Invention Grant
- Patent Title: Impact-cooling tubular insert for a turbomachine distributor
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Application No.: US17429474Application Date: 2020-03-16
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Publication No.: US11434769B2Publication Date: 2022-09-06
- Inventor: Guillaume Klein , Matthieu Jean Luc Vollebregt , Thomas Joseph Lardellier , Guillaume Carrerot , Stephane Lavignotte
- Applicant: SAFRAN AIRCRAFT EGINES , SAFRAN HELICOPTER ENGINES
- Applicant Address: FR Paris; FR Bordes
- Assignee: SAFRAN AIRCRAFT EGINES,SAFRAN HELICOPTER ENGINES
- Current Assignee: SAFRAN AIRCRAFT EGINES,SAFRAN HELICOPTER ENGINES
- Current Assignee Address: FR Paris; FR Bordes
- Agency: Womble Bond Dickinson (US) LLP
- Priority: FR1902874 20190320
- International Application: PCT/FR2020/050548 WO 20200316
- International Announcement: WO2020/188212 WO 20200924
- Main IPC: F01D5/18
- IPC: F01D5/18 ; F01D5/14 ; B33Y80/00

Abstract:
A tubular ventilation sleeve for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and including a perforated tubular wall around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall, wherein it further includes support beams when the sleeve is made by additive manufacturing, the beams extending inside the sleeve between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall and the bottom wall and the last side of which is free and extends inside the sleeve, perforations in the tubular wall being provided between the support beams.
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