Three stream, variable area, vectorable nozzle
AssigneeRolls-Royce North American Technologies Inc.
InventorsKenneth M. Pesyna, Anthony F. Pierluissi, Bryan H. Lerg, Justin N. Moore
Life of this patent
Estimating the term…
Abstract
An exhaust nozzle for a gas turbine engine may include a plurality of flap trains in the exhaust stream of the gas turbine engine. The flap trains are operable to selectively control three separate flow paths of gas that traverse the engine. A first stream of is the core airflow. The second stream of air is peeled off of the first stream to form a low pressure fan bypass air stream. The third stream of air traverses along the engine casing and is passed over a flap assembly to aid in cooling. The flaps are operable converge/diverge to control the multiple streams of air.
Claims20
A gas turbine engine having an exhaust nozzle, the engine comprising:
- a fan operable to direct intake air to an intake portion of a gas turbine engine, the intake air is separated into multiple streams of air throughout the engine, the multiple streams of air include:
- a first stream of air that is directed to a core of an engine;
- a second stream of air that is partitioned from the first stream of air, the second stream of air traverses a length of the engine;
- a third stream of air that is separated from the second stream of air, the third stream of air traverses a length of the engine and is injectable to a plenum of a nozzle;
- and
- the engine further comprising a nozzle assembly that is selectively operable to control the flow of the first, second and third streams of air in order to accommodate varying flight operating demands.
An exhaust nozzle for an engine comprising:
- a first stream of air that exits a core of an engine;
- a second stream of air that is conditioned by a heat exchanger, the second stream of air traverses a length of the nozzle and is directed to a plenum of the nozzle;
- and
- a third stream of air that is separated from the second stream of air, the third stream of air traverses a length of the engine and is injectable to a plenum of a nozzle, the third stream of air includes fan bypass air.
A method of transferring air through a gas turbine engine comprising:
- providing a first duct, a second duct, and a third duct;
- providing a fan to induce air into each of said ducts;
- providing a mechanical flap system;
- motivating the fan to cause first, second and third streams of air to be pushed through said first, second and third ducts, respectively;
- combusting the first stream of air to form a combusted stream of air and then combining the combusted stream of air with the second stream of air to form a core outlet air stream;
- separating the air in the third duct into a conditioned air stream and bypass air stream;
- and
- manipulating the mechanical flap system to control the flow of the core outlet air stream, the conditioned air stream, and the bypass air stream.
Dependencies are inferred from the claim text.