Wide fuselage aircraft with increased boundary layer ingestion

Patent metadata

Field	Value
Publication number	US-9611034-B1
Application number	US-201514930712-A
Country	US
Kind code	B1
Filing date	Nov 3, 2015
Priority date	Nov 3, 2015
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

An arrangement for reducing drag on the body of an aircraft with a relatively wide fuselage comprises a gas turbine engine. At least one duct is selectively moveable between a closed position and an open position, such that the at least one duct allows airflow to move toward a fan rotor in the gas turbine engine in the open position, but blocks airflow when in the closed position. An aircraft body is also disclosed.

First claim

The invention claimed is:

1. An arrangement for reducing drag on the body of an aircraft with a relatively wide fuselage comprising:
a gas turbine engine;
at least one duct wall being selectively moveable between a closed position and an open position, such that said at least one duct wall allows airflow from below the fuselage to move toward a fan rotor in said gas turbine engine in said open position, but blocks airflow when in said closed position, and said at least one duct wall being in said closed position at take-off, and in said open position at cruise; and
airflow from an upper surface of the fuselage that will receive said arrangement will reach the fan rotor when said at least one duct wall is in both said open or closed positions.

2. The arrangement as set forth in claim 1 , wherein there are at least two of said duct walls, with each of said duct walls being moveable between open and closed positions.

3. The arrangement as set forth in claim 2 , wherein airflow from an upper surface of the aircraft fuselage that will receive said arrangement will reach the fan rotor when said at least two duct walls are in both said open or closed positions.

4. The arrangement as set forth in claim 2 , wherein at least one motor and control drive said at least two duct walls between the open and closed positions.

5. The arrangement as set forth in claim 4 , wherein a mechanical connection connects each of said at least two duct walls, such that a single one of said at least one motor can drive said at least two duct walls.

6. The arrangement as set forth in claim 4 , wherein said at least two duct walls pivot about pivot axes between the open and closed positions.

7. The arrangement as set forth in claim 1 , wherein said at least one duct wall pivots about a pivot axis between the open and closed positions.

8. The arrangement as set forth in claim 1 , wherein a motor and control drive the duct wall between the open and closed positions.

9. An aircraft body comprising:
a relatively wide fuselage leading toward a tail section, and a pair of gas turbine engines mounted in said tail section;
an upper surface of said fuselage leading into an inlet which is positioned vertically below said upper surface to deliver boundary layer air from the upper surface into said gas turbine engines;
at least one duct wall selectively moveable between a blocking position and an open position, such that said at least one duct wall allows airflow from below the fuselage to move toward a fan rotor in said gas turbine engines in said open position, but blocks airflow when in said closed position, and said at least one duct wall being in said closed position at take-off, and in said open position at cruise;
airflow from an upper surface of the fuselage that will receive said arrangement will reach the fan rotor when said at least one duct wall is in both said open or closed positions; and
the relatively wide fuselage has a width and a height, and a width to height ratio is greater than or equal to at least 1.5.

10. The aircraft body as set forth in claim 9 , wherein there are at least two duct walls, with each of said duct walls being moveable between open and closed positions.

11. The aircraft body as set forth in claim 10 , wherein airflow from an upper surface of the fuselage that will receive said arrangement will reach the fan rotor when said at least two duct walls are in both said open or closed positions.

12. The aircraft body as set forth in claim 11 , wherein at least one motor and control drive said at least two duct walls between the open and closed positions.

13. The aircraft body as set forth in claim 12 , wherein a mechanical connection connects each of said at least two duct walls, such that a single one of said at least one motor can drive said at least two duct walls.

14. The aircraft body as set forth in claim 13 , wherein said at least two duct walls pivot about pivot axes between the open and closed positions.

15. The aircraft body as set forth in claim 10 , wherein at least one motor and control drive said at least two duct walls between the open and closed positions.

16. The aircraft body as set forth in claim 15 , wherein a mechanical connection connects each of said at least two duct walls, such that a single one of said at least one motor can drive said at least two ducts.

17. The aircraft body as set forth in claim 9 , wherein said at least one duct wall pivots about a pivot axis between the open and closed positions.

18. The aircraft body as set forth in claim 9 , wherein a motor and control drive the at least one duct wall between the open and closed positions.

Assignees

• United Technologies Corp

Inventors

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

Classifications

• B64D2033/0253

  specially adapted for particular type of aircraft · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64C2230/06

  by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure · CPC title

• B64C21/08 Primary

  adjustable · CPC title