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US 11,448,162 B2Granted
Propelling nozzle for a turbofan engine on a supersonic aircraft
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsPredrag Todorovic, Thomas Schillinger
Life of this patent
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Abstract
The invention relates to a propelling nozzle for a turbofan engine on a supersonic aircraft, the propelling nozzle including: a propelling nozzle wall, a duct, which is radially outwardly bounded by the propelling nozzle wall, and a central body arranged in the duct. According to the invention, the central body is connected to the propelling nozzle wall via at least one brace.
Claims20
A thrust nozzle for a turbofan engine of a supersonic aircraft, wherein the thrust nozzle comprises:
- a thrust nozzle wall,
- a flow channel which is delimited radially to an outside by the thrust nozzle wall,
- a central body arranged in the flow channel,
- two struts connecting the central body to the thrust nozzle wall,
- a thrust reverser integrated into the thrust nozzle, the thrust reverser including two pivotable thrust reverser doors which are rotatably mounted in two side structures of the thrust nozzle wall, the two side structures being formed on opposite sides of the thrust nozzle wall,
- the two struts being connected respectively to the two side structures of the thrust nozzle wall, and
- wherein the thrust reverser doors are, in a pivoted position, arranged such that radially inner ends thereof are arranged at least partially downstream of leading edges of the two struts and at the same time lie against the two struts.
4 more elements
A thrust nozzle for a turbofan engine of a supersonic aircraft, wherein the thrust nozzle comprises:
- a thrust nozzle wall,
- a flow channel which is delimited radially to an outside by the thrust nozzle wall,
- a central body arranged in the flow channel,
- at least two struts connecting the central body to the thrust nozzle wall,
- a thrust reverser integrated into the thrust nozzle, the thrust reverser including two pivotable thrust reverser doors which are rotatably mounted in two side structures of the thrust nozzle wall, the two side structures being formed on opposite sides of the thrust nozzle wall,
- the at least two struts being connected respectively to the two side structures of the thrust nozzle wall,
- wherein the central body is axially displaceable with respect to the thrust nozzle wall, and
- wherein the at least two struts are axially displaceable relative to the thrust nozzle wall.
5 more elements
Dependencies are inferred from the claim text.