Antoine Jean-Philippe Beaujard
28Patents
5h-index
40Co-inventors
65Inventor score
Filing activity: Aug 8, 2011 → Feb 20, 2023
Most-cited inventions
| Patent | Title | Area | Cited by | Status |
|---|---|---|---|---|
| US9045992B2 | Turbomachine blades or vanes having complementary even/odd geometry | Emerging Cross-Sectional Technologies | 17 | Active |
| US9062562B2 | Composite material turbomachine engine blade or vane, compressor stator segment or turbine nozzle segment incorporating such vanes and method for manufacturing same | Emerging Cross-Sectional Technologies | 14 | Active |
| US9033673B2 | Turbomachine blade or vane having complementary asymmetrical geometry | Emerging Cross-Sectional Technologies | 13 | Active |
| US9506355B2 | Turbine engine blade or vane made of composite material, turbine nozzle or compressor stator incorporating such vanes and method of fabricating same | Emerging Cross-Sectional Technologies | 7 | Active |
| US9708918B2 | Hollow-blade turbine vane made from composite material, turbine or compressor including a nozzle or guide vane assembly formed by such blades, and turbomachine comprising same | Emerging Cross-Sectional Technologies | 7 | Active |
| US9822655B2 | Assembly formed by a turbine nozzle or a compressor diffuser made of CMC for a turbine engine and by an abradable material support ring, and a turbine or a compressor incorporating such an assembly | Emerging Cross-Sectional Technologies | 5 | Active |
| US9784113B2 | Method of fabricating a turbine or compressor guide vane sector made of composite material for a turbine engine, and a turbine or a compressor incorporating such guide vane sectors | Emerging Cross-Sectional Technologies | 5 | Active |
| US9103219B2 | CMC turbine nozzle adapted to support a metallic turbine internal casing by an axial contact | Emerging Cross-Sectional Technologies | 3 | Active |
| US10072508B2 | Turbomachine rotor with optimised bearing surfaces | Emerging Cross-Sectional Technologies | 3 | Active |
| US10773813B2 | Aircraft with a propulsion unit comprising a fan at the rear of the fuselage | Emerging Cross-Sectional Technologies | 2 | Active |
| US9518472B2 | Turbine engine stator wheel and a turbine or a compressor including such a stator wheel | Emerging Cross-Sectional Technologies | 2 | Active |
| US11261754B2 | Shell for reducing overpressure in the vicinity of the upstream seal of a turbojet bearing housing | Mechanical Engineering; Lighting; Heating | 2 | Active |
| US9834312B2 | Method for holding an adapter piece on a tubular housing of a turbo engine, and corresponding adapter piece and holding system | Emerging Cross-Sectional Technologies | 2 | Active |
| US10351252B2 | Aircraft comprising a propulsion assembly including a pair of propellers at the rear of the fuselage | Mechanical Engineering; Lighting; Heating | 1 | Active |
| US9784122B2 | Method of fabricating a composite material casing for a gas turbine engine, and a casing obtained thereby | Emerging Cross-Sectional Technologies | 1 | Active |
| US9429030B2 | Device for locking a root of a rotor blade | Mechanical Engineering; Lighting; Heating | 1 | Active |
| US9194241B2 | CMC turbine nozzle adapted to support a metallic turbine internal casing by a radial contact | Emerging Cross-Sectional Technologies | 1 | Active |
| US9638042B2 | Turbine engine comprising a metal protection for a composite part | Emerging Cross-Sectional Technologies | 1 | Active |
| US12025018B2 | Turbine arrangement incorporating an oil recovery circumferential trough | Mechanical Engineering; Lighting; Heating | 0 | Active |
| US10450884B2 | Impeller having a radial seal for a turbine engine turbine | Emerging Cross-Sectional Technologies | 0 | Active |
| US10138737B2 | Rotor for turbine engine comprising blades with added platforms | Emerging Cross-Sectional Technologies | 0 | Active |
| US11136937B2 | Aircraft propulsion assembly comprising a thrust reverser | Mechanical Engineering; Lighting; Heating | 0 | Active |
| US11371432B2 | Aircraft engine intake arrangement comprising a mechanical decoupler | Mechanical Engineering; Lighting; Heating | 0 | Active |
| US11377978B2 | Device for evacuation of a ventilated lubricated chamber of a turbomachine | Mechanical Engineering; Lighting; Heating | 0 | Active |
| US11499439B2 | Double flow turbojet including an intermediate flow path dedicated to supplying with air via radial arms an exhaust casing of this turbojet | Mechanical Engineering; Lighting; Heating | 0 | Active |
Source: USPTO / EPO open patent data. Inventor disambiguation is heuristic; counts are objective bibliographic measures.