Aircraft propulsion system assembly, including an enhanced performance heat exchanger

Abstract

The invention relates to an assembly (15) for an aircraft propulsion system, comprising: - a radial boundary structure (34) for the circulation of a gas flow (12b), having a radial boundary surface (34a); - a heat exchanger (45a) projecting from the radial boundary surface (34a), configured to be traversed by a first portion (12b1) of the gas flow, the exchanger also comprising a cowling (50), an upstream inlet (52) and a downstream outlet (54). The cowling (50) comprises: - an intermediate inlet (52a) intended to be traversed by a sample (P1) from the second portion (12b2) of the gas flow; - an intermediate outlet (54a) intended to be traversed by a primary portion (12b1a) of the first part (12b1), the sample (P1) and a secondary portion (12b1b) of the first part (12b1) being extracted by the outlet (54). Figure 3

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