AIRCRAFT PROPELLED BY A TURBOJET ENGINE WITH CONTRAROTATING FANS

• US 20150291285A1
• Filed: 10/29/2013
• Published: 10/15/2015
• Est. Priority Date: 11/08/2012
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Gallet, Franois
• Granted Patent: US 10,435,163 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 2027/005 Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• CPC Class Codes: B64D 2033/0273 for jet engines
• CPC Class Codes: B64D 2033/0286 for turbofan engines
• CPC Class Codes: B64D 27/14 within, or attached to, fuselages
• CPC Class Codes: B64D 27/20 within, or attached to, fuselages
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00
• CPC Class Codes: F01D 13/02 Working-fluid interconnection of machines or engines
• CPC Class Codes: F02C 6/02 Plural gas-turbine plants having a common power output
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An aircraft propelled by a turbojet having contrarotating fans, the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and including two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators, and distinct air intakes for feeding each gas generator, the air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft.

Claims

1. An aircraft propelled by a turbojet having contrarotating fans, the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and comprising two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators, and distinct air intakes for feeding each gas generator, said air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft.

2. An aircraft according to claim 1, wherein the fans present an outside diameter that is substantially identical to the maximum diameter of the fuselage of the aircraft.

3. An aircraft according to claim 1, wherein the gas generators are arranged in primary flow passages forming a V-shape between them.

4. An aircraft according to claim 3, wherein each of the primary flow passages lies at an angle in the range 80°

to 120°

relative to a longitudinal axis of the fuselage of the aircraft.

5. An aircraft according to claim 1, wherein the working turbine and the fans are centered on a longitudinal axis of the fuselage of the aircraft.

6. An aircraft according to claim 1, wherein the fans are ducted by a nacelle fastened to a vertical empennage of the aircraft.