Convergent divergent exit nozzle for a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsDmitriy B. Sidelkovskiy, Oleg Petrenko, Robert E. Malecki, Steven H. Zysman
Life of this patent
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Abstract
A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.
Claims8
A gas turbine engine comprising:
- an engine core and a fan driven by the engine core;
- a nacelle radially surrounding the engine core and the fan;
- a bypass passage including a convergent-divergent exit nozzle, the bypass passage being defined by the nacelle at an outer diameter of the bypass passage and by an outer diameter of the engine core at an inner diameter of the bypass passage, wherein the convergent-divergent exit nozzle includes:
- a primary passage and a secondary passage radially exterior to the primary passage, wherein the secondary passage includes a secondary passage inlet disposed in a convergent region of the convergent-divergent exit nozzle, a secondary passage outlet disposed in a divergent region of the convergent-divergent exit nozzle, and wherein the secondary passage includes a circumferential ring duct and a plurality of isolated airflow passages;
- and
- wherein the plurality of isolated airflow passages are aft of the circumferential ring duct, relative to a fluid flow through the secondary passage, and wherein each of the plurality of isolated airflow passages are directly connected to the secondary passage outlet.
A gas turbine engine comprising:
- an engine core and a fan driven by the engine core;
- a nacelle radially surrounding the engine core and the fan;
- a bypass passage including a convergent-divergent exit nozzle, the bypass passage being defined by the nacelle at an outer diameter of the bypass passage and by an outer diameter of the engine core at an inner diameter of the bypass passage, wherein the convergent-divergent exit nozzle includes:
- a primary passage and a secondary passage radially exterior to the primary passage, wherein the secondary passage includes a secondary passage inlet disposed in a convergent region of the convergent-divergent exit nozzle, a secondary passage outlet disposed in a divergent region of the convergent-divergent exit nozzle, and wherein the secondary passage includes a circumferential ring duct and a plurality of isolated airflow passages;
- and
- wherein the secondary passage outlet of the secondary passage and an outlet of the convergent-divergent exit nozzle are axially aligned, relative to an axis defined by the gas turbine engine.
Dependencies are inferred from the claim text.