Dedicated fans for boundary layer ingestion

Patent metadata

Field	Value
Publication number	US-10549845-B2
Application number	US-201715606051-A
Country	US
Kind code	B2
Filing date	May 26, 2017
Priority date	May 26, 2017
Publication date	Feb 4, 2020
Grant date	Feb 4, 2020

Abstract

A propulsion system for an aircraft including at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans. The propulsion system is arranged such that a combined thrust produced by the boundary layer ingestion fans is less than 20 percent of a total thrust of the main engines and the boundary layer ingestion fans. The boundary layer ingestion fans are controllable and selectively turned off at lower speeds.

First claim

The invention claimed is:

1. A propulsion system for an aircraft comprising:
at least two main gas turbine engines and a plurality of dedicated boundary layer ingestion fans;
wherein a total thrust provided by a combination of said at least two main gas turbine engines and said dedicated boundary layer ingestion fans is such that a combination of a thrust provided by said dedicated plurality of boundary layer ingestion fans is less than 20 percent of said total thrust;
wherein a control selectively turns said dedicated boundary layer ingestion fans off at lower aircraft speeds; and
said dedicated boundary layer ingestion fans are driven by a motor, said motor controlled by said control, and said motor being separate from said at least two main gas turbine engines.

2. The propulsion system as set forth in claim 1 , wherein said total thrust provided by said combination of said at least two main gas turbine engines and said dedicated boundary layer ingestion fans is such that said combination of said thrust provided by said dedicated plurality of boundary layer ingestion fans is less than 10 percent of said total thrust.

3. The propulsion system as set forth in claim 2 , wherein there are more than five of said dedicated boundary layer ingestion fans.

4. The propulsion system as set forth in claim 3 , wherein a diameter of said dedicated boundary layer ingestion fans is less than 15 inches and a fan pressure ratio at cruise condition is less than 1.5.

5. The propulsion system as set forth in claim 1 , wherein said lower aircraft speeds include takeoff of an associated aircraft.

6. The propulsion system as set forth in claim 1 , wherein a curved surface provides an inlet to said dedicated boundary layer ingestion fans.

7. The aircraft as set forth in claim 6 , wherein said total thrust provided by a combination of said at least two main gas turbine engines and said dedicated boundary layer ingestion fans is such that said combination of said thrust provided by said plurality of dedicated boundary layer ingestion fans is less than 10 percent of said total thrust.

8. An aircraft comprising:
a wide fuselage and having a tail section, with a plurality of main gas turbine engines mounted at a location outside said wide fuselage; and
a plurality of dedicated boundary layer ingestion fans mounted in said tail section of said aircraft to ingest boundary layer air created by said wide fuselage; and

wherein a total thrust provided by a combination of said at least two main gas turbine engines and said dedicated boundary layer ingestion fans is such that a combination of a thrust provided by said plurality of dedicated boundary layer ingestion fans is less than 20 percent of said total thrust.

9. The aircraft as set forth in claim 8 , wherein there are more than five of said dedicated boundary layer ingestion fans.

10. The aircraft as set forth in claim 9 , wherein a diameter of said dedicated boundary layer ingestion fans is less than 15 inches and a fan pressure ratio at cruise condition is less than 1.5.

11. The aircraft as set forth in claim 9 , wherein a control selectively turns said dedicated boundary layer ingestion fans off at lower aircraft speeds.

12. The aircraft as set forth in claim 11 , wherein said lower aircraft speeds include takeoff.

13. The aircraft as set forth in claim 11 , said dedicated boundary layer and ingestion fans are driven by a motor, said motor controlled by said control, and said motor being separate from said at least two main gas turbine engines.

14. The aircraft as set forth in claim 8 , wherein a control selectively turns said dedicated boundary layer ingestion fans off at lower aircraft speeds.

15. The aircraft as set forth in claim 14 , wherein said lower aircraft speeds include takeoff.

16. The aircraft as set forth in claim 14 , said dedicated boundary layer and ingestion fans are driven by a motor, said motor controlled by said control, and said motor being separate from said at least two main gas turbine engines.

17. The aircraft as set forth in claim 8 , wherein said wide fuselage is defined as having a height and a width with said width being greater than one and a half times said height.

18. The aircraft as set forth in claim 17 , wherein a curved surface on said fuselage provides an inlet to said dedicated boundary layer ingestion fans.

19. The aircraft as set forth in claim 8 , wherein said main gas turbine engine each have a fan independent of said boundary layer ingestion fans.

20. The propulsion system as set forth in claim 8 , wherein said main gas turbine engine each have a fan independent of said boundary layer ingestion fans.

Assignees

• United Technologies Corp

Inventors

• Epstein Alan H
• Suciu Gabriel L
• Chandler Jesse M

Classifications

• B64D2033/0226

  comprising boundary layer control means · CPC title

• B64C23/02 Primary

  by means of rotating members of cylindrical or similar form · CPC title

• B64C1/0009

  Aerodynamic aspects · CPC title

• B64C21/06 Primary

  for sucking (BLI propulsion B64C21/01) · CPC title

• Y02T50/10

  Drag reduction · CPC title