Stepped fairing modulated exhaust cooling

Patent metadata

Field	Value
Publication number	US-10087884-B2
Application number	US-201514877607-A
Country	US
Kind code	B2
Filing date	Oct 7, 2015
Priority date	Dec 15, 2014
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing.

First claim

What is claimed is:

1. A system for a gas turbine engine, comprising:
at least one fairing;
a liner;
a convergent flap and a divergent flap that define a throat of the system; and
an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing,
wherein the modulation of the metering area by the actuator controls a radial dimension of the throat, and
wherein the modulation of the metering area by the actuator adjusts a bypass ratio between a first flow that is subjected to combustion in a core of the gas turbine engine and a second flow that bypasses the core.

2. The system of claim 1 , wherein the at least one fairing comprises a plurality of fairings.

3. The system of claim 1 , wherein the at least one airing comprises metal.

4. The system of claim 1 , wherein the metering area is based on a shape of the liner relative to a shape of the at least one fairing.

5. The system of claim 1 , wherein the metering area is based on a position of the liner relative to a position of the at least one fairing.

6. The system of claim 1 , wherein the metering area is based on a gap that exists between the liner and the at least one fairing.

7. The system of claim 1 , wherein the system is associated with an exhaust of the gas turbine engine.

8. A gas turbine engine, comprising:
a combustor section;
an exhaust nozzle;
at least one fairing;
a liner;
a convergent flap and a divergent flap that define a throat of the exhaust nozzle; and
an actuator configured to cause the at least one fairing to be translated relative to the liner to obtain a modulation of a metering area between the liner and the at least one fairing,
wherein the modulation of the metering area controls a dimension of the throat, and
wherein the modulation of the metering area adjusts a bypass ratio between a first flow that is subjected to combustion in the combustor section and a second flow that bypasses the combustor section.

9. The gas turbine engine of claim 8 , wherein the modulation of the metering area controls a radial dimension of the throat.

Assignees

• United Technologies Corp

Inventors

• Peters Donald W
• Bangerter James P

Classifications

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F02K1/1292

  of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure, the internal downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series and at their downstream ends on the downstream ends of the flaps of the external downstream series hinged at their upstream ends on a substantially axially movable structure · CPC title

• F02K1/1223 Primary

  of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series · CPC title

• F02K1/09 Primary

  by axially moving an external member, e.g. a shroud (F02K1/12 takes precedence) · CPC title

• F02K1/08

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