Cross-flow tubular heat exchanger for aircraft turbomachinery
The cross-flow tubular heat exchanger with a parallelepiped distributor and perforated plate addresses integration and assembly complexities, enhancing thermomechanical resistance and reducing stress concentrations through brazing.
FR3169988A1Pending Publication Date: 2026-06-19SAFRAN SA
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Applications
- Current Assignee / Owner
- SAFRAN SA
- Filing Date
- 2024-12-12
- Publication Date
- 2026-06-19
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Abstract
The invention relates to a cross-flow tubular heat exchanger for an aircraft turbomachine, comprising a distributor (303) having a substantially parallelepiped shape, and having an inlet (311) connected to a first chamber (313) and an outlet (315) connected to a second chamber (317), a reversing zone comprising a third chamber and first tubes connected to the first chamber (313) on one side and to the third chamber on the other, and second tubes connected to the third chamber on the one hand and to the second chamber on the other. The first chamber (313) and the second chamber (317) are closed on one side by a perforated plate whose holes open into the first and second tubes.Columns (331) extend longitudinally, in the first and second chambers (313, 317), from the inner face of the perforated plate to an inner wall of the distributor (303) located opposite the inner face of the perforated plate. Figure for the abbreviation: Fig. 7.
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