Suspension pylon for an aircraft engine fitted with a counterflow cooling exchanger
The invention relates to an aircraft pylon comprising a cooling exchanger ( 10 ) with counterflow of a flow of hot primary air ( 22 ) by a flow of cold secondary air ( 24 ) flowing oppositely to each other in a longitudinal direction (L), characterized in that it comprises two bundles ( 10 a, 10 b ) juxtaposed on both sides of a central axis ( 12 ) and each comprising a plurality of parallel longitudinal plates ( 15 ) forming a hot pass and a cold pass of the bundle, and in that one of the hot or cold passes of each bundle is supplied by a central inlet ( 14 a ) common to the two bundles ( 10 a, 10 b ) and one of the hot or cold passes of each bundle opens into a central outlet ( 16 ) common to the two bundles, said inlets ( 14 b, 14 c ) and outlets ( 16 b, 16 c ) of the conjugate passes, referred to as side inlets and outlets, being separate and diverging laterally from said central axis ( 12 ).
1 . A suspension pylon for a propulsion engine of an aircraft under a wing of an aircraft having a main axis, characterized in that it comprises:
a counterflow cooling exchanger of a flow of hot primary air by a flow of cold secondary air flowing oppositely to each other in a direction, referred to as the longitudinal direction (L), coinciding with said main axis of said engine, said exchanger comprising two plate exchanger blocks, referred to as bundles, juxtaposed one beside the other on both sides of a central juxtaposition axis extending in said longitudinal direction (L), and each comprising:
a plurality of parallel longitudinal plates forming in alternation flow ducts for the flow of hot primary air, which define a hot pass of the bundle, and flow ducts for the flow of cold secondary air, which define a cold pass of the bundle,
a single hot air inlet and a single hot air outlet arranged respectively at each longitudinal end of said bundle,
a single cold air inlet and a single cold air outlet arranged respectively at each longitudinal end of said bundle, said hot passes of the two bundles being in fluid communication with a central inlet common to the two bundles forming said single hot air inlets of the two bundles and a central outlet common to the two bundles forming said single hot air outlets of said bundles, and said cold passes of the two bundles being in fluid communication with separate side inlets and side outlets which diverge laterally from said central axis, said separate side inlets being supplied by fresh ambient air drawn from the proximity of said pylon,
conduits for distribution of hot air suitable for fluidly connecting a device for drawing air from said aircraft engine and said central inlet common to the two bundles.
2 . The pylon as claimed in claim 1 , wherein said cold and/or hot passes of the two bundles of said exchanger are separated by a central closure bar.
3 . The pylon as claimed in claim 1 wherein each bundle of said exchanger is housed in a housing comprising, at each longitudinal end, an end wall formed from two openwork planes inclined with respect to the longitudinal direction (L) and connected by a joint edge which extends perpendicularly to said longitudinal direction (L), each inclined openwork plane forming a side inlet or a side outlet of one of the passes of said bundle, and each pair of inclined openwork planes of the two bundles arranged facing each other forming an inlet common to said bundles and/or an outlet common to said bundles.