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FR-3168235-A1 - Blade for an aircraft turbomachine

FR3168235A1FR 3168235 A1FR3168235 A1FR 3168235A1FR-3168235-A1

Abstract

Blade for an aircraft turbomachine comprising: a platform (10) having a duct surface (15), a blade (9, 22, 25) having a leading edge (11, 27, 28), a trailing edge (12, 29, 30), an intrados (13) and an extrados (14), the extrados (14) and the intrados (13) connecting the leading edge (11, 27, 28) and the trailing edge (12, 29, 30), a flow channel (18) extending into the platform (10) and having a suction inlet (19) which is configured to draw in an airflow downstream of the leading edge (11, 27, 28), the suction inlet (19) having an edge (23) which runs along the extrados (14) of the blade (9, 22, 25) from the leading edge (11, 27, 28), said channel (18) having an ejection outlet (21) configured to eject the airflow downstream of the trailing edge (12, 29, 30). Fig. 3.

Inventors

  • Nicolas ZELLER
  • Simon PARINET
  • Ludovic Pintat
  • Franck Davy BOISNAULT

Assignees

  • SAFRAN AIRCRAFT ENGINES

Dates

Publication Date
20260508
Application Date
20241105