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Gas-electric Propulsion System for An Aircraft
| Content Provider | The Lens |
|---|---|
| Related Links | https://www.lens.org/lens/patent/010-887-917-899-701/frontpage |
| Language | English |
| Publisher Date | 2019-04-03 |
| Access Restriction | Open |
| Alternative Title | Gas-elektro-antriebssystem Für Ein Luftfahrzeug Système De Propulsion Gaz-électrique Pour Un Avion |
| Content Type | Text |
| Resource Type | Patent |
| Date Applied | 2016-01-20 |
| Agent | Illingworth-law, William Illingworth |
| Applicant | Gen Electric |
| Application No. | 16152115 |
| Claim | A gas-electric propulsion system (100) for an aircraft (10), the system comprising: a pair of jet engines (102,104) suspendable beneath a wing (20) of the aircraft; an electric powered boundary layer ingestion fan (106) coupleable to a fuselage portion (12) of the aircraft aft of the wing; and an electric generator (108) electronically coupled to the pair of jet engines (102,104) and to the boundary layer ingestion fan (106), wherein the electric generator (108) converts rotational energy from at least one jet engine of the pair of jet engines to electrical energy; wherein the electric generator (108) provides at least a portion of the electrical energy to the boundary layer ingestion fan (106); characterized in that the boundary layer ingestion fan (106) is intended to be coupled to the fuselage portion (12) downstream from a tail section (18) of the aircraft. The system (100) as in claim 1, wherein each jet engine of the pair of jet engines (102,104) is a high-bypass ratio turbofan jet engine. The system (100) as in claim 2, wherein the high-bypass ratio turbofan jet engines (102,104) include a fan section (204) having a plurality of fan blades (232), wherein the fan blades are variable or fixed pitch. The system (100) as in claim 2, wherein the high-bypass ratio turbofan jet engines (102,104) are geared or direct drive. The system (100) as in any preceding claim, wherein the boundary layer ingestion fan (106) is configured to provide thrust to the aircraft (10). The system (100) as in any preceding claim, wherein the thrust provided by the boundary layer ingestion fan (106) is sufficient to independently propel the aircraft (10). The system (100) as in any preceding claim, wherein the boundary layer ingestion fan (106) includes an electric motor (304) electronically coupled to the electric generator (108). The system (100) as in any preceding claim, wherein the electric motor (304) is a superconductivity electric motor. The system (100) as in any preceding claim, wherein the electric generator (108) is a high pressure electric generator and is coupled to a high pressure spool of at least one jet engine of the pair of jet engines (102,104). The system (100) as in any preceding claim, wherein the electric generator (108) is a low pressure electric generator and it coupled to a low pressure spool of at least one jet engine of the pair of jet engines (102,104). The system (100) as in any preceding claim, further comprising an energy storage device (110) electronically coupled to the electric generator (108) and to the boundary layer ingestion fan (106). The system (100) as in any preceding claim, further comprising an energy management system (112). A method for propelling an aircraft (10) via a gas-electric propulsion system (100), the method comprising: providing electrical energy from an energy storage device (110) to an electric motor (304) of a boundary layer ingestion fan (106), wherein the boundary layer ingestion fan is mounted to the aircraft (10) aft of a wing (20) of the aircraft; and engaging an electric motor (304) of the boundary layer ingestion fan (106) to produce thrust sufficient to propel the aircraft (10); characterized in that the boundary layer ingestion fan (106) is mounted to the aircraft (10) downstream from a tail section (18) of the aircraft. |
| CPC Classification | EQUIPMENT FOR FITTING IN OR TO AIRCRAFT;FLIGHT SUITS;PARACHUTES;ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS Climate Change Mitigation Technologies Related To Transportation AEROPLANES;HELICOPTERS |
| Extended Family | 195-704-672-235-345 143-246-015-232-644 010-887-917-899-701 071-335-271-580-079 163-436-512-857-664 073-085-753-534-01X 013-945-280-753-394 173-920-992-618-730 070-361-145-163-533 054-952-795-430-271 049-303-963-564-113 079-970-989-462-366 086-519-958-698-736 187-919-183-581-667 030-390-193-262-837 181-811-323-662-096 067-172-944-978-981 |
| Patent ID | 3048042 |
| Inventor/Author | Hamel Jeffrey Anthony Murrow Kurt David |
| IPC | B64C21/06 B64D27/20 B64D27/24 |
| Status | Active |
| Simple Family | 195-704-672-235-345 143-246-015-232-644 010-887-917-899-701 071-335-271-580-079 163-436-512-857-664 073-085-753-534-01X 013-945-280-753-394 173-920-992-618-730 070-361-145-163-533 054-952-795-430-271 049-303-963-564-113 079-970-989-462-366 086-519-958-698-736 187-919-183-581-667 030-390-193-262-837 181-811-323-662-096 067-172-944-978-981 |
| CPC (with Group) | B64D27/02 B64D27/18 B64D27/20 Y10S903/905 Y10S903/906 Y10S903/907 Y02T50/60 Y02T50/10 B64C21/01 B64D27/33 B64D27/357 B64D31/18 B64D27/31 B64D27/026 B64D2205/00 |
| Issuing Authority | United States Patent and Trademark Office (USPTO) |
| Kind | Patent/Patent 1st level of publication/Inventor's certificate |
