A shrouded nozzle arrangement for a gas turbine engine exhaust comprises a shrouded nozzle and duct means. The exhaust nozzle is translatable from a first position, wherein the exit plane of the nozzle lies upstream of the exit aperture of the shroud, to a second position, wherein the exit plane of
A shrouded nozzle arrangement for a gas turbine engine exhaust comprises a shrouded nozzle and duct means. The exhaust nozzle is translatable from a first position, wherein the exit plane of the nozzle lies upstream of the exit aperture of the shroud, to a second position, wherein the exit plane of the exhaust duct lies substantially downstream of the exit aperture of the shroud. In this second position, the use of reheat or thrust vectoring may be used without damage to the shroud.
대표청구항▼
The invention claimed is: 1. A shrouded nozzle arrangement for a gas turbine engine exhaust gas comprising a gas turbine, an exhaust nozzle, a duct means for providing communication of exhaust gas between the gas turbine and the exhaust nozzle, and a shroud which encloses the nozzle and duct means,
The invention claimed is: 1. A shrouded nozzle arrangement for a gas turbine engine exhaust gas comprising a gas turbine, an exhaust nozzle, a duct means for providing communication of exhaust gas between the gas turbine and the exhaust nozzle, and a shroud which encloses the nozzle and duct means, the shroud having an exit aperture through which, in use, the exhaust nozzle discharges, wherein the exhaust nozzle is translatable from a first position, wherein an exit plane of the nozzle lies upstream of the exit aperture of the shroud, to a second position, wherein the exit plane of the exhaust duct lies substantially downstream of the exit aperture of the shroud; and wherein the duct means comprises an inner duct member and an outer duct member concentric with one another, wherein the inner and outer duct members are slideably mounted and movable relative to one another, the outer duct member at all times overlapping the inner duct member such that inner and outer duct members provide continuous duct means. 2. A shrouded nozzle arrangement as claimed in claim 1 wherein a substantially annular support means is provided, the support means remaining fixed relative to one of the duct members the other duct member being slideably mounted within the support means and moving relative to the support means. 3. A shrouded nozzle arrangement as claimed in claim 2 wherein a reheat system is provided within the duct means. 4. A shrouded nozzle arrangement as claimed in claim 2 wherein the nozzle is capable of thrust vectoring. 5. A shrouded nozzle arrangement as claimed in claim 2 wherein the shroud is configured to minimise the radar and infra-red signatures of the nozzle and exhaust gas issuing from the nozzle. 6. A shrouded nozzle arrangement as claimed in claim 2 wherein the support means is provided with an inwardly projecting first flange, the first flange slideably engaging the slideable duct member about an annular periphery to provide a substantially gas tight seal, the slideable duct member provided with an outwardly projecting second flange, the second flange slideably engaging the support means about an annular periphery to provide a substantially gas tight seal, the first and second flanges defining a chamber between support means and slideable duct member into which exhaust gas may be held from within the duct means the first and second flanges being disposed such that pressure within the chamber acts upon the slideable duct member to counter the loads imposed by exhaust gas impinging upon the exit nozzle. 7. A shrouded nozzle arrangement as claimed in claim 6 wherein the nozzle is capable of thrust vectoring. 8. A shrouded nozzle arrangement as claimed in claim 6 wherein the shroud is configured to minimise the radar and infra-red signatures of the nozzle and exhaust gas issuing from the nozzle. 9. A shrouded nozzle arrangement as claimed in claim 6 wherein a reheat system is provided within the duct means. 10. A shrouded nozzle arrangement as claimed in claim 1 wherein a reheat system is provided within the duct means. 11. A shrouded nozzle arrangement as claimed in claim 1 wherein the nozzle is capable of thrust vectoring. 12. A shrouded nozzle arrangement as claimed in claim 1 wherein the shroud is configured to minimise the radar and infra-red signatures of the nozzle and exhaust gas issuing from the nozzle. 13. A shrouded nozzle arrangement for a gas turbine engine comprising, an exhaust nozzle, defining an upstream inlet aperture and a downstream exit aperture, said exit aperture having an exit plane, duct means defining an upstream aperture in flow communication with the gas turbine engine, and a downstream aperture in flow communication with the exhaust nozzle inlet aperture, the duct means in use providing flow communication of an exhaust gas between the gas turbine engine and the exhaust nozzle, and, a shroud, defining an upstream aperture and a downstream aperture, said shroud enclosing the exhaust nozzle and duct means, said exhaust nozzle being translatable from a first position, wherein the exit plane of the nozzle lies upstream of the downstream aperture of the shroud, to a second position, wherein the exit plane of the exhaust nozzle lies substantially downstream of the downstream aperture of the shroud; and wherein the duct means comprises an inner duct member and an outer duct member concentric with one another, wherein the inner and outer duct members are slideably mounted and movable relative to one another, the outer duct member at all times overlapping the inner duct member such that inner and outer duct members provide continuous duct means. 14. The shrouded nozzle arrangement of claim 13, wherein said exhaust nozzle is translatable as a unit from said first position to said second position. 15. The shrouded nozzle arrangement of claim 14, wherein the exit plane of the nozzle lies fully upstream of the downstream aperture of the shroud. 16. A shrouded nozzle arrangement as claimed in claim 13 wherein a substantially annular support means is provided, the support means remaining fixed relative to one of the duct members the other duct member being slideably mounted within the support means and moving relative to the support means. 17. A shrouded nozzle arrangement as claimed in claim 16 wherein the support means is provided with an inwardly projecting first flange, the first flange slideably engaging the slideable duct member about an annular periphery to provide a substantially gas tight seal, the slideable duct member provided with an outwardly projecting second flange, the second flange slideably engaging the support means about an annular periphery to provide a substantially gas tight seal, the first and second flanges defining a chamber between support means and slideable duct member into which exhaust gas may be held from within the duct means the first and second flanges being disposed such that pressure within the chamber acts upon the slideable duct member to counter the loads imposed by exhaust gas impinging upon the exit nozzle.
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이 특허에 인용된 특허 (5)
Nash Dudley O. (Forest Park OH), Actuating means for a thrust vectoring gas turbine engine exhaust nozzle.
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