Propulsion assembly for an aircraft, comprising a gas generator and two offset fans
US-10518890-B2 · Dec 31, 2019 · US
Aircraft with multiple fan propulsion assembly fixed under the wing
US2018281978A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2018281978-A1 |
| Application number | US-201615765469-A |
| Country | US |
| Kind code | A1 |
| Filing date | Sep 29, 2016 |
| Priority date | Oct 5, 2015 |
| Publication date | Oct 4, 2018 |
| Grant date | — |
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Abstract
Official abstract text for this publication.
The present invention relates to an aircraft comprising a fuselage, a lateral support wing ( 1 ) and propulsion assembly ( 100 ) mounted under the wing, the wing comprising at least two structural spars ( 11 ba, 11 bf ) extending from the fuselage toward the tip of the wing, one of these ( 11 ba ) being upstream and the other ( 11 bf ) downstream, and the propulsion assembly comprising a gas generator ( 106 ) and at least two offset fans ( 102, 104 ) arranged on either side of the axis of the gas generator. The aircraft is characterized in that the offset fans ( 102, 104 ) are attached directly to one of the said spars ( 11 ba, 11 bf ) and the gas generator ( 106 ) is attached directly to the two spars. In particular, with the leading edge of the wing forming a given sweep of angle (α) with the axis of the fuselage, the two offset fans ( 102, 104 ) are axially offset from one another.
First claim
Opening claim text (preview).
1 . Aircraft comprising a fuselage, a lateral lifting wing and a powerplant mounted under the wing, the wing comprising at least two structural spars extending from the fuselage towards the tip of the wing, one being upstream and the other downstream, with the powerplant comprising a gas generator and at least two offset fans arranged on either side of the axis of the gas generator, characterized in that the offset fans are attached directly to one of said spars and the gas generator is attached directly to both spars. 2 . Aircraft according to claim 1 , wherein the offset fans are attached to the upstream spar. 3 . Aircraft according to claim 2 , wherein each fan comprises a housing supported by the upstream spar via a suspension device that connects the housing to said upstream spar directly. 4 . Aircraft according to claim 1 , wherein the leading edge of the wing forms a sweepback of a given angle (α) with the axis of the fuselage, the two offset fans being displaced axially relative to one another. 5 . Aircraft according to claim 4 , wherein the air intakes of the two offset fans are under and close to the leading edge of the wing. 6 . Aircraft according to claim 1 , wherein the axis of the gas generator is located at a higher level than the axes of the two offset fans. 7 . Aircraft according to claim 6 , wherein the gas generator is integral with the wing, an outer envelope of the gas generator being formed at least partly by a part of the wall forming the lower surface and/or the upper surface of the wing. 8 . Aircraft according to claim 7 , wherein at least part of the envelope of at least one of the fans is formed by a part of the wall forming the lower surface and/or the upper surface of the wing. 9 . Aircraft according to claim 1 , wherein the gas generator comprises a gas ejection nozzle, the axis of the ejected gas stream forming an angle (β) between 5 and 25° downwards with the horizontal plane. 10 . Aircraft according to claim 1 , wherein the gas generator comprises a gas ejection channel directing the gas flow along the upper surface of the wing.
Assignees
Inventors
Classifications
Operations & Transport · mapped topic
the plant being of the multiple flow type, i.e. having three or more flows · CPC title
Air intakes for gas-turbine plants or jet-propulsion plants · CPC title
Operations & Transport · mapped topic
Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title
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- What does patent US2018281978A1 cover?
- The present invention relates to an aircraft comprising a fuselage, a lateral support wing ( 1 ) and propulsion assembly ( 100 ) mounted under the wing, the wing comprising at least two structural spars ( 11 ba, 11 bf ) extending from the fuselage toward the tip of the wing, one of these ( 11 ba ) being upstream and the other ( 11 bf ) downstream, and the propulsion assembly comprisi…
- Who is the assignee on this patent?
- Safran Aircraft Engines
- What technology area does this patent fall under?
- Primary CPC classification B64D27/12. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Thu Oct 04 2018 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 6 related publications on this page (citations in our corpus or others sharing the same primary CPC).