Angled reverse core gas turbine engine with widened nozzle

Patent metadata

Field	Value
Publication number	US-10502085-B2
Application number	US-201414265856-A
Country	US
Kind code	B2
Filing date	Apr 30, 2014
Priority date	Feb 25, 2014
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

A propulsion system for an aircraft includes a furcated nozzle that has at least a first duct that extends from a first propulsor to a first trailing end duct opening and a second duct that extends from a second propulsor to a second trailing end duct opening.

First claim

What is claimed is:

1. A propulsion system for an aircraft, comprising:
a first turbine engine including a first engine core having a first compressor, a first combustor, a first turbine, and a first intake duct leading into the first compressor;
a second turbine engine including a second engine core having a second compressor, a second combustor, a second turbine, and a second intake duct leading into the second compressor;
a first propulsor coupled to be driven by the first turbine engine, the first propulsor being disposed about a first propulsor axis and the first engine core being disposed about a first core axis that is skewed from the first propulsor axis;
a second propulsor coupled to be driven by the second turbine engine, the second propulsor being disposed about a second propulsor axis parallel to the first propulsor axis, and the second engine core being disposed about a second core axis that is skewed from the second propulsor axis; and
a furcated nozzle having at least a first duct extending from the first propulsor to a first trailing end duct opening and a second duct extending from the second propulsor to a second trailing end duct opening, wherein the first trailing end duct opening and the second trailing end duct opening are each laterally elongated.

2. The propulsion system as recited in claim 1 , wherein the first intake duct is within the first duct of the furcated nozzle, and the second intake duct is within the second duct of the furcated nozzle.

3. The propulsion system as recited in claim 1 , wherein the first duct and the second duct share a common wall there between.

4. The propulsion system as recited in claim 1 , wherein the first trailing end duct opening and the second trailing end duct opening are symmetric with respect to a plane between the first duct and the second duct.

5. The propulsion system as recited in claim 1 , wherein the first trailing end duct opening is elongated along a first direction and the second trailing end duct opening is elongated along a second direction that is coaxial with the first direction.

6. The propulsion system as recited in claim 1 , wherein the first trailing end duct opening is elongated along a first direction and the second trailing end duct opening is elongated along a second direction that is non-coaxial with the first direction.

7. The propulsion system as recited in claim 1 , wherein at least the first trailing end duct opening includes four quadrants with regard to the first propulsor axis that are equal in cross-sectional area.

8. The propulsion system as recited in claim 1 , wherein the first core axis, the second core axis, the first propulsor axis, and the second propulsor axis are non-coplanar.

9. The propulsion system as recited in claim 1 , wherein the first core axis, the second core axis, the first propulsor axis, and the second propulsor axis are coplanar.

10. The propulsion system as recited in claim 1 , wherein the first core axis is skewed from the second core axis.

11. The propulsion system as recited in claim 1 , wherein the first turbine engine and the second turbine engine are respective reverse flow turbine engines.

12. A nozzle for a multi-engine propulsion system, comprising:
a furcated nozzle including a first duct extending from a first forward end duct opening to a first trailing end duct opening and a second duct extending from a second forward end duct opening to a second trailing end duct opening, the first trailing end duct opening and the second trailing end duct opening being laterally elongated.

13. The nozzle as recited in claim 12 , wherein the first duct and the second duct share a common wall there between.

14. The nozzle as recited in claim 12 , wherein the first trailing end duct opening and the second trailing end duct opening are symmetric with respect to a plane between the first duct and the second duct.

15. The nozzle as recited in claim 12 , wherein the first trailing end duct opening is elongated along a first direction and the second trailing end duct opening is elongated along a second direction that is coaxial with the first direction.

16. The nozzle as recited in claim 12 , wherein the first trailing end duct opening is elongated along a first direction and the second trailing end duct opening is elongated along a second direction that is non-coaxial with the first direction.

17. The propulsion system as recited in claim 1 , wherein the first core axis and the second core axis diverge in an aft direction.

Assignees

• United Technologies Corp

Inventors

• Lord Wesley K
• Chandler Jesse M
• Suciu Gabriel L

Classifications

• F01D13/006

  one being a reverse turbine · CPC title

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F01D13/003 Primary

  with at least two independent shafts, i.e. cross-compound · CPC title

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title