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EP-4276019-B1 - SYSTEMS AND METHODS FOR AIRCRAFT WING PLUG

EP4276019B1EP 4276019 B1EP4276019 B1EP 4276019B1EP-4276019-B1

Inventors

  • BERTRAND, PIERRE
  • THOMASSIN, JEAN

Dates

Publication Date
20260506
Application Date
20210518

Claims (10)

  1. An aircraft (10'), comprising: a fuselage (12); at least one wing (14; 16) extending from the fuselage (12), wherein the wing (14; 16) includes first and second original portions (102; 104) and a plug portion (106) positioned between the first and second original portions (102; 104); and a propulsion system (108) positioned on the at least one wing (14; 16), characterised in that : the propulsion system (108) includes at least one electric powerplant (110) and at least one combustion powerplant (112), each powerplant delivers power to a respective air mover (114) for propelling the aircraft (10'), and the at least one electric powerplant (110) or the at least one combustion powerplant (112) is positioned outboard from and on the plug portion (106).
  2. The aircraft (10') as recited in claim 1, wherein the plug portion (106) has a leading edge (150) and a trailing edge (152), and the leading and trailing edges (150; 152) are parallel to one another to match a width of the first original portion (102).
  3. The aircraft (10') as recited in claim 1 or 2, wherein the electric powerplant (110) is positioned outboard from and on the plug portion (106).
  4. The aircraft (10') as recited in claim 1, 2 or 3, wherein the combustion powerplant (112) includes a heat engine (109), wherein the heat engine (109) is a gas turbine, a rotary engine or a reciprocating engine of any fuel type with a configuration of turbomachiney elements, selected from the group consisting of a turbocharger, turbosupercharger or supercharger and exhaust recovery turbo compounding, that is mechanically, electrically, hydraulically or pneumatically driven.
  5. The aircraft (10') as recited in any preceding claim, further comprising an outer nacelle (124) positioned at an abutment of the second original portion (104) and the plug portion (106), wherein the outer nacelle (124) houses an electric motor (107) of the electric powerplant (110).
  6. The aircraft (10') of any preceding claim, wherein the combustion powerplant (112) is positioned inboard from the plug portion (106).
  7. The aircraft (10') of any preceding claim, further comprising an inner nacelle (122) positioned at an abutment of the first original portion (102) and the plug portion (106), wherein the inner nacelle (122) houses the combustion powerplant (112).
  8. The aircraft (10') of claim 7, wherein the inner nacelle (122) houses the heat engine (109) of the combustion powerplant (112).
  9. The aircraft (10') of any preceding claim, wherein a length (Ls) of the plug portion (106) is greater than a combined length of a first propeller blade (120) operatively connected to the air mover (114) of the electric powerplant (110) and a second propeller blade (118) operatively connected to the air mover (114) of the combustion powerplant (112).
  10. The aircraft (10') of any preceding claim, further comprising batteries (126) positioned outboard of the plug portion (106).

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The subject invention is directed to propulsion configurations in aircraft, and more particularly to propulsion configurations for an aircraft having mixed drive systems, including hybrid-electric propulsion systems. 2. Description of Related Art The level of air traffic continues to increase worldwide, leading to increased fuel consumption and air pollution. Consequently, efforts are underway to make aircraft more environmentally compatible through the use of specific types of fuel and/or by reducing fuel consumption through the use of more efficient drive systems. For example, aircraft having mixed drive systems that include a combination of various types of engines are known for reducing pollutants and increasing efficiency. Some current combinations include reciprocating engines and j et engines, reciprocating engines and rocket engines, jet engines and rocket engines, or turbojet engines and ramjet engines. While these mixed drive systems are useful, they are not readily adaptable for use on commercial passenger aircraft. However, hybrid-electric propulsion systems that provide power through a combustion engine and an electric motor are indeed adaptable for use with commercial passenger aircraft and can provide efficiency benefits including reduced fuel consumption. The subject invention is directed to aircraft having such propulsion systems. Prior art aircrafts are disclosed in US6726149, EP2581308, EP3620386, US2016/0355272, US8660712, CN210162240 and US20080149758. SUMMARY OF THE DISCLOSURE In accordance with the present invention, an aircraft is provided as claimed in claim 1. In some embodiments, the electric powerplant is positioned outboard from and on the plug portion. The combustion powerplant can be positioned inboard from the plug portion. A length of the plug portion can be greater than a combined length of a first propeller blade operatively connected to the air mover of the electric powerplant and a second propeller blade operatively connected to the air mover of the combustion powerplant. The combustion powerplant can include a heat engine. The heat engine can be a gas turbine, a rotary engine or a reciprocating engine of any fuel type with a configuration of turbomachiney elements, selected from the group consisting of a turbocharger, turbosupercharger or supercharger and exhaust recovery turbo compounding, that is mechanically, electrically, hydraulically or pneumatically driven. An inner nacelle can be positioned at an abutment of the first portion (or 'original' portion) and the plug portion. The inner nacelle can house a heat engine of the combustion powerplant. An outer nacelle can be positioned at an abutment of the second portion (or 'original' portion) and the plug portion. The outer nacelle can house the electric motor of the electric powerplant. Batteries can be positioned out board of the plug portion. These and other features of the systems and methods of the subject disclosure will become more readily apparent to those skilled in the art from the following detailed description of the preferred embodiments taken in conjunction with the drawings. BRIEF DESCRIPTION OF THE DRAWINGS So that those having ordinary skill in the art will readily understand how to make and use the subject invention without undue experimentation, preferred embodiments thereof will be described in detail herein below with reference to the figures wherein: Fig. 1 is a schematic top plan view of a traditional commercial passenger aircraft;Fig. 2 is a schematic top plan view of a commercial passenger aircraft constructed in accordance with an embodiment of the present disclosure, showing each wing having a plug portion;Fig. 3 is a schematic top plan view of a portion of one of the wings of the commercial passenger aircraft of Fig. 1, showing the length of the plug portion;Fig. 4 is a schematic top plan view of the plug portion of the commercial passenger aircraft of Fig. 1, showing the outer nacelle operatively connected thereto; andFig. 5 is a schematic top plan view of a commercial passenger aircraft constructed in accordance with another embodiment of the present disclosure, showing each wing having a plug portion. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an embodiment of a system in accordance with the disclosure is shown in Fig. 2. Other embodiments of systems in accordance with the disclosure, or aspects thereof, are provided in Figs. 3-5, as will be described. The systems and methods described herein can be used to provide aircraft with increased fuel efficiency. In traditional aircraft, for example the Dash 8 - Q400, the wingspan is sized to accommodate faster take-off, climb and cruise speeds. One compone