Convergent divergent exit nozzle for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11236701-B2
Application number	US-201816031202-A
Country	US
Kind code	B2
Filing date	Jul 10, 2018
Priority date	Aug 8, 2014
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

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.

First claim

The invention claimed is:

1. 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.

2. 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.

3. The gas turbine engine of claim 2 , wherein each of the isolated airflow passages extend a partial length of the secondary passage.

4. The gas turbine engine of claim 3 , wherein the plurality of airflow passages are fore of the circumferential ring duct, relative to a fluid flow through the secondary passage.

5. The gas turbine engine of claim 3 , wherein the plurality of airflow passages are aft of the circumferential ring duct, relative to a fluid flow through the secondary passage.

6. The gas turbine engine of claim 3 , wherein each of the isolated airflow passages is at least partially disposed in the divergent region of the convergent-divergent exit nozzle.

7. The gas turbine engine of claim 2 , wherein the circumferential ring duct is an unobstructed circumferential ring duct.

8. The gas turbine engine of claim 2 , further comprising a plurality of structures disposed circumferentially within said secondary passage, and wherein said plurality of structures supports a portion of the convergent-divergent exit nozzle, the portion being radially inward of the secondary passage.

Assignees

• Raytheon Tech Corp

Inventors

• Sidelkovskiy Dmitriy B
• Petrenko Oleg
• Malecki Robert E
• Zysman Steven H

Classifications

• F02K1/36 Primary

  having an ejector · CPC title

• F02K1/40

  Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet · CPC title

• F02K3/077

  the plant being of the multiple flow type, i.e. having three or more flows · CPC title

• F02K1/78 Primary

  Other construction of jet pipes · CPC title

• B64D29/02

  associated with wings · CPC title