Stabilizer assembly for an aircraft AFT engine

Patent metadata

Field	Value
Publication number	US-10106265-B2
Application number	US-201615191586-A
Country	US
Kind code	B2
Filing date	Jun 24, 2016
Priority date	Jun 24, 2016
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

An aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft is presented. The stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. The inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.

First claim

What is claimed is:

1. An aircraft having a fuselage, the aircraft comprising:
a propulsion system, the propulsion system comprising:
an aft engine configured to be mounted to the aircraft at an aft end of the aircraft, the aft engine defining a central axis, the aft engine comprising a fan comprising a plurality of fan blades rotatable about the central axis and a nacelle surrounding the plurality of fan blades;
a stabilizer assembly comprising:
at least one generally horizontal stabilizer comprising an inner portion and an outer portion, the inner portion being mounted to the nacelle of the fan and the fuselage at a predetermined downward angle with respect to the central axis so as to direct airflow upwards and into the fan, the outer portion being mounted to the inner portion.

2. The propulsion system of claim 1 , wherein the inner portion comprises a longer chord than the outer section of the stabilizer assembly.

3. The propulsion system of claim 1 , wherein a cross-section of the inner portion comprises an inverted airfoil cross-section.

4. The propulsion system of claim 1 , wherein a cross-section of the inner portion of the stabilizer assembly tapers from a first end to a second end.

5. The propulsion system of claim 1 , wherein the predetermined downward angle comprises from about 20 degrees to about 45 degrees with respect to the central axis in a downward vertical direction.

6. The propulsion system of claim 1 , wherein the aft engine is configured as a boundary layer ingestion fan, and wherein the additional stabilizers are configured to direct fuselage bottom boundary layer airflow upwards and into the fan.

7. The propulsion system of claim 1 , wherein the aft engine is configured to be mounted to an aircraft having a pair of wings, and wherein the propulsion system further includes two or more aircraft engines, each of which mounted to one of the pair of wings of the aircraft.

8. An aircraft having a fuselage, the aircraft comprising:
a boundary layer ingestion fan assembly for mounting to an aft end of a fuselage of an aircraft, the boundary layer ingestion fan assembly comprising:
a fan rotatable about a central axis of the boundary layer ingestion fan, the fan comprising a plurality of fan blades;
a nacelle surrounding the plurality of fan blades of the fan, the nacelle defining an inlet with the fuselage of the aircraft, the inlet extending substantially around the fuselage of the aircraft when the boundary layer ingestion fan is mounted at the aft end of the aircraft;
a stabilizer assembly comprising:
at least one generally horizontal stabilizer comprising an inner portion and an outer portion, the inner portion being mounted to the nacelle of the fan and the fuselage at a predetermined downward angle with respect to the central axis so as to direct airflow upwards and into the fan, the outer portion being mounted to the inner portion.

9. The boundary layer ingestion fan assembly of claim 8 , wherein the inner portion of the stabilizer assembly is integrated with one or more inlet guide vanes of the aft fan.

10. The boundary layer ingestion fan assembly of claim 8 , wherein the inner portion comprises a loner chord than the outer section of the stabilizer assembly.

11. The boundary layer ingestion fan assembly of claim 8 , wherein a cross-section of the inner portion comprises an inverted airfoil cross-section.

12. The boundary layer ingestion an assembly of claim 8 , wherein a cross-section of the inner portion of the stabilizer assembly tapers from a first end to a second end.

13. The boundary layer ingestion fan assembly of claim 8 , wherein the predetermined downward angle comprises from about 20 degrees to about 45 degrees with respect to the central axis in a downward vertical direction.

14. An aircraft having a fuselage, the aircraft comprising:
An an aerodynamic stabilizer assembly for stabilizing an aft fan mounted to the fuselage of the aircraft, the stabilizer assembly comprising:
at least two generally horizontal stabilizers for mounting to opposite sides of a nacelle of the aft fan and the fuselage so as to stabilize the aft fan, each of the generally horizontal stabilizers comprising an inner portion and an outer portion, the inner portions being mounted to the nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.

15. The stabilizer assembly of claim 14 , wherein the inner portion of the stabilizer assembly is integrated with one or more inlet guide vanes of the aft fan.

16. The stabilizer assembly of claim 14 , wherein a cross-section of the inner portion comprises an inverted airfoil cross-section.

Assignees

• Gen Electric

Inventors

• Yao Jixian
• Breeze-Stringfellow Andrew

Classifications

• B64C1/26

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64D27/14

  within, or attached to, fuselages · CPC title

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64D27/18

  within, or attached to, wings · CPC title