Flow control device for a three stream turbofan engine

Patent metadata

Field	Value
Publication number	US-9506423-B2
Application number	US-201414206232-A
Country	US
Kind code	B2
Filing date	Mar 12, 2014
Priority date	Mar 14, 2013
Publication date	Nov 29, 2016
Grant date	Nov 29, 2016

Abstract

A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a core engine;
a first bypass passage disposed about the core engine;
a second bypass passage disposed about the first bypass passage, wherein the second bypass passage includes an outlet opening;
an exhaust nozzle defining an exhaust passage for a core gas flow from the core engine and a first bypass flow from the first bypass passage, wherein the outlet opening is disposed radially outward of the exhaust passage, the outlet opening including an open portion and a converging portion; and
a flow control disposed within the second bypass passage for controlling bypass airflow through the second bypass passage, the flow control movable axially between an open position and a closed position, the flow control comprising a tear-drop shape in cross-section, wherein the flow control translates axially aft to the closed position and axially forward to the open position, wherein the flow control seats against walls in the outlet opening of the second bypass passage in the closed position.

2. A gas turbine engine comprising:
a core engine;
a first bypass passage disposed about the core engine;
a second bypass passage disposed about the first bypass passage;
an exhaust nozzle defining an exhaust passage for a core gas flow from the core engine and a first bypass flow from the first bypass passage, wherein the second bypass passage includes an outlet opening disposed radially outward of the exhaust passage, the outlet opening including an open portion and a converging portion; and
a flow control disposed within the second bypass passage for controlling bypass airflow through the second bypass passage and the outlet opening, the flow control movable axially between an open position and a closed position, the open position disposed axially forward of the closed position, wherein the flow control seats against walls in the outlet opening of the second bypass passage when in the closed position to stop flow through the second bypass passage;
wherein the flow control comprises a tear-drop shape in cross-section, the tear-drop shape including a rounded shape upstream and a pointed surface downstream.

3. The gas turbine engine as recited in claim 2 , wherein the flow control is annular about an engine axis.

4. The gas turbine engine as recited in claim 2 , wherein the flow control translates axially rearward from the open position to the closed position.

5. The gas turbine engine as recited in claim 2 , including an actuator for moving the flow control axially parallel to a longitudinal axis of the core engine between the open and closed positions.

Assignees

• United Technologies Corp

Inventors

• Izquierdo Felix
• Bush Robert H
• Mcalice Timothy J

Classifications

• F02K3/077

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

• F02K1/383

  with retractable elements · CPC title

• F05D2270/051

  Thrust · CPC title

• F02K3/075 Primary

  controlling flow ratio between flows · CPC title

• F02K1/08

  by axially moving or transversely deforming an internal member, e.g. the exhaust cone · CPC title