IP Library › Granted Patent US 10,739,086
Granted Patent B2
US 10,739,086 · App. 15/521,864 · Granted Aug 11, 2020

Heat exchanger and turbine engine comprising such an exchanger

Inventors: Gilles Yves Aouizerate (Moissy-Cramayel, FR); Benjamin Boudsocq (Moissy-Cramayel, FR); Gerard Philippe Gauthier (Moissy-Cramayel, FR)
Assignee: SAFRAN AIRCRAFT ENGINES
F28F13/00F28F27/00F28D2021/0021F28F2215/14F28F2255/02
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Quick Facts
Patent No.
US 10,739,086
App. No.
15/521,864
Granted
Aug 11, 2020
Kind
B2
Abstract

The invention relates to a heat exchanger ( 10 ) for heat-exchange between a first fluid and a second fluid, comprising a membrane separating the two fluids and a heat-conductive element ( 17 ) in thermal contact with the membrane and with the first fluid, characterised in that said heat-conductive element ( 17 ) moves between an active position and an inactive position, such that the capacity of heat exchange with the first fluid is weaker in the inactive position than in the active position. The exchanger is applied, in particular, for the cooling of fluid in the secondary stream of a turbofan.

Claims (7)

1. A heat exchanger for heat exchange between a first fluid and a second fluid, comprising a membrane separating the two fluids and a heat-conductive element in thermal contact with both the membrane and the first fluid, said heat-conductive element being movable between an active position and an inactive position such that the capacity of heat exchange with the first fluid is less in the inactive position than in the active position, wherein the heat-conductive element is in the form of a blade, the blade being rigidly connected to the membrane by a connecting edge, wherein said element is prestressed in the active position and the transition from the active position to the inactive position is achieved by deforming the membrane along the connecting edge connecting the blade to the membrane, the deformation of the membrane being achieved by applying a force that is parallel to the plane of the membrane, and comprising a piston by means of which the force is applied to the membrane.

2. The heat exchanger according to claim 1 , wherein in the active position, the blade is moved away from the membrane so as to be in contact with the first fluid by the two faces thereof.

3. The heat exchanger according to claim 2 , wherein in the inactive position the blade is arranged by one face close to the membrane.

4. The heat exchanger according to claim 2 , wherein in the active position the blade has a curved shape which moves away from the membrane at the connecting edge.

5. The heat exchanger according to claim 4 , wherein the connecting edge is rectilinear and the blade is curved around the connecting edge in the active position.

6. The heat exchanger according to claim 1 , wherein the deformation of the membrane is achieved by applying a compressive force.

7. A turboshaft engine comprising a heat exchanger according to claim 1 .

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded May 1, 2017
From: AOUIZERATE, GILLES YVES; BOUDSOCQ, BENJAMIN; GAUTHIER, GERARD PHILIPPE
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 042198/0324 →
Priority Claims (1)
FR 14 60461 · Oct 30, 2014 · national
Continuity (1)
Related Publication 20170321972A1 · Nov 9, 2017
Cited By (5)
US 12,203,415 US 12,221,927 US 12,326,092 US 12,553,383 US 12,704,332