#F02C3/10

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]

TURBOSHAFT ENGINE WITH AXIAL COMPRESSOR

A turboshaft engine (10) includes a core section (100) extending between an inlet (12) and an outlet (14) of the turboshaft engine (10). The core section (100) includes a compressor (18, 26), a main c…

DRIVE·Mar 25·2 min read

F02C3/10 RTX CORP [US]

TURBOFAN GAS TURBINE ENGINE WITH COMBUSTED COMPRESSOR BLEED FLOW

A gas turbine engine (20) includes a core section including a compressor (44, 50), a main combustor (54), and a main turbine (46, 52). Combustion products from the main combustor (54) drive rotation o…

DRIVE·Mar 25·2 min read

F02C3/10 RTX CORP [US]

HYDROGEN FUELED TURBINE ENGINE CONDENSER DUCT

A propulsion system for an aircraft including a gas generating core engine (70) that generates an exhaust gas flow (52) that is expanded through a turbine section (32). A power turbine (38) engine is …

DRIVE·Mar 11·2 min read

F02C3/10 RTX CORP [US]

TURBINE ENGINE BLEED WASTE HEAT RECOVERY

A gas turbine engine assembly includes a core engine that includes a core flow path (C) where a core airflow (25) is compressed in a compressor section (24), communicated to a combustor section (26), …

DRIVE·Nov 12·2 min read

F02C3/10 RTX CORP [US]

SPLIT COMPRESSOR GAS TURBINE ENGINE

A turboprop or turboshaft gas turbine engine (10) includes a low pressure turbine (30) drivingly engaged to an output shaft (46) for driving a rotatable load (22). A low pressure compressor (26) is de…

DRIVE·Jul 10·2 min read

F02C3/10 PRATT & WHITNEY CANADA [CA]

SPEED LIMITING FOR POWER TURBINE GOVERNING AND PROTECTION IN A TURBOSHAFT ENGINE

A control system (240) for limiting a power turbine torque of a gas turbine engine (100; 300) is disclosed. In various embodiments, the control system (240) includes an engine control module (242) con…

DRIVE·May 15·1 min read

F02C3/10 RTX CORP [US]

TURBOFAN WITH OFFSET GAS GENERATOR AND AUXILIARY POWER CORE

A gas turbine engine (10) includes a fan (22) positioned at an engine central longitudinal axis (A), and a fan drive turbine (58) located at the engine central longitudinal axis (A) and configured to …

DRIVE·May 15·2 min read

F02C3/10 RTX CORP [US]

Gas turbine engine with auxiliary fan

A method of operating a propulsion system (14) includes powering an auxiliary fan (18) with a gas turbine engine (20), where the auxiliary fan (18) is along an auxiliary axis (F) and the gas turbine e…

DRIVE·May 1·1 min read

F02C3/10 UNITED TECHNOLOGIES CORP [US]

Combuster control method and combustor controller

Provided are a combustor control method and a combustor controller capable of calculating the combustion air flow and the fuel flow in multi-shafts gas turbine with high precision and without the need…

DRIVE·May 2·2 min read

F02C3/10 HITACHI LTD [JP]

Gas turbine engine

An engine arrangement has a first propeller assembly (21a), and a first hydraulic actuator (23a) for angular displacement of propellers (22a) of the first propeller assembly, the first hydraulic actua…

DRIVE·Jun 15·2 min read

F02C3/10 ROLLS ROYCE PLC [GB]

Method of detecting in-range engine sensor faults

The subject invention is directed to a new and useful method of detecting in-range engine sensor faults for a gas turbine engine associated with a helicopter. The method includes the steps of computin…

DRIVE·May 21·2 min read

F02C3/10 GOODRICH PUMP & ENGINE CONTROL [US]