#B64D15/04

SHIELDED SWIRL GAS TURBINE ENGINE INLET ANTI-ICING SYSTEM

A gas turbine engine inlet anti-ice system includes a nacelle having an inlet lip, an anti-ice air supply duct, and a flow deflector. The inlet lip has an annular anti-icing chamber formed therein tha…

DRIVE·May 27·2 min read

B64D15/04 HONEYWELL INT INC [US]

AIRCRAFT ENGINE NACELLE AIR INTAKE LIP PROVIDED WITH A DEVICE FOR PASSIVELY SEALING AN EXHAUST DEVICE

Air inlet lip (12) of an aircraft engine nacelle equipped with a passive closure device for a communication orifice The subject of the invention is an air inlet lip (12) of a nacelle (10) of an aircra…

DRIVE·Apr 29·1 min read

B64D15/04 AIRBUS OPERATIONS SAS [FR]

LEAK DETECTION SYSTEM FOR ANTI-ICE DUCTS

An inlet cowl (200) may comprise: a forward bulkhead; an aft bulkhead (138) spaced apart axially aft of the forward bulkhead; an annular structure having a radially inner wall (152) spaced apart from …

DRIVE·Jul 9·1 min read

B64D15/04 ROHR INC [US]

PRESSURE REGULATING VALVE ASSEMBLY

Pressure regulating valve assembly (5) comprising: a valve (50) having an upstream side (51) receiving an input flow (I) and a downstream side (52) providing an output flow (O), actuating means (60) f…

DRIVE·Jan 31·2 min read

B64D15/04 ROLLS ROYCE DEUTSCHLAND LTD & CO KG [DE]

VARIABLE DIAMETER PICCOLO TUBE FOR ANTI-ICING SYSTEM

A piccolo tube (152) for an anti-icing system may comprise an annular tube (156) and a plurality of openings (154) formed along a circumference of the annular tube. The annular tube may comprise a fir…

DRIVE·Sep 6·1 min read

B64D15/04 ROHR INC [US]

NOZZLE FOR A THERMAL ANTI-ICING SYSTEM

An assembly (48) is provided for an aircraft propulsion system (20). The assembly (48) includes a nacelle inlet structure (32) with an internal cavity (82). The assembly (48) also includes a nozzle (8…

DRIVE·Aug 30·1 min read

B64D15/04 ROHR INC [US]

THERMAL ANTI-ICING SYSTEM WITH NON-CIRCULAR PICCOLO TUBE

A system is provided for an aircraft propulsion system (10). This system includes an inlet lip (42), a bulkhead (46) and a piccolo tube (48) for a thermal anti-icing system (38). The inlet lip (42) ex…

DRIVE·May 31·1 min read

B64D15/04 ROHR INC [US]

Acoustic treatment panel including hot-air channels and at least one stabilising chamber

The nacelle has a lip (34) that is prolonged by an interior pipe (36) forming an air intake part. A front frame (32) delimits the lip, and an annular pipe (40) is utilized for circulation of hot air. …

DRIVE·Apr 10·1 min read

B64D15/04 AIRBUS OPERATIONS SAS [FR]

Acoustic treatment panel including hot-air channels and at least one annular channel

The nacelle has a lip (34) prolonged by an interior pipe (36) forming an air intake. A front frame (32) delimits an annular pipe (40) in which hot air circulates and an acoustic treatment panel with t…

DRIVE·Apr 10·1 min read

B64D15/04 AIRBUS OPERATIONS SAS [FR]

Aircraft nacelle comprising a device for supplying hot air to a panel combining acoustic and ice treatments

The nacelle has a lip prolonged by an interior pipe forming an air intake. A front frame delimits an annular duct (40) in which hot air circulates, and a panel treats sound from an outer side toward a…

DRIVE·Apr 10·1 min read

B64D15/04 AIRBUS OPERATIONS SAS [FR]

Method for producing an acoustic treatment panel including the function of de-icing with hot air

The method involves deforming a layer i.e. sheet metal made of titanium alloy so as to produce furrows at one of surfaces of the layer. The deformed layer is flattened and integrated with an acoustica…

DRIVE·Dec 26·1 min read

B64D15/04 AIRBUS OPERATIONS SAS [FR]

De-icing device for an aviation gas turbine engine

The device has an annular tubular element (31) extended along a circumferential direction. The tubular element comprises outflow openings for supplying hot air to a ring lip region (29) of a double-wa…

DRIVE·Nov 28·1 min read

B64D15/04 ROLLS ROYCE DEUTSCHLAND [DE]

Jet engine air intake fairing with de-icing device

There is presented an air inlet cowl for a jet engine provided with de-icing means comprising an air extraction opening (34) made in the partition (20), to put into communication the insulation volume…

DRIVE·Oct 23·1 min read

B64D15/04 AIRBUS FRANCE [FR]

Deicing method with forced circulation for jet engine intake fairing and device for the implementation of said method

The jet engine air intake cowling comprises an air intake lip (6a), a de-icing system (10) and acoustic attenuation means (11). The acoustic attenuation means are constituted by separate islets (11a) …

DRIVE·Aug 21·1 min read

B64D15/04 AIRBUS FRANCE SAS [FR]

Hot air exhaust device for a jet engine air intake fairing with de-icing circuit

The air intake cowling (9) for a jet engine, whose leading edge (16) is hollow and traversed by a hot air flow for de-icing (17), comprises outlets for the hot air flow to the outside of said leading …

DRIVE·Jun 27·1 min read

B64D15/04 AEROSPATIALE MATRA AIRBUS [FR]

Method and apparatus for aircraft inlet ice protection

An inlet ice protection system (60), and methods for making and using ice protection systems. The inlet (50) includes an acoustic liner (70a,70b) having a perforated face sheet (71a,71b), a perforated…

DRIVE·May 30·1 min read

B64D15/04 BOEING CO [US]