A device for de-icing a splitter nose of an aviation turbine engine, the device including a splitter nose having an outer annular wall defining the inside of the bypass stream flow channel and an inner annular wall defining an inlet of the core stream flow channel, and an inner shroud mounted at its upstream end on the inner annular wall of the splitter nose and designed to have inlet guide vanes fastened thereto, the splitter nose and the inner shroud defining an annular volume. The device includes an annular deflector positioned inside the annular volume so as to subdivide the annular volume into a first annular cavity and a second annular cavity, the second annular cavity being defined between the annular deflector and the outer annular wall of the splitter nose.

An exemplary system may include a gas turbine engine configured to operate at an engine power level to satisfy an engine power demand. The system may also include at least one generator operatively coupled to the engine and configured to generate electrical power based at least in part on the engine power demand. The system further may include at least one heating element in communication with the at least one generator, and at least one control unit coupled to the at least one heating element. The at least one heating element may be configured to receive electrical power from the at least one generator to generate thermal energy. The at least one control unit may be configured to energize the heating element when the engine power demand is below the engine power level and/or there is an anticipated increase in the engine power demand.

An exemplary system may include a gas turbine engine configured to operate at an engine power level to satisfy an engine power demand. The system may also include at least one generator operatively coupled to the engine and configured to generate electrical power based at least in part on the engine power demand. The system further may include at least one heating element in communication with the at least one generator, and at least one control unit coupled to the at least one heating element. The at least one heating element may be configured to receive electrical power from the at least one generator to generate thermal energy. The at least one control unit may be configured to energize the heating element when the engine power demand is below the engine power level and/or there is an anticipated increase in the engine power demand.

A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.

A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.

A turbomachine comprising a cone positioned at an upstream end and secured in rotation to the low-pressure shaft, a system for deicing said cone, comprising resistive heating elements positioned in the cone, an energy transfer system, an electrical power source coupled to the high-pressure shaft and connected to the energy transfer system by a set of switches, and a computer configured so as to define a power set point for deicing the cone depending on ambient temperature and pressure data, and on an operating speed of the low-pressure shaft, and, depending on the electrical power supplied by the electrical power source, define a duty cycle of the set of switches to deliver electrical power to the resistive heating elements.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

[Object] To provide a fan blade, an engine, and a structure with anti-icing and de-icing functions, which are capable of efficiently performing anti-icing or de-icing with a simple structure. [Solving Means] A fan blade 8 is disposed on an air inlet 4 side of a jet engine 1 of an aircraft. The fan blade 8 includes a fan blade main body 21 made of a carbon fiber reinforced plastic (CFRP), and a pair of energizing units 31 and 32 that are provided on a leading edge 24 side and a trailing edge 25 side of a heating region 36 of the fan blade main body 21 and pass current through the fan blade main body 21. Voltage is applied between the pair of energizing units 31 and 32 and current passes through the fan blade main body 21 to heat the fan blade main body 21, thus performing anti-icing or de-icing.

The invention relates to a de-icing device designed to supply de-icing air to a turbomachine separation nozzle extending along a longitudinal axis, the turbomachine comprising:—the separation nozzle which is designed to be positioned downstream from a turbomachine fan and comprises an internal casing and an external casing which form a separation between a primary flow vein for a primary stream and a secondary flow vein for a secondary stream, said streams issuing from the fan, the internal casing and the external casing defining an inter-vein space;—turbomachine guide vanes designed to be secured by screws to the internal casing such that the screws extend into the inter-vein space, the de-icing device being intended to be positioned in the inter-vein space and comprising—an air inlet;—an air outlet;—a plurality of channels extending from the air inlet toward the air outlet; the channels being arranged in relation to one another such that they are designed to extend from the air inlet toward the air outlets, passing between the screws for securing the guide vanes.