Nozzle for jet engines

Patent metadata

Field	Value
Publication number	US-10378477-B2
Application number	US-201615054982-A
Country	US
Kind code	B2
Filing date	Feb 26, 2016
Priority date	Apr 30, 2015
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

An exhaust system or nozzle for use in a gas turbine engine is disclosed herein. The exhaust system is adapted to adjust various streams of pressurized air produced by the gas turbine engine to control operation of the gas turbine.

First claim

What is claimed is:

1. A gas turbine engine comprising:
an engine core configured to discharge a first stream of pressurized core air that is passed through the engine core,
a fan coupled to the engine core to be driven by the engine core, the fan configured to discharge a second stream of pressurized bypass air and a third stream of pressurized bypass air that are passed around the engine core, and
an exhaust system coupled to the engine core, the exhaust system including a primary-stream nozzle arranged to adjust the first stream of pressurized core air discharged from the engine core and the second stream of pressurized bypass air discharged from the fan and including a third-stream nozzle arranged to adjust the third stream of pressurized bypass air discharged by the fan,
wherein the third stream of pressurized bypass air is adjustable via the third-stream nozzle based on adjustment of the first stream of pressurized core air and the second stream of pressurized bypass air by the primary-stream nozzle,
wherein the primary-stream nozzle includes at least one primary-stream duct wall, a plurality of forward primary-stream adjustment flaps mounted to pivot relative to the at least one primary-stream duct wall to adjust a primary-nozzle-throat defined between the plurality of forward primary-stream adjustment flaps, a plurality of aft primary-stream adjustment flaps mounted to move relative to the plurality of forward primary-stream adjustment flaps to adjust an outlet area of the primary-stream nozzle defined between the plurality of aft primary-stream adjustment flaps, one primary-stream-nozzle actuator coupled to at least one of the forward primary-stream adjustment flaps and configured to pivot the at least one of the forward primary-stream adjustment flaps relative to the primary-stream duct wall, and another primary-stream-nozzle actuator coupled to at least one of the aft primary-stream adjustment flaps and configured to move the at least one of the aft primary-stream adjustment flaps relative to the at least one of the forward primary-stream adjustment flaps.

2. The gas turbine engine of claim 1 , wherein the third-stream nozzle includes a third-stream duct wall and a plurality of third-stream adjustment flaps mounted to move relative to the third-stream duct wall between (i) a constricted position in which the third-stream adjustment flaps substantially close down a third-stream-nozzle throat defined between the third-stream adjustment flaps and a plurality of primary-stream adjustment flaps of the primary-stream nozzle to restrict the third stream of pressurized bypass air from passing through the third-stream nozzle and (ii) an unconstricted position in which the third-stream adjustment flaps open the third-stream-nozzle throat to allow the third stream of pressurized bypass air to pass more freely through the third-stream nozzle.

3. The gas turbine engine of claim 2 , wherein the third-stream nozzle includes third-stream-nozzle actuators coupled to the third-stream adjustment flaps and configured to pivot the third-stream adjustment flaps between the constricted position and the unconstricted position.

4. The gas turbine engine of claim 1 , wherein (i) each of the forward primary-stream adjustment flaps has a leading edge spaced forward of a trailing edge along a central axis of the gas turbine engine, and (ii) the primary-nozzle-throat is defined between the trailing edges of the forward primary-stream adjustment flaps.

5. The gas turbine engine of claim 4 , wherein (i) each of the aft primary-stream adjustment flaps has a trailing edge spaced aft of a leading edge along the central axis, and (ii) the outlet area is defined between the trailing edges of the aft primary-stream adjustment flaps.

6. The gas turbine engine of claim 1 , wherein each of the forward primary-stream adjustment flaps extends aft of the primary-stream duct wall toward a central axis of the gas turbine engine.

7. The gas turbine engine of claim 6 , wherein each of the aft primary-stream adjustment flaps extends aft of one of the forward primary-stream adjustment flaps away from the central axis.

8. A gas turbine engine comprising:
an engine core configured to discharge a first stream of pressurized core air that is passed through the engine core,
a fan coupled to the engine core to be driven by the engine core, the fan configured to discharge a second stream of pressurized bypass air and a third stream of pressurized bypass air that are passed around the engine core, and
an exhaust system coupled to the engine core, the exhaust system including a primary-stream nozzle arranged to adjust the first stream of pressurized core air discharged from the engine core and the second stream of pressurized bypass air and including a third-stream nozzle arranged to adjust the third stream of pressurized bypass air,
wherein the primary-stream nozzle includes a primary-stream duct wall, a plurality of forward primary-stream adjustment flaps mounted to pivot relative to the primary-stream duct wall to adjust a primary-nozzle-throat defined between the plurality of forward primary-stream adjustment flaps, and a plurality of aft primary-stream adjustment flaps mounted to pivot relative to the plurality of forward primary-stream adjustment flaps to adjust a primary-stream-nozzle outlet area defined between the plurality of aft primary-stream adjustment flaps,
wherein the primary-stream nozzle includes one primary-stream-nozzle actuator coupled to at least one of the forward primary-stream adjustment flaps and configured to pivot the at least one of the forward primary-stream adjustment flaps relative to the primary-stream duct wall and another primary-stream-nozzle actuator coupled to at least one of the aft primary-stream adjustment flaps and configured to move the at least one of the aft primary-stream adjustment flaps relative to the at least one of the forward primary-stream adjustment flaps.

9. The gas turbine engine of claim 8 , wherein the third-stream nozzle includes a third-stream duct wall and a plurality of third-stream adjustment flaps mounted to move relative to the third-stream duct wall between (i) a constricted position in which the third-stream adjustment flaps substantially close down a third-stream-nozzle throat defined between the third-stream adjustment flaps and the aft primary-stream adjustment flaps and (ii) an unconstricted position in which the third-stream adjustment flaps open the third-stream-nozzle throat.

10. The gas turbine engine of claim 9 , wherein the third-stream nozzle includes a third-stream-nozzle actuator coupled to the third-stream adjustment flaps and configured to pivot the third-stream adjustment flaps between the constricted position and the unconstricted position.

11. The gas turbine engine of claim 8 , wherein (i) the third-stream nozzle includes a third-stream duct wall and a plurality of third-stream adjustment flaps mounted to pivot relative to the third-stream duct wall to adjust a third-stream-nozzle throat defined between the plurality of third-stream adjustment flaps and the aft primary-stream adjustment flaps, and (ii) the third-stream-nozzle throat is adjustable based on adjustment of the primary-stream-nozzle throat.

12. An exhaust system for a gas turbine engine, the exhaust system comprising:
a primary-stream nozzle internal to an engine core of the gas turbine engine and arranged to adjust at least one of a primary stream of pressurized core air that is passed through and discharged from the engine core and a second stream of pressurized bypass air that is discharged from a fan of the gas turbine engine and passed around the engine core, and
a third-stream noz

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Pesyna Kenneth M

Classifications

• F02K3/075

  controlling flow ratio between flows · CPC title

• F02K1/12 Primary

  by means of pivoted flaps · CPC title

• F05D2240/128

  Nozzles · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F02K3/077

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