Supersonic aircraft turbofan

Patent metadata

Field	Value
Publication number	US-11053886-B2
Application number	US-201916456870-A
Country	US
Kind code	B2
Filing date	Jun 28, 2019
Priority date	Jul 20, 2018
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A turbofan engine having: an engine core having a centre axis and including in flow series a compressor, a combustor and a turbine; and a bypass duct surrounding the engine core, the bypass duct has a bypass duct exit area at its downstream end. The engine further includes an exhaust nozzle assembly including: coaxially arranged inner mixer and outer exhaust nozzles, the exhaust nozzle being axially downstream of said mixer nozzle; a core flow duct defined by the mixer nozzle, the core flow duct having a core exit area; and an exhaust duct defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust throat area.

First claim

We claim:

1. A turbofan engine comprising:
an engine core having a centre axis and comprising in flow series a compressor, a combustor and a turbine;
a bypass duct surrounding the engine core, the bypass duct having a bypass duct exit area at its downstream end; and
a nozzle assembly comprising:
an inner mixer nozzle and an outer exhaust nozzle that are coaxially arranged about the centre axis, the exhaust nozzle being axially downstream of the mixer nozzle;
a core flow duct defined by the mixer nozzle, the core flow duct having a core exit area; and
an exhaust duct defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust throat area,

wherein the bypass duct exit area and the core exit area are axially aligned at a mixing plane to form a mixing plane area;
wherein the turbofan engine has a transonic thrust condition, a supersonic cruise condition and a take-off condition; and
wherein the turbofan engine further comprises means for adjusting the nozzle assembly by which:
(1) in the supersonic cruise condition, the exhaust throat area is increased relative to the exhaust throat area in the transonic condition; and
(2) in the take-off condition, (i) the core exit area is increased relative to the core exit area in the transonic condition and (ii) the bypass duct exit area is decreased relative to the bypass duct exit area in the transonic condition.

2. The turbofan engine according to claim 1 , wherein in the supersonic cruise condition, and by way of the means for adjusting the nozzle assembly:
(1) the core exit area is increased by between 20 and 60% relative to the core exit area in the transonic condition,
(2) the bypass duct exit area is decreased by 10 to 40% relative to the bypass duct exit area in the transonic condition, and
(3) the mixing plane area is decreased by between 0 to 10% relative to the mixing plane area in the transonic condition.

3. The turbofan engine according to claim 1 , wherein in the take-off condition, and by way of the means for adjusting the nozzle assembly:
(1) the core exit area is increased by between 40 and 60% relative to the core exit area in the transonic condition,
(2) the bypass duct exit area is decreased by 25 to 40% relative to the bypass duct exit area in the transonic condition, and
(3) the mixing plane area is decreased by between 5 to 10% relative to the mixing plane area in the transonic condition.

4. The turbofan engine according to claim 1 , wherein:
the nozzle assembly further comprises a plug axially mounted within the mixer nozzle, and
the plug comprises an axial variation in its radial cross-section from its upstream end to its downstream end.

5. The turbofan engine according to claim 4 , wherein:
the means for adjusting the nozzle assembly comprises the mixer nozzle and the plug, and
the mixer nozzle and the plug are axially translatable in order to effect variation in values of the core exit area, the bypass duct exit area and the mixing plane area.

6. The turbofan engine according to claim 1 , wherein, in the supersonic cruise condition, and by way of the means for adjusting the nozzle assembly, the exhaust throat area is increased by between 5 and 15% relative to the exhaust throat area in the transonic condition.

7. The turbofan engine according to claim 1 , wherein in the take-off condition, and by way of the means for adjusting the nozzle assembly, the exhaust throat area is increased relative to the exhaust throat area in the transonic condition.

8. The turbofan engine according to claim 7 , wherein in the take-off condition, and by way of the means for adjusting the nozzle assembly, the exhaust throat area is increased by between 0 and 15% relative to the exhaust throat area in the transonic condition.

9. The turbofan engine according to claim 1 , further comprising:
a fan located upstream of the engine core; and
a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake;
wherein the fan is configured to generate a core airflow to the engine core and a bypass airflow through the bypass duct.

10. The turbofan engine according to claim 1 , wherein
the means for adjusting the nozzle assembly comprises a controller configured to control the exhaust throat area, the core exit area, and the bypass duct exit area.

11. A supersonic aircraft having a turbofan engine according to claim 1 .

12. A method of operating a turbofan engine,
the turbofan engine comprising:
an engine core having a centre axis and comprising in flow series a compressor, a combustor and a turbine;
a bypass duct surrounding the engine core, the bypass duct having a bypass duct exit area at its downstream end; and
a nozzle assembly comprising:
an inner mixer nozzle and an outer exhaust nozzle that are coaxially arranged about the centre axis, the exhaust nozzle being axially downstream of the mixer nozzle;
a core flow duct defined by the mixer nozzle, the core flow duct having a core exit area; and
an exhaust duct defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust throat area,

wherein the bypass duct exit area and the core exit area are axially aligned at a mixing plane to form a mixing plane area; and
the method comprising:
performing a take-off operation;
performing a transonic thrust operation; and
performing a supersonic cruise operation;
wherein in the supersonic cruise condition, the exhaust throat area is increased relative to the exhaust throat area in the transonic condition; and
wherein in the take-off condition, (i) the core exit area is increased relative to the core exit area in the transonic condition and (ii) the bypass duct exit area is decreased relative to the bypass duct exit area in the transonic condition.

13. The method according to claim 12 , further comprising, in the supersonic cruise condition:
(1) increasing the core exit area by between 20 and 60% relative to the core exit area in the transonic condition,
(2) decreasing the bypass duct exit area by 10 to 40% relative to the bypass duct exit area in the transonic condition, and
(3) decreasing the mixing plane area by between 0 to 10% relative to the mixing plane area in the transonic condition.

14. The method according to claim 12 , further comprising, in the take-off condition:
(1) increasing the core exit area by between 40 and 60% relative to the core exit area in the transonic condition,
(2) decreasing the bypass duct exit area by 25 to 40% relative to the bypass duct exit area in the transonic condition, and
(3) decreasing the mixing plane area by between 5 to 10% relative to the mixing plane area in the transonic condition.

15. The method according to claim 12 , further comprising, in the supersonic cruise condition, increasing the exhaust throat area by between 5 and 15% relative to the exhaust throat area in the transonic condition.

16. The method according to claim 12 , further comprising, in the take-off condition, increasing the exhaust throat area by between 0 and 15% relative to the exhaust throat area in the transonic condition.

Assignees

• Rolls Royce Plc

Inventors

• Whurr John R
• Hickey Conor

Classifications

• F02K1/48 Primary

  Corrugated nozzles · CPC title

• F02K1/386

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title

• F02K1/08 Primary

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

• F02K1/1207

  of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence) · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title