Shrouded nozzle arrangement
AssigneeROLLS-ROYCE plc
InventorClive Olive
Life of this patent
Estimating the term…
Abstract
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.
Claims17
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.
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.
Dependencies are inferred from the claim text.