Box wing with angled gas turbine engine cores

Patent metadata

Field	Value
Publication number	US-9567062-B2
Application number	US-201314440895-A
Country	US
Kind code	B2
Filing date	Mar 14, 2013
Priority date	Nov 12, 2012
Publication date	Feb 14, 2017
Grant date	Feb 14, 2017

Abstract

An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone.

First claim

What is claimed is:

1. An aircraft lift system comprising;
an aft portion of a fuselage and a propulsion system mounted within the aft portion of the fuselage;
the propulsion system including first and second turbine engines, including respective first and second engine cores mounted so that respective first and second axes running therethrough are not-parallel;
wherein a defined burst zone from the engine cores extends outward and at a forward swept angle from the propulsion system, so that the burst zone has respective first and second forward edges; and
a box wing extending at a forward swept angle from the aft portion of the fuselage;
wherein first and second trailing edges of the box wing are disposed between respective first and second forward edges of the burst zone and the fuselage.

2. The system as recited in claim 1 , wherein the box wing is a rhomboidal wing.

3. The system as recited in claim 1 , wherein the box wing includes a forward primary wing portion and an upper horizontal stabilizer attached to the forward primary wing structure.

4. The system as recited in claim 3 , including a vertical stabilizer extending from the aft portion of the fuselage supporting the upper horizontal stabilizer.

5. The system as recited in claim 4 , wherein the vertical stabilizer is swept forward.

6. The system as recited in claim 1 , wherein the propulsion system comprises a first turbine engine including a first engine core that drives a first propulsor, wherein the first propulsor is disposed about a first propulsor axis and a second turbine engine including a second engine core and a second propulsor, wherein the second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis, and the first engine core and the second engine core are mounted at an angle relative to a corresponding one of the first and second propulsor axes.

7. The aircraft as recited in claim 6 , wherein the first engine core is disposed about a first engine axis and the second engine core is disposed about a second engine axis, wherein the first engine axis and the second engine axis are angled away from each other.

8. The aircraft as recited in claim 7 , wherein each of the first and second engine cores are each disposed outside of a burst zone defined about the other of the first and second engine cores.

9. The aircraft as recited in claim 8 , wherein the burst zone is defined as burst angle relative to a line extending perpendicular to each end of the corresponding first and second engine core.

10. The aircraft as recited in claim 6 , wherein a burst zone is defined about each of the first and second engine cores.

11. The aircraft as recited in claim 6 , wherein the first and second engine cores comprise a reverse flow gas turbine engine.

12. The aircraft as recited in claim 11 , wherein the first engine core is disposed about a first engine axis and the second engine core is disposed about a second engine axis, wherein the first engine axis and the second engine axis are angled away from each other.

13. The aircraft as recited in claim 11 , wherein each of the first and second engine cores are each disposed outside of a burst zone defined about the other of the first and second engine cores.

14. The aircraft as recited in claim 11 , wherein the first and second engine cores comprise a reverse flow gas turbine engine.

15. An aircraft comprising:
a fuselage including a forward portion and an aft portion;
a first turbine engine including a first engine core that drives a first propulsor, wherein the first propulsor is disposed about a first propulsor axis;
a second turbine engine including a second engine core and a second propulsor, wherein the second propulsor is disposed about a second propulsor axis parallel to the first propulsor axis, and the first engine core and the second engine core are mounted at an angle relative a corresponding one of the first and second propulsor axes, wherein a defined burst zone extends outward from each of the first and second engine cores; and
a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage, where the box wing is disposed outside of the burst zone.

16. The aircraft as recited in claim 15 , wherein the box wing includes a forward primary wing portion and an upper horizontal stabilizer attached to the forward primary wing structure.

17. The aircraft as recited in claim 16 , wherein the vertical stabilizer is swept forward.

18. The aircraft as recited in claim 15 , including a vertical stabilizer extending from the aft portion of the fuselage supporting the upper horizontal stabilizer.

Assignees

• United Technologies Corp

Inventors

• Chandler Jesse M
• Suciu Gabriel L

Classifications

• F02K1/56 Primary

  Reversing jet main flow · CPC title

• B64C39/068

  having multiple wings joined at the tips · CPC title

• B64C5/06 Primary

  Fins (B64C5/08 takes precedence) · CPC title

• B64C39/10

  All-wing aircraft · CPC title

• B64C39/12

  Canard-type aircraft · CPC title