US 11,772,810 B2
Aircraft nacelle comprising at least one heat exchanger
Vincent Peyron, Moissy Cramayel (FR); and Jean-Nicolas Bouchout, Moissy Cramayel (FR)
Assigned to Safran Nacelles, Gonfreville l'Orcher (FR)
Filed by Safran Nacelles, Gonfreville l'Orcher (FR)
Filed on Apr. 3, 2020, as Appl. No. 16/839,145.
Claims priority of application No. 1903542 (FR), filed on Apr. 3, 2019.
Prior Publication US 2020/0317358 A1, Oct. 8, 2020
Int. Cl. B64D 33/10 (2006.01); B64D 27/18 (2006.01); B64D 29/02 (2006.01); B64D 33/02 (2006.01); F02C 7/16 (2006.01); F28D 9/00 (2006.01); F28D 21/00 (2006.01)
CPC B64D 33/10 (2013.01) [B64D 27/18 (2013.01); B64D 29/02 (2013.01); B64D 33/02 (2013.01); F02C 7/16 (2013.01); F28D 9/00 (2013.01); F05D 2260/213 (2013.01); F28D 2021/0021 (2013.01)] 15 Claims
OG exemplary drawing
 
1. An aircraft comprising a fuselage disposed in a longitudinal plane of the aircraft, at least two propulsion units disposed in a plane transverse to the longitudinal plane of the aircraft on either side of the fuselage, and a nacelle of at least one of the at least two propulsion units, the nacelle suspended from a mast and defining a centerline axis and a circumferential direction about the centerline axis, wherein the centerline axis extends within each of a vertical plane and a lateral plane perpendicular to the vertical plane, the vertical plane bisecting the mast at an upper circumferential position of the nacelle, the nacelle comprising:
four dials defined respectively between an upper point circumferentially aligned with the upper circumferential position of the nacelle and located in the vertical plane, a lower point diametrically opposed from the upper point and located in the vertical plane, a proximal lateral point relative to the longitudinal plane, the proximal lateral point located in the lateral plane, and a distal lateral point relative to the longitudinal plane, the distal lateral point diametrically opposed from the proximal lateral point and located in the lateral plane, the four dials including a proximal upper dial, a distal upper dial, a proximal lower dial, and a distal lower dial;
an upstream section comprising a leading edge forming an air inlet lip;
a middle section;
a downstream section comprising a trailing edge;
at least one surface heat exchanger including a cold source exchanger between a heat transfer fluid and a cold air flow, the cold source exchanger being integrated into a closed circuit in which the heat transfer fluid circulates, and the entirety of the cold source exchanger being disposed in at least one of the proximal upper dial, the distal upper dial and the distal lower dial such that the cold source exchanger is circumferentially spaced from each of the vertical plane and the lateral plane, the cold source exchanger further positioned in at least one of the middle section and the downstream section; and
an outer structure comprising an outer fairing defining an outer aerodynamic surface, and an inner fairing defining an inner aerodynamic surface, the inner and outer fairings being connected upstream by the leading edge forming the air inlet lip, and the cold source exchanger being in contact with at least one of the inner fairing and the outer fairing of the nacelle,
wherein an outer surface of the cold source exchanger is formed at least partially by a double wall of at least one of the inner fairing and the outer fairing of the nacelle.