System and method for operating a boundary layer ingestion fan

Patent metadata

Field	Value
Publication number	US-11111029-B2
Application number	US-201715663380-A
Country	US
Kind code	B2
Filing date	Jul 28, 2017
Priority date	Jul 28, 2017
Publication date	Sep 7, 2021
Grant date	Sep 7, 2021

Abstract

An aircraft includes a fuselage having a tail section and an engine core coupled via an external pylon to the fuselage. The aircraft further includes a boundary layer ingestion (BLI) fan coupled to the tail section of the fuselage and coupled via a shaft to the engine core.

First claim

What is claimed is:

1. An aircraft comprising:
a fuselage having a tail section;
a first engine core without a third fan collocated with the first engine core to provide thrust to the aircraft, the first engine core coupled to the fuselage via an external pylon;
a boundary layer ingestion (BLI) fan coupled to the tail section of the fuselage and coupled to the first engine core via a shaft, wherein the shaft provides power that rotates the BLI fan;
a second engine core coupled to the fuselage, the second engine core including a second fan collocated with the second engine core to provide thrust to the aircraft; and
a propulsion system configured to adjust a thrust ratio between the BLI fan and one or more fans, wherein the one or more fans include the second fan, wherein the thrust ratio has a first value during a take-off portion of a flight, and wherein the thrust ratio is increased to a second value for a cruise portion of the flight.

2. The aircraft of claim 1 , wherein the BLI fan is configured to provide thrust to the aircraft based on rotation of the shaft.

3. The aircraft of claim 1 , wherein the second engine core is coupled to a BLI fan drive system to provide power to the BLI fan.

4. The aircraft of claim 1 , wherein the first engine core corresponds to a turboshaft engine, and wherein the second engine core corresponds to a turbofan engine, a propfan engine, or a turboprop engine.

5. The aircraft of claim 1 , further comprising a third engine core coupled to the fuselage, the third engine core including a fourth fan collocated with the third engine core to provide thrust to the aircraft.

6. The aircraft of claim 1 , further comprising a transmission configured to transfer power from the first engine core and the second engine core to the BLI fan, wherein the shaft and the transmission are included in a BLI fan drive system.

7. The aircraft of claim 1 , further comprising a second shaft coupled to the shaft via a gear system, the shaft coupled to the BLI fan and configured to receive power from the second shaft to rotate the BLI fan.

8. The aircraft of claim 1 , wherein the BLI fan includes an inlet configured to receive air from a boundary layer of the fuselage, and wherein the air from the boundary layer has a first speed that is less than a second speed of free stream air received by the first engine core.

9. The aircraft of claim 1 , further comprising a hydraulic drive system coupled to the shaft and to the BLI fan, the hydraulic drive system configured to transmit power from the shaft to the BLI fan.

10. The aircraft of claim 1 , further comprising at least one wing coupled to the fuselage, wherein the first engine core is coupled to the fuselage aft of the at least one wing.

11. An aircraft comprising:
a fuselage having a tail section;
a first engine core without a third fan collocated with the first engine core to provide thrust to the aircraft, the first engine core coupled to the fuselage via an external pylon;
a pair of wings coupled to the fuselage;
a second engine core coupled to a first wing of the wings, the second engine core including a second fan collocated with the second engine core to provide thrust to the aircraft;
a boundary layer ingestion (BLI) fan coupled to the tail section of the fuselage and coupled via a mechanical driveshaft system or a hydraulic drive system to the first engine core; and
a propulsion system configured to adjust a thrust ratio between the BLI fan and one or more fans, wherein the one or more fans include the second fan, wherein the thrust ratio has a first value during a take-off portion of a flight, and wherein the thrust ratio is increased to a second value for a cruise portion of the flight.

12. The aircraft of claim 11 , wherein the second engine core is positioned below the first wing.

13. The aircraft of claim 11 , wherein the second engine core is positioned above the first wing.

14. The aircraft of claim 11 , wherein the first engine core is coupled to the BLI fan via a first shaft of the mechanical driveshaft system.

15. The aircraft of claim 11 , wherein an auxiliary drive shaft coupled to the first engine core is coupled to drives a hydraulic pump of the hydraulic drive system.

16. An aircraft comprising:
a fuselage having a tail section;
a tail coupled to the tail section of the fuselage;
a first engine core coupled to the tail, the first engine core without a fan collocated with the first engine core to provide thrust to the aircraft;
a second engine core coupled to the fuselage, the second engine core including a second fan collocated with the second engine core to provide thrust to the aircraft;
a boundary layer ingestion (BLI) fan coupled to the tail section of the fuselage and coupled to the first engine core by a shaft; and
a propulsion system configured to adjust a thrust ratio between the BLI fan and one or more fans, wherein the one or more fans include the second fan, wherein the thrust ratio has a first value during a take-off portion of a flight, and wherein the thrust ratio is increased to a second value for a cruise portion of the flight.

17. The aircraft of claim 16 , wherein the second engine core is coupled to the tail section.

18. The aircraft of claim 16 , further comprising a third engine core coupled externally to the fuselage and configured to drive a fourth fan collocated with the third engine core to provide thrust to the aircraft.

19. The aircraft of claim 18 , wherein the second engine core is coupled to a BLI fan drive system to provide power to the BLI fan.

20. A method comprising:
generating power by a first engine core coupled by an external pylon to a fuselage of an aircraft, the first engine core without a third fan collocated with the first engine core to provide thrust to the aircraft;
generating thrust for the aircraft via a second fan of a second engine core coupled to the fuselage, wherein the first engine core and the second engine core are asymmetrically positioned relative to a longitudinal centerline of the fuselage;
applying the power via a shaft to a mechanical driveshaft system or a hydraulic drive system to drive a boundary layer ingestion (BLI) fan coupled to a tail section of the fuselage and aft of the first engine core, wherein driving the BLI fan causes the BLI fan to provide thrust to the aircraft; and
adjusting a thrust ratio between the BLI fan and one or more fans, wherein the one or more fans include the second fan, wherein the thrust ratio has a first value during a take-off portion of a flight, and wherein the thrust ratio is increased to a second value for a cruise portion of the flight.

21. The method of claim 20 , further comprising:
receiving, by an inlet of the first engine core, free stream air;
compressing, by a compressor of the first engine core, the free stream air to compressed free stream air; and
combusting, by a combustor of the first engine core, the compressed free stream air and fuel to rotate a turbine of the first engine core to generate the power.

Assignees

• Boeing Co

Inventors

• Hoisington Zachary Charles

Classifications

• B64D27/14

  within, or attached to, fuselages · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64D35/00

  Transmitting power from power plants to propellers or rotors; Arrangements of transmissions · CPC title

• B64D35/04

  characterised by the transmission driving a plurality of propellers or rotors · CPC title

• B64D27/20 Primary

  within, or attached to, fuselages · CPC title