#RTX CORP [US]

AIRCRAFT POWERPLANT GEARBOX WITH SELECTABLE POWER COUPLER

An aircraft powerplant (20) assembly includes a gearbox (88) having a first power transfer apparatus (120) and a second power transfer apparatus (122) independent of the first power transfer apparatus…

DRIVE·4d ago·2 min read

F02C3/107 RTX CORP [US]

AIRCRAFT HEAT EXCHANGE SYSTEM WITH MULTIPLE HEAT EXCHANGERS

A vane structure (140) includes a structure passage (142) that extends internally from a passage inlet (160) to a passage outlet (162). The passage inlet (160) fluidly couples the structure passage (1…

DRIVE·4d ago·2 min read

F02C7/14 RTX CORP [US]

BURNER PRESSURE SYNTHESIS FROM FUEL SYSTEM PRESSURE

A method (200) includes determining a current burn flow value of a turbine engine (205), measuring a fuel pressure of a metered fuel flow of liquid fuel to a combustor of the turbine engine at a measu…

DRIVE·4d ago·1 min read

F02C7/22 RTX CORP [US]

ATTACHMENT FOR MOUNTING AIRCRAFT PROPULSION SYSTEM TO PYLON STRUCTURE

An aircraft system includes a turbine engine case and an attachment that is configured to mount the turbine engine case (64) to a pylon structure (88) and transfer one or more loads between the turbin…

DRIVE·4d ago·2 min read

B64D27/402 RTX CORP [US]

NOSE CONE WITH AIR SCOOP FOR OPEN ROTOR PROPULSION SYSTEM

An assembly is provided for an aircraft propulsion system (20). This assembly includes an open propulsor rotor (34) and a nose cone (38). The open propulsor rotor (34) is configured to rotate about an…

DRIVE·4d ago·2 min read

B64C11/14 RTX CORP [US]

OPEN ROTOR GAS TURBINE ENGINE WITH ADAPTIVE TURBINE CLEARANCE CONTROL SYSTEM AND METHOD

A gas turbine engine (20) disposed within a nacelle (40) is provided that includes an open rotor propulsion system (28), compressor (30), combustion (32), and turbine (34) sections, a lubrication syst…

DRIVE·Jun 10·1 min read

F01D11/14 RTX CORP [US]

GAS TURBINE ENGINE WITH ADAPTIVE TURBINE CLEARANCE CONTROL SYSTEM AND METHOD

A gas turbine engine (20) is provided that includes fan (28), compressor (30), combustion (32), and turbine (34) sections, a fan bypass air path (38), and a turbine active clearance control system (54…

DRIVE·Jun 10·2 min read

F01D11/24 RTX CORP [US]

GAS TURBINE ENGINE WITH ADAPTIVE TURBINE CLEARANCE CONTROL SYSTEM AND METHOD

Gas turbine engine (20) including a fan (28), compressor, combustion (32), and turbine sections, a fan bypass air path (38), a lubrication system (70), and a turbine active clearance control system (5…

DRIVE·Jun 10·2 min read

F01D11/24 RTX CORP [US]

ASSEMBLY FOR MOUNTING AN AUXILIARY COMPONENT TO AN ENGINE CASE OF A GAS TURBINE ENGINE, AND GAS TURBINE ENGINE

An assembly (200) for mounting an auxiliary component to an engine case (110) of a gas turbine engine (100) includes a support bracket (122), the support bracket having a first end (230) configured fo…

DRIVE·Jun 10·2 min read

F01D21/045 RTX CORP [US]

AIRCRAFT WITH ELECTRICALLY POWERED ENGINE ACCESSORIES

An aircraft assembly includes a fan case (70), a core case (62), an accessory gearbox (104), one or more electric machines (94), a first electric device (120) and an electrical system (92). The core c…

DRIVE·Jun 10·2 min read

B64D27/10 RTX CORP [US]

GAS TURBINE ENGINE WITH ADAPTIVE TURBINE COOLING AIR SYSTEM AND METHOD

A gas turbine engine (20) includes compressor (30) and turbine (34) sections, and a turbine cooling air (TCA) system (54). The turbine section (34) has upstream (44A) and downstream (44B) rotor stages…

DRIVE·Jun 10·2 min read

F01D11/24 RTX CORP [US]

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]

OPEN ROTOR GAS TURBINE ENGINE WITH ADAPTIVE TURBINE CLEARANCE CONTROL SYSTEM AND METHOD

A gas turbine engine (20) disposed within a nacelle (40) includes an open rotor propulsion system (28), compressor (30), combustion (32), and turbine (34) sections, and a turbine active clearance cont…

DRIVE·Jun 10·2 min read

F01D11/24 RTX CORP [US]

TURBINE ENGINE WITH INVERSE BRAYTON CYCLE

An engine system (200) includes a turbine engine (202) including a compressor section (206), a combustor section (208) having a burner, a turbine section (210), and a nozzle (212) in an open-loop conf…

DRIVE·Jun 10·1 min read

F02C6/006 RTX CORP [US]

STARTING OPEN ROTOR PROPULSION SYSTEM DURING AIRCRAFT FLIGHT

A propulsion system (20) includes an open propulsor rotor (34), an open guide vane structure (36), a turbine engine (32) and a blade actuation system (48). The open propulsor rotor (34) includes a plu…

DRIVE·Jun 10·2 min read

B64C11/305 RTX CORP [US]

AIRCRAFT WITH SYMMETRIC PROPULSION SYSTEM ROTATING PATTERNS

A first core turbine rotor of a first propulsion system (24A) is disposed in a first core turbine section (89) and is configured to rotate in a first rotational direction. A first power turbine rotor …

DRIVE·Jun 10·2 min read

B64D27/10 RTX CORP [US]

INTEGRATED VEHICLE MOUNT STRUCTURE

An integrated mount structure (42) including a foundation section (46) located adjacent to a shoulder section (40) of an aft case section (30) of an engine (10); a column section (50) adjacent the fou…

DRIVE·Jun 10·1 min read

B22F10/68 RTX CORP [US]

CRYOGENIC COOLING SYSTEM FOR AN AIRCRAFT

A cryogenic cooling system (2200) for an aircraft (800) includes a first air cycle machine (2201), a second air cycle machine (2220), and a means for collecting liquid air. The first air cycle machine…

DRIVE·Jun 3·1 min read

B01D45/08 RTX CORP [US]

OPEN ROTOR AIRCRAFT PROPULSION SYSTEM WITH GUIDE VANE STRUCTURE RECEPTACLE

An aircraft propulsion system (20) assembly includes an open propulsor rotor (34) and a housing structure (54). The housing structure (54) includes an engine case (106), a nacelle structure (108) and …

DRIVE·May 27·1 min read

B64C7/02 RTX CORP [US]

AIRCRAFT SYSTEM WITH GAS TURBINE ENGINE POWERED COMPRESSOR

An aircraft system (20) includes a gas turbine engine (22), a gearbox (26) and at least one compressor (24). The gas turbine engine (22) includes a compressor section (32), a turbine section (36), a c…

DRIVE·May 27·1 min read

F02C3/073 RTX CORP [US]

AIRCRAFT POWERPLANT GEARBOX WITH SELECTABLE POWER COUPLER

An aircraft powerplant (20) assembly includes a gearbox (88) and a power coupler (90). The gearbox (88) includes a first engine power transfer apparatus (120), a second engine power transfer apparatus…

DRIVE·May 27·1 min read

F01D15/10 RTX CORP [US]

AIRCRAFT POWERPLANT WITH ELECTRIC MACHINE SYSTEM

An aircraft powerplant (20) assembly includes a gearbox (102), a first electric machine (90A), a first electric cable (112A), a second electric machine (90B) and a second electric cable (112B). The fi…

DRIVE·May 27·2 min read

F02C3/10 RTX CORP [US]

CMC COMPONENT WITH DORMANT COOLING HOLES

A method is described for introducing dormant cooling holes (120) into CMC components that have a base (200) made of a first group of plies (110) and a second group of plies (210). Before or after den…

DRIVE·May 27·1 min read

C04B35/62886 RTX CORP [US]

AIRFOIL WITH GEOMETRICALLY SEGMENTED COATING SECTION HAVING MECHANICAL SECONDARY BONDING FEATURE

An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall (172) that has an outer side. The outer side include…

DRIVE·May 27·1 min read

F01D5/28 RTX CORP [US]

BACKSIDE FEATURES WITH INTERMITTED PIN FINS

According to one embodiment, a heat shield panel (400) for a combustor (300) of a gas turbine engine is provided. The heat shield comprising: a panel body (402) having a first surface (410) configured…

DRIVE·May 27·1 min read

B22C7/02 RTX CORP [US]

TURBO EXPANDERS FOR TURBINE ENGINES HAVING HYGRODEN FUEL SYSTEMS

An aircraft propulsion system includes aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure …

DRIVE·May 27·2 min read

B64D15/12 RTX CORP [US]

CONSTRAINTS ENGINE AND ASSOCIATED METHODS FOR DESIGN TOOL

A system (60) for establishing components of a gas turbine engine (20) may include a constraints engine (62). The constraints engine (62) may be operable to determine a set of constraints (81) based o…

DRIVE·May 27·2 min read

F02C3/06 RTX CORP [US]

REDUCED MISALIGNMENT GEAR SYSTEM

A lubrication system for a fan drive planetary gear system includes a stationary first bearing configured to receive a lubricant from a lubricant input, the stationary first bearing is located adjacen…

DRIVE·May 20·1 min read

F01D25/16 RTX CORP [US]

PRE-SHAPED SPACE FILLERS FOR SMALL CROSS SECTION FEATURES

A method of fabricating a variable geometry space filling insert for a ceramic matrix composite component includes arranging a plurality of fiber bodies (26A) into a preform insert (12A), applying a p…

DRIVE·May 13·1 min read

B29B11/16 RTX CORP [US]

STEAM TURBINE BYPASS FOR INCREASED WATER HEAT ABSORPTION CAPACITY STEAM INJECTED TURBINE ENGINE

A turbine engine assembly (20) includes a core engine (22) that generates an exhaust gas flow (38), a condenser (48) where water is extracted from the exhaust gas flow (38), an evaporator (64) where h…

DRIVE·May 6·1 min read

B64D27/026 RTX CORP [US]

MODULAR HEAT EXCHANGER FOR AN AIRCRAFT POWERPLANT

An apparatus is provided for an aircraft powerplant. This apparatus includes a heat exchanger (20). The heat exchanger (20) includes a frame (22), a plurality of heat exchanger cores (24), a first flo…

DRIVE·May 6·1 min read

B64D33/08 RTX CORP [US]

TURBO EXPANDERS FOR TURBINE ENGINES HAVING HYDROGEN FUEL SYSTEMS

DRIVE·May 6·2 min read

B64D15/12 RTX CORP [US]

TURBINE ENGINE WITH INVERSE BRAYTON CYCLE

DRIVE·Apr 29·1 min read

F02C6/006 RTX CORP [US]

BIFURCATION AIR SCOOP FOR GAS TURBINE ENGINE

A gas turbine engine includes a fan received within a fan case (102), the fan delivers bypass air into a bypass duct between an inner radial portion of the fan case (102) and an outer radial surface o…

DRIVE·Apr 29·2 min read

B64D13/02 RTX CORP [US]

ENGINE BEARING SUPPORT

A turbofan engine (20) comprises an engine case (22). A gaspath extends through the engine case (22). A fan (42) has a circumferential array of fan blades (100). A fan case (40) encircles the fan blad…

DRIVE·Apr 22·1 min read

F01D25/16 RTX CORP [US]

FUEL-AIR MIXER FOR TURBINE ENGINE COMBUSTION SECTION

An apparatus for a turbine engine (20) includes a fuel-air mixer (66) having an inner passage (130), a sidewall (110), a fuel nozzle (112), an air swirler (116) and a first quench aperture (146A). The…

DRIVE·Apr 15·1 min read

F02C7/22 RTX CORP [US]

MODULATING FLUID FLOW WITHIN A TURBINE ENGINE USING STEAM

An assembly is provided for a turbine engine (20) includes a combustor (62) and an injection system (104). The combustor (62) includes a combustion chamber (60). The injection system (104) includes an…

DRIVE·Apr 15·1 min read

F02C3/30 RTX CORP [US]

SYSTEM FOR ACTIVE DATA ACQUISITION MANAGEMENT IN A GAS TURBINE ENGINE

An aircraft sensor system (100) includes a first sensor (90; 110; 430) configured to detect a parameter of an aircraft system and a first micro electromechanical-system (MEMS) (120, 122, 124, 126, 128…

DRIVE·Apr 8·2 min read

F01D17/02 RTX CORP [US]

ACOUSTIC ATTENUATION STRUCTURES

Acoustic structures (122; 222; 322) for a gas turbine engine (100) are disclosed. In various embodiments, the acoustic structures (122; 222; 322) comprise a panel (118; 218) in the form of a cellular …

DRIVE·Apr 8·2 min read

B64D27/10 RTX CORP [US]

HYBRID ELECTRIC POWER FOR TURBINE ENGINES HAVING HYDROGEN FUEL SYSTEMS

An aircraft propulsion systems (400) has an aircraft systems (404) including at least one hydrogen tank (432) and an aircraft-systems heat exchanger (458) and engine systems (402) includes at least a …

DRIVE·Apr 8·1 min read

B64D37/30 RTX CORP [US]