#F01D25/02

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

A vane assembly (200) for a gas turbine engine (10). The vane assembly is a single unitary component that includes an aerofoil (202). The vane assembly further includes a leading edge passageway (230)…

DRIVE·Dec 31·2 min read

F01D25/02 ROLLS ROYCE PLC [GB]

PROTECTION SYSTEM FOR GAS TURBINE ENGINE IN ICE CRYSTAL CONDITIONS

A gas turbine engine (10) comprises a fan (23); an engine core (11) comprising a compressor (14), a combustor (16), and a turbine (19) coupled to the compressor (14) through a shaft (26); a reduction …

DRIVE·Nov 6·2 min read

F01D25/02 ROLLS ROYCE PLC [GB]

CLOSED LOOP FAN INLET VANE ANTI ICING SYSTEM

A gas turbine engine de-icing system includes a heat exchanger (64). A coolant loop (92) is in fluid communication with the heat exchanger and is configured to circulate a heat transfer fluid. An engi…

DRIVE·Aug 14·1 min read

F01D25/02 RTX CORP [US]

Method and device for suppressing the formation of ice on structures at the air intake of a turbomachine

The application relates to a method and a device for suppressing ice formation on intake structures of a compressor, particularly the compressor of a gas turbine. The technical aim of the present inve…

DRIVE·Dec 24·2 min read

F01D25/02 ALSTOM TECHNOLOGY LTD [CH]

Gas turbine engine with an heated rigid electrical system

A rigid electrical raft has electrical conductors embedded in a rigid material. The electrical conductors transmit electrical signals through the rigid electrical raft, which may form part of an elect…

DRIVE·Jun 18·1 min read

F01D25/02 ROLLS ROYCE PLC [GB]

SPLITTER OF AN AXIAL TURBOMACHINE, CORRESPONDING COMPRESSOR AND AXIAL TURBOMACHINE

The nose (122) has guide walls which are provided to extend from a leading edge. A leading edge de-icing channel (140) is provided to extend annularly along the edge. The channel is designed to conduc…

DRIVE·Jun 11·1 min read

F01D25/02 TECHSPACE AERO SA [BE]

System and method for heat recovery in a gas turbine engine

A system (10) includes an anti-icing heat recovery system (50), which includes a first heat exchanger (54), a second heat exchanger (58), and a variable speed fan (56). The first heat exchanger (54) i…

DRIVE·Nov 20·2 min read

F01D25/02 GEN ELECTRIC [US]

Gaseous flow separator with device for thermal-bridge defrosting

The separator has a leading edge de-icing device comprising a metal blade (38) that is in thermal contact with a separator leading edge (30). The blade extends from the leading edge to a rear part of …

DRIVE·Oct 3·1 min read

F01D25/02 TECHSPACE AERO SA [BE]

Heated booster splitter plenum

A splitter apparatus for a gas turbine engine includes: a splitter (38) including: an annular outer wall (40) which defines a convex-curved leading edge at a forward end thereof; an annular floorplate…

DRIVE·Aug 1·1 min read

F01D25/02 GEN ELECTRIC [US]

Integration of a surface heat exchanger with controlled air flow in an airplane engine

The cooler (1) has outer and inner exchange surfaces (2, 3) positioned on sides of an oil circuit (4) and swept by an air flow. The inner surface is positioned in a cavity (9) provided with an air inl…

DRIVE·Jul 4·1 min read

F01D25/02 TECHSPACE AERO SA [BE]

Turbofan engine internal anti-ice device

A system and method are provided for preventing the formation of ice on or removing ice from an internal surface of a turbofan engine. A splitter region (18), associated with a booster compressor of t…

DRIVE·Apr 7·1 min read

F01D25/02 GEN ELECTRIC [US]

Methods and apparatus for operating gas turbine engines

A method for operating an aircraft engine facilitates preventing ice accumulation on the aircraft engine. The method comprises coupling a semi-permeable membrane (66) to the engine adjacent an outer s…

DRIVE·Jan 7·1 min read

F01D25/02 GEN ELECTRIC [US]