Invention Grant
- Patent Title: Turbomachine blade having a sweep law with high flutter margin
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Application No.: US17312212Application Date: 2019-12-10
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Publication No.: US11753943B2Publication Date: 2023-09-12
- Inventor: Guillaume Pascal Jean-Charles Gondre , Nicolas Pierre Alain Edme De Cacqueray-Valmenier , Mickaël Cavarec , Sadim Dieudonne
- Applicant: SAFRAN AIRCRAFT ENGINES
- Applicant Address: FR Paris
- Assignee: SAFRAN AIRCRAFT ENGINES
- Current Assignee: SAFRAN AIRCRAFT ENGINES
- Current Assignee Address: FR Paris
- Agency: Sughrue Mion, PLLC
- Priority: FR 72700 2018.12.11
- International Application: PCT/FR2019/053004 2019.12.10
- International Announcement: WO2020/120897A 2020.06.18
- Date entered country: 2021-06-09
- Main IPC: F01D5/16
- IPC: F01D5/16

Abstract:
A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.
Public/Granted literature
- US20220018259A1 TURBOMACHINE BLADE HAVING A SWEEP LAW WITH HIGH FLUTTER MARGIN Public/Granted day:2022-01-20
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