#B64D33/02

MULTI-ENGINE AIRCRAFT PROVIDED WITH AT LEAST ONE AIR SUPPLY DUCT EQUIPPED WITH AN AIR DEFLECTOR

The present invention relates to an aircraft (1) comprising a first turbine engine (21) and a second turbine engine (31) supplied with air respectively by a first air supply system (401) and a second …

DRIVE·Jun 10·1 min read

B64D33/02 AIRBUS HELICOPTERS [FR]

CONTROL SYSTEM FOR OPEN ROTOR PROPULSION SYSTEM WITH ONE OR MORE SENSORS

An assembly is provided for an aircraft (20). This assembly includes a propulsion system (24) and a control system (138). The propulsion system (24) includes an open propulsor rotor (60) and a turbine…

DRIVE·Jun 10·2 min read

B64D33/02 RTX CORP [US]

TAIL CONE MOUNTED GENERATOR INPUT SHAFT FOR AN AIRCRAFT

A jet engine includes a housing (12), an intake portion (14) leading into the housing, and an exhaust portion (16) leading from the housing. The exhaust portion includes an exhaust duct (23) and a tai…

DRIVE·Apr 1·2 min read

B64D33/02 HAMILTON SUNDSTRAND CORP [US]

VARIABLE GEOMETRY INLET FOR TURBOPROPELLER INLET PRESSURE RECOVERY OPTIMIZATION

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), a…

DRIVE·Feb 25·1 min read

B64D33/02 GEN ELECTRIC [US]

AIRCRAFT PROVIDED WITH A HEATING SYSTEM FOR A TURBINE ENGINE PLENUM

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 tu…

DRIVE·Feb 25·1 min read

B64D33/02 AIRBUS HELICOPTERS [FR]

SYSTEMS AND METHODS FOR CONTROLLING AN INTAKE INLET SHAPE OF A PROPULSION SYSTEM AIR INTAKE

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…

DRIVE·Dec 24·2 min read

B64D33/02 PRATT & WHITNEY CANADA [CA]

DIFFUSER FOR ROTATING DETONATION ENGINE

A diffuser (300) may comprise an inlet (310) and an outlet (340). The inlet may comprise an arcuate shape. The outlet may comprise an annular shape. The diffuser may transition from the arcuate shape …

DRIVE·Dec 24·1 min read

B64D33/02 RTX CORP [US]

SYSTEMS AND METHODS FOR CONTROLLING AN AIR FLOW PATH FOR A PROPULSION SYSTEM AIR INTAKE

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 inl…

DRIVE·Dec 24·2 min read

B64D33/02 PRATT & WHITNEY CANADA [CA]

AIRCRAFT ENGINE INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR

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 circumferen…

DRIVE·Sep 24·1 min read

B64D33/02 PRATT & WHITNEY CANADA [CA]

AIRCRAFT PROPULSION SYSTEM INLET STRUCTURE WITH VARIABLE AIRFLOW INLET AREA

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle inlet structure (58). The nacelle inlet structure (58) includes an inner inlet op…

DRIVE·Jul 16·1 min read

B64D33/02 ROHR INC [US]

AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET ASSEMBLY

An assembly (64) is provided for an aircraft propulsion system (20). This assembly (64) includes a center body (66), a scarfed inlet structure (58) and an inlet passage (68). The scarfed inlet structu…

DRIVE·Nov 27·2 min read

B64D33/02 ROHR INC [US]

AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET

An assembly (58) for an aircraft propulsion system (20) includes a variable area inlet (66) with a fixed structure (70) and a moveable structure (72). The variable area inlet (66) is configured to ope…

DRIVE·Oct 9·2 min read

B64D33/02 ROHR INC [US]

AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET

An assembly is provided for an aircraft propulsion system (20). This assembly includes a variable area inlet (66). The variable area inlet (66) includes a moveable structure (72) configured to move ax…

DRIVE·Oct 2·2 min read

B64D33/02 ROHR INC [US]

NACELLE INLET STRUCTURES, ENGINE ASSEMBLIES AND VEHICLES INCLUDING THE SAME, AND RELATED METHODS

Nacelle inlet structures, engine assemblies and vehicles including the same, and related methods. A nacelle inlet structure of an engine assembly includes an inlet outer barrel and an inlet inner barr…

DRIVE·Aug 7·1 min read

B64D33/02 BOEING CO [US]

Method of controlling a cooling system

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 seco…

DRIVE·Aug 6·2 min read

B64D33/02 ROLLS ROYCE PLC [GB]

Turboshaft engine having improved inlet particle scavenge systems and method for the manufacture thereof

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 Separato…

DRIVE·Apr 30·2 min read

B64D33/02 HONEYWELL INT INC [US]

ADJUSTABLE SUPERSONIC AIR INLET

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 en…

DRIVE·Mar 5·2 min read

B64D33/02 OTKRYTOE AKCIONERNOE OBSCHESTVO AVIACIONNAYA HOLDINGOVAYA KOMPANIYA SUHOI [RU]

Supersonic air intake system

An air intake system suitable for a supersonic vehicle is disclosed. The system includes a channel comprising an inlet and a side wall and a plenum coupled to the side wall. The plenum is configured t…

DRIVE·Nov 6·1 min read

B64D33/02 LOCKHEED CORP [US]

Gas turbine engine nacelle with sound damping means in the fan intake area

The housing (29) has a honeycomb structural layer arranged in a region of an inflow-side air inlet (11) at the housing arranged upstream of a fan (12). Sound proofing elements arranged at radially out…

DRIVE·Jul 31·1 min read

B64D33/02 ROLLS ROYCE DEUTSCHLAND [DE]

Gas turbine engine anti-icing mounting arrangements

A clamp suitable for use in an anti-icing system of a gas turbine engine is provided is disclosed. The clamp has a clasping portion for clasping a heating element. Two resilient arms extend from the c…

DRIVE·Apr 10·1 min read

B64D33/02 ROLLS ROYCE PLC [GB]

Linking device more specifically suited to providing the link between an air intake and an engine of an aircraft nacelle

The device has a first annular flange (50) connected to an air intake (42). A second annular flange (46) is connected to a motorization pipe (44) plated against the first flange. A connection element …

DRIVE·Feb 6·1 min read

B64D33/02 AIRBUS OPERATIONS SAS [FR]

Linking device more specifically suited to providing the link between an air intake and an engine of an aircraft nacelle

The nacelle has a connecting device comprising an annular flange (46) that is connected to an air inlet (42), and another annular flange (50) connected to a motor (44) that is pressed against the form…

DRIVE·Feb 6·1 min read

B64D33/02 AIRBUS OPERATIONS SAS [FR]

Linking device more specifically suited to providing the link between an air intake and an engine of an aircraft nacelle

The device has an annular flange (50) linked to an air intake, and another annular flange linked to an engine that is pressed-up against the former annular flange. A blade (66) is arranged between a f…

DRIVE·Feb 6·1 min read

B64D33/02 AIRBUS OPERATIONS SAS [FR]

Linking device more specifically suited to providing the link between an air intake and an engine of an aircraft nacelle

The nacelle has two conduits connected together by a fastening device, which comprises two annular flanges (46, 50) respectively attached to an air inlet (42) and an engine (44). A fastening element (…

DRIVE·Feb 6·1 min read

B64D33/02 AIRBUS OPERATIONS SAS [FR]

AIRCRAFT

A bird knocking-off rod of a bird knocking-off device is disposed outside a jet engine, in front of an air inlet of the jet engine and capable of rotating with a rotation area that is larger than an o…

DRIVE·Dec 19·1 min read

B64D33/02 YUUGENGAISYA OKUDO YOSETSU [JP]

Arrangement for preventing icing in the air inlet of an auxiliary power unit

An example auxiliary power unit air inlet assembly (30;30a) includes a noise attenuating component (46;46a) disposed within a conduit (34;34a). The conduit is configured to communicate a first flow of…

DRIVE·Jul 11·1 min read

B64D33/02 HAMILTON SUNDSTRAND CORP [US]

Air intake for propulsion system of an aircraft with a structure withstanding overpressure and method for repairing an air intake of an aircraft propulsion system

The intake (18) has an annular internal shell (30) including fluid passage orifices, and an annular lip (24) connected to external and internal downstream edges (28, 32) of external shroud (26) and th…

DRIVE·Jun 13·2 min read

B64D33/02 AIRBUS OPERATIONS SAS [FR]

An air intake system for an air vehicle

A missile comprises a propulsion system, a passageway (1) for delivering air to the propulsion system and a ducting element (9) associated with the passageway (1). The ducting element (9) has a ductin…

DRIVE·Jun 6·1 min read

B64D33/02 MBDA UK LTD [GB]

Aircraft nacelle including a continuous joining area between an outer wall and a front frame and fabrication method

The nacelle has a lip (114) extended inside and outside the nacelle by inner and outer walls (116, 118), respectively. A front frame (122) connects the inner wall and the outer wall that delimits an a…

DRIVE·Apr 18·1 min read

B64D33/02 AIRBUS OPERATIONS SAS [FR]

Fan nacelle with porous surfaces

A fan nacelle (34) for a gas turbine engine includes a leading edge region (40) with a flow path (42) between an intake region (48) in a nacelle outer surface (44) and an exhaust region (50) in a nace…

DRIVE·Mar 28·1 min read

B64D33/02 UNITED TECHNOLOGIES CORP [US]

Air intake of a turbine aircraft engine, aircraft equipped with such air intake and method for optimizing the operation of a turbine aircraft engine with an air intake

The inlet has a dynamic inlet duct (30) provided with a grid (40) for protection against ingesting foreign bodies. The grid is moved in translation along a dynamic axis (AX1) relative to a front flow …

DRIVE·May 18·1 min read

B64D33/02 EUROCOPTER FRANCE [FR]

Noise absorbing liner assembly for a fan case

A liner assembly (12) for a fan case (10) includes a noise attenuation layer (16) covered by a face sheet (18). The face sheet (18) includes openings (20) to the underlying noise attenuation layer (16…

DRIVE·Feb 1·2 min read

B64D33/02 UNITED TECHNOLOGIES CORP [US]

Gas turbine engine inlet with noise reduction features

A gas turbine engine comprises a fan section (12), a compressor (14), a combustor (16) and a turbine (18) and includes a nacelle (22) having an inner nacelle surface (32) defining an inlet duct (42). …

DRIVE·Dec 21·2 min read

B64D33/02 UNITED TECHNOLOGIES CORP [US]

Noise reduction assembly for flight gas turbine

The assembly has an air inlet structure with an inner wall (32) having a sound wave attenuating acoustic structure (36, 38, 40). The wall has a protrusion part (32`) extending backwards beyond a bond …

DRIVE·Nov 2·1 min read

B64D33/02 AIRBUS FRANCE [FR]

Air intake structure for an airplane engine

The structure has an annular part which defines a fan case ducting that includes inner and outer casings (16, 17). A rigidifying bar (20) has ends (24, 22) integrated to the respective casings and to …

DRIVE·Oct 5·1 min read

B64D33/02 AIRBUS FRANCE [FR]

Method and system for reduction of jet engine noise

In an aspect, a method is provided for attenuating jet engine noise. Air velocity, adjacent to an inlet fan duct outer wall (22), is increased to a greater rate than typical velocity of an operational…

DRIVE·Mar 23·1 min read

B64D33/02 GEN ELECTRIC [US]

Air intake and method for breathing air using an air intake

An air intake (10) includes a spike (11) and a cylindrical cowl (26). The spike is composed of a plurality of plates (22) which are arranged axial symmetrically around a central axis thereof, and the …

DRIVE·Jul 28·1 min read

B64D33/02 JAPAN AEROSPACE EXPLORATION [JP]

Soundproof aircraft engine nacelle

The pod has a tubular air intake (6) comprising an acoustic-attenuation internal tubular piece (10) of resonator type. A tubular transition part (17), which has an acoustically homogeneous internal fa…

DRIVE·Jun 9·1 min read

B64D33/02 AIRBUS FRANCE [FR]

Active ground vortex suppression system for an aircraft engine

Air inlet for a gas turbine engine with an active system (10) for the suppression of a ground vortex generated by the engine of an aircraft avoiding the vortex ingestion into the engine, the system in…

DRIVE·Apr 28·1 min read

B64D33/02 BOEING CO [US]

Acoustic liner for gas turbine engine

The liner system (50) includes a mode-scattering segment (48) providing a reactance between -12 and -2 rho c and a sound absorbing segment (40) providing a reactance between -1 and -0 rho c, to provid…

DRIVE·Apr 21·1 min read

B64D33/02 ROLLS ROYCE PLC [GB]