exhaust portion for the hot exhaust gases, and an exhaust mixer projecting axially rearwardly from the turbine exhaust case for mixing the hot exhaust gases with a cooler
A turbine exhaust section comprises a turbine exhaust case having radially outer and inner ducts defining therebetween an annular exhaust portion for the hot exhaust gases, and an exhaust mixer projecting axially rearwardly from the turbine exhaust case for mixing the hot exhaust gases with a cooler bypass duct flow. The upstream end of the exhaust mixer surrounds a downstream end of the outer duct and defines therewith an axially extending overlap joint with a radial play between the outer duct and the exhaust mixer. A sliding attachment in the radial direction is provided between the outer duct and the exhaust mixer for accommodating differences in thermal growth during engine operation. The sliding attachment includes a circumferential array of sliding guides extending radially through the axially extending overlap joint. A resilient sealing ring seals the radial play between the outer duct and the exhaust mixer at the overlap joint.
대표청구항▼
1. An exhaust section for a gas turbine engine of the type having an annular main gas path passage for channeling high temperature gases along an axis of the engine, and a bypass passage extending concentrically about the main gas path passage for axially channeling bypass air; the exhaust section c
1. An exhaust section for a gas turbine engine of the type having an annular main gas path passage for channeling high temperature gases along an axis of the engine, and a bypass passage extending concentrically about the main gas path passage for axially channeling bypass air; the exhaust section comprising: a turbine exhaust case having radially outer and inner ducts defining therebetween an annular exhaust portion of the main gas path; an exhaust mixer projecting axially rearwardly from the turbine exhaust case, the exhaust mixer having an upstream end, a downstream end, and an annular wall extending axially therebetween and defining a plurality of circumferentially distributed alternating inner and outer lobes, the outer lobes protruding radially outwardly into the bypass passage and the inner lobes protruding radially inwardly into the main gas path passage, the upstream end of the exhaust mixer surrounding a downstream end of the outer duct of the turbine exhaust case and defining therewith an axially extending overlap joint with a radial play between the outer duct and the exhaust mixer along the axially extending overlap joint; a sliding attachment in a radial direction between the outer duct of the turbine exhaust case and the exhaust mixer, the sliding attachment including a circumferential array of sliding guides extending radially through the axially extending overlap joint; and a resilient sealing ring sealing the radial play between the outer duct of the turbine exhaust case and the exhaust mixer at the axially extending overlap joint. 2. The exhaust section defined in claim 1, wherein the sliding guides extends radially outwardly from the downstream end of the outer case and in sliding engagement in corresponding holes defined in the upstream end of the exhaust mixer. 3. The exhaust section defined in claim 2, wherein each of the sliding guides comprises a bolt having a shank and a head, a sliding sleeve mounted over the shank of the bolt and a nut threadably engaged with a threaded end portion of the shank of the bolt, the nut maintaining the head and the sliding sleeve in clamping engagement with radially inwardly and radially outwardly facing surfaces of the outer duct, respectively. 4. The exhaust section defined in claim 3, wherein the sliding sleeve is provided at a radially outer end thereof with a flange, the flange facing a radially outer surface of the exhaust mixer. 5. The exhaust section defined in claim 3, wherein a doubler plate is welded to a radially inner surface of the outer duct at each sliding guide locations, the doubler plate defining a hole in registry with a corresponding hole in the outer duct for receiving an associated one of the bolts. 6. The exhaust section defined in claim 1, wherein the resilient sealing ring is received in a groove defined in a radially inner surface of the upstream end of the exhaust mixer, the resilient sealing ring projecting radially out of the groove across the radial play in sealing contact with a radially outer surface of the outer duct of the turbine exhaust case. 7. The exhaust section defined in claim 6, wherein the resilient sealing ring is disposed axially downstream of the sliding guides relative to the flow high temperature gases. 8. The exhaust section defined in claim 6, wherein the resilient sealing ring is a rope seal. 9. The exhaust section defined in claim 1, wherein the inner lobes are supported by radial struts at the downstream end of the exhaust mixer, each radial strut being provided with a clamping arrangement at a radially outer end thereof for radial clamping engagement with an associated one of the inner lobes. 10. The exhaust section defined in claim 9, wherein the radial struts extend radially outwardly from an inner ring connected to the inner duct of the turbine exhaust case. 11. The exhaust section defined in claim 9, wherein the radial struts extend radially through respective slots defined in the inner lobes, wherein each radial strut has a pair of side wings for engagement with a radially inner surface of an associated one of the inner lobes and a radial stopper for engagement with a radially outer surface of the associated one of the inner lobes, the associated inner lobe being radially trapped between the radial stopper and the side wings. 12. The exhaust section defined in claim 11, wherein the radial stopper and the side wings are shaped to generally follow a curvature of an associated one of the inner lobes. 13. An exhaust section for a bypass gas turbine engine having an annular main gas path passage for channeling high temperature gases along an axis of the engine, and a bypass passage surrounding the main gas path passage for axially channeling bypass air; the exhaust section comprising: a turbine exhaust case having radially outer and inner ducts defining therebetween an annular exhaust portion of the main gas path; an exhaust mixer extending rearwardly from the outer duct of the turbine exhaust case, the exhaust mixer having an upstream end, a downstream end, and an annular wall extending axially therebetween and defining a plurality of circumferentially distributed alternating inner and outer lobes, the outer lobes protruding radially outwardly into the bypass passage and the inner lobes protruding radially inwardly into the main gas path passage, the exhaust mixer and the turbine exhaust case being made out of different materials, the upstream end of the exhaust mixer surrounding a downstream end of the outer duct of the turbine exhaust case and defining therewith a radial play; a circumferential array of sliding guides extending radially outwardly from the downstream end of the outer duct of the turbine exhaust case and through a corresponding array of circumferentially distributed holes defined in the upstream end of the exhaust mixer, the circumferential array of sliding guides being free to slide in said circumferentially distributed holes when the outer duct thermally expand into said radial play, and a resilient radial seal disposed in said radial play in sealing engagement with the outer duct and the exhaust mixer. 14. The exhaust section defined in claim 13, wherein the exhaust mixer and the turbine exhaust case are made of materials having different coefficients of thermal expansion, and wherein the material used for the exhaust mixer is lighter in weight in comparison to the material used for the turbine exhaust case. 15. The exhaust section defined in claim 14, wherein the turbine exhaust case is made of a high temperature resistant nickel based alloy, whereas the exhaust mixer is made of titanium. 16. The exhaust section defined in claim 13, wherein the exhaust mixer is supported at its downstream end by radial struts. 17. The exhaust section defined in claim 16, wherein the inner lobes of the exhaust mixer has a radially inner surface, and wherein the radial struts extend radially outwardly from an inner ring in support engagement with the radially inner surface of the inner lobes. 18. The exhaust section defined in claim 17, wherein side wings extend laterally from opposed sides of each of the radial struts to provide a radially inner bearing surface for the inner lobes of the exhaust mixer. 19. The exhaust section defined in claim 18, wherein a radial stopper is provided at a radially outer end of each of the radial struts, the inner lobes being radially trapped between the radial stoppers and the side wings. 20. The exhaust section defined in claim 19, wherein the radial struts, the inner ring, the side wings and the radial stoppers are made of the same material as that of the turbine exhaust case.
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이 특허에 인용된 특허 (13)
Bouiller Jean G. (Brunoy FRX) Jourdain Grard E. A. (Corbeil Essonnes FRX) Loubet Marc G. (Nandy FRX), Assembly of two bodies having distinctly different coefficients of expansion.
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