About 39 results
https://drivepatents.com/patents/1386298 · 25 Feb 2026
Aircraft (1) fitted with a turbine engine (10) comprising a gas generator (15), the gas generator (15) comprising a compression assembly (20) supplying air to a combustion chamber (24) as well as a turbine assembly (25) supplied with gas by the combustion ...
https://drivepatents.com/patents/1391164 · 25 Feb 2026
A turboprop engine (110) includes a main nacelle body (212), a rotatable hub (220) provided on the main nacelle body (212), a plurality of propellers (215, 520) connected to the rotatable hub (220), and a nacelle extension (214) coupled to the main nacelle...
https://drivepatents.com/patents/1391153 · 25 Feb 2026
An air inlet (40) for an aircraft propulsion system nacelle (24) includes an outer skin (44), an inner skin (46), a lip skin (48), and a forward bulkhead (50). The lip skin (48) extends between and to an outer end (62) and an inner end (64). The outer end ...
https://drivepatents.com/patents/1392612 · 24 Dec 2025
An air intake (36) for an aircraft propulsion system (10) includes an air inlet duct (54) and a flow control device (120). The air inlet duct (54) includes an interior surface (52) and an intake inlet (60). The interior surface (52) extends from the intake...
https://drivepatents.com/patents/1392628 · 24 Dec 2025
An air intake (36) for an aircraft propulsion system (10) includes an air inlet duct (54), a core flow duct (56), a bypass flow duct (58), a splitter (60), and a flow control device (114). The air inlet duct (54) includes an intake inlet (64) and a gas pat...
https://drivepatents.com/patents/1394142 · 24 Sep 2025
An aircraft engine (10), has: an inlet (12) leading to a compressor section (13), the inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) extending circumferentially around the central axis (A), the annular inlet du...
https://drivepatents.com/patents/1399817 · 7 Aug 2024
- Peau poreuse pourvue d'une pluralité de bandes et panneau d'atténuation acoustique comprenant une telle peau poreuse. - La peau poreuse (1) comporte une pluralité de bandes (2) qui sont agencées transversalement à un écoulement de fluide (E) et qui...
https://drivepatents.com/patents/971557 · 6 Aug 2014
A method of controlling an aircraft gas turbine engine cooling system (20). The cooling system comprises a heat exchanger (22) having a first fluid path (24) through which fan air can flow, and a second fluid path (26) through which relatively hot compress...
https://drivepatents.com/patents/975473 · 30 Apr 2014
Embodiments of a turboshaft engine (40) are provided, as are embodiments of a method for manufacturing a turboshaft engine. In one embodiment, the turboshaft engine includes an Inlet Particle Separator (IPS) system (42) having an IPS scavenge flow circuit ...
https://drivepatents.com/patents/977846 · 5 Mar 2014
The invention relates to aeronautical engineering and, more specifically, to air intakes for supersonic aircraft propulsion systems. The technical result to be achieved by the invention consists in ensuring stable operation of the engine in all flight regi...