Distributed propulsion and electric power generation system

Patent metadata

Field	Value
Publication number	US-10738692-B2
Application number	US-201715709541-A
Country	US
Kind code	B2
Filing date	Sep 20, 2017
Priority date	Sep 20, 2017
Publication date	Aug 11, 2020
Grant date	Aug 11, 2020

Abstract

A propulsion and electric power generation system includes a gas turbine propulsion engine, an electrical generator, an aircraft power distribution system, a plurality of auxiliary fans, and a controller. The gas turbine propulsion engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool, and the low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and generates a total amount of electrical power (Pe). The aircraft power distribution system receives a first fraction (Pa) of the total amount of electrical power. The auxiliary fans receive a second fraction (Pf) of the total amount of electrical power. The controller is configured to control a ratio of Pf to Pa (Pf/Pa) such that the ratio spans a range from less than 0.6 to at least 0.9.

First claim

What is claimed is:

1. A propulsion and electric power generation system, comprising:
a gas turbine propulsion engine including at least a low-pressure turbine coupled to a fan via a low-pressure spool, the low-pressure turbine configured to generate mechanical power;
an electrical generator directly connected to the low-pressure spool and disposed downstream of the low-pressure turbine, the electrical generator configured, upon receiving a portion of the mechanical power generated by the low-pressure turbine, to generate a total amount of electrical power (P e );
an aircraft power distribution system electrically coupled to the electrical generator to receive a first fraction (P a ) of the total amount of electrical power generated by the electrical generator;
a plurality of electrically-powered auxiliary fans electrically coupled to the electrical generator to receive a second fraction (P f ) of the total amount of electrical power generated by the electrical generator; and
a controller coupled to receive signals that are at least representative of P a and P f , the controller configured, in response to these signals, to control a ratio of P f to P a (P f /P a ),
wherein:
the controller is configured to control the ratio of (P f /P a ) over a range of values,
the range of values spans from a non-zero value that is less than 0.6 to a value that is at least 0.9,
a first fraction of the mechanical power generated by the low-pressure turbine is supplied to the fan for propulsive power generation (P t ),
a second fraction of the mechanical power generated by the low-pressure turbine is controllably supplied to the electrical generator for generating the total amount of electrical power (P e ), and
the controller is further coupled to receive signals that are at least representative of P e and P t , and
the controller is further configured, in response to the signals that are at least representative of P e and P t , to control the ratio of P f to P a (P f /P a ) such that there is at least one operating condition where P f /P a is less than 0.6 when P e /P t is greater than 0.3 and at least one other operating condition where P f /P a is greater than 0.9 when P e /P t is less than 0.1.

2. The system of claim 1 , wherein the controller is further configured to control a ratio of P e to P t (P e /P t ), during operation of the gas turbine propulsion engine, to a range from less than 0.06 to at least 0.18.

3. The system of claim 1 , further comprising:
a speed reduction gear box disposed between the low-pressure turbine and the fan.

4. The system of claim 1 , further comprising:
a plurality of auxiliary fan air ducts, each fan air duct having one of the electrically-powered auxiliary fans disposed therein.

5. The system of claim 4 , wherein each electrically-powered auxiliary fan, upon being energized, supplies a flow of air that, upon exiting the fan air duct in which it is disposed, generates a thrust.

6. The system of claim 4 , wherein at least a portion of the flow of air from one or more of the electrically-powered auxiliary fans is directly applied to one or more heat loads.

7. The system of claim 4 , further comprising:
at least one heat exchanger, the at least one heat exchanger disposed within one of the fan air ducts,
wherein at least one of the electrically-powered auxiliary fans, upon being energized, flows air through the at least one heat exchanger that is disposed within the same one of the fan air ducts.

8. The system of claim 1 , wherein the electrical generator is configured to generate from 200 kilowatt to about 1.5 megawatt of electrical power.

9. An aircraft propulsion and electric power generation system, comprising:
an aircraft;
a gas turbine propulsion engine mounted on the aircraft and including at least a low-pressure turbine coupled to a fan via a low-pressure spool, the low-pressure turbine configured to generate mechanical power;
a plurality of auxiliary fan air ducts disposed within the aircraft;
an electrical generator directly connected to the low-pressure spool and disposed downstream of the low-pressure turbine, the electrical generator configured, upon receiving a portion of the mechanical power generated by the low-pressure turbine, to generate a total amount of electrical power (P e );
an aircraft power distribution system electrically coupled to the electrical generator to receive a first fraction (P a ) of the total amount of electrical power generated by the electrical generator;
a plurality of electrically-powered auxiliary fans electrically coupled to the electrical generator to receive a second fraction (P f ) of the total amount of electrical power generated by the electrical generator, each electrically-powered auxiliary fan disposed within a different one of the auxiliary fan ducts; and
a controller coupled to receive signals that are at least representative of P a and P f , the controller configured, in response to these signals, to control a ratio of P f to P a (P f /P a ) such that the ratio spans a range from less than 0.6 to at least 0.9,
wherein:
the controller is configured to control the ratio of (P f /P a ) over a range of values,
the range of values spans from a non-zero value that is less than 0.6 to a value that is at least 0.9, and
each electrically-powered auxiliary fan, upon being energized, supplies a flow of air that, upon exiting the fan air duct in which it is disposed, generates a thrust on the fuselage.

10. The system of claim 9 , wherein:
a first fraction of the mechanical power generated by the low-pressure turbine is supplied to the fan for propulsive power generation (P t ),
a second fraction of the mechanical power generated by the low-pressure turbine is controllably supplied to the electrical generator for generating the total amount of electrical power (P e ), and
the controller is further coupled to receive signals that are at least representative of P e and P t , and is further configured, in response to these signals, to control the ratio of P f to P a (P f /P a ) such that there is at least one operating condition where P f /P a is less than 0.6 when P e /P t is greater than 0.3 and at least one other operating condition where P f /P a is greater than 0.9 when P e /P t is less than 0.1.

11. The system of claim 10 , wherein the controller is further configured to control a ratio of P e to P t (P e /P t ), during operation of the gas turbine propulsion engine, to a range from less than 0.06 to at least 0.18.

12. The system of claim 9 , wherein at least a portion of the flow of air from one or more of the electrically-powered auxiliary fans is directly applied to one or more heat loads.

13. The system of claim 9 , further comprising:
a plurality of heat exchangers, each heat exchanger disposed within a different one of the fan air ducts,
wherein each electrically-powered auxiliary fan, upon being energized, flows air through the heat exchanger that is disposed within the same fan air duct.

14. The system of claim 9 , wherein the electrical generator is configured to generate from 200 kilowatt to about 1.5 megawatt of electrical power.

15. An aircraft propulsion and electric power generation system, comprising:
an aircraft;
a gas turbine propulsion engine mounted on the aircraft and including at least a low-pressure turbine coupled to a fan via a low-pressure spool, the low-pressure turbine configured to generate mechanical power;
a plurality of auxiliary fan air ducts disposed within the aircraft;
an electrical generator directly connected to the low-pressure spool and disposed

Assignees

• Honeywell Int Inc

Inventors

• Nolcheff Nick
• Meier John
• Laffan James
• Hemmingson Alan D
• Anghel Cristian
• Koerner Mike

Classifications

• B64D27/31

  within, or attached to, wings · CPC title

• B64D35/024

  of series type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• F02B77/14 Primary

  Engine-driven auxiliary devices combined into units · CPC title