A process for coating a gas turbine engine disk comprises placing the disk having an outer surface into a chamber, the chamber configured to perform atomic layer deposition; injecting a first reactant into the chamber; forming a first monolayer gas thin film on the outer surface; removing the first reactant from the chamber; injecting a second reactant into the chamber; reacting second reactant with the first monolayer gas thin film; removing the second reactant from the chamber; and forming a protective barrier coating on the outer surface.

A process for coating a gas turbine engine disk comprises placing the disk having an outer surface into a chamber, the chamber configured to perform atomic layer deposition; injecting a first reactant into the chamber; forming a first monolayer gas thin film on the outer surface; removing the first reactant from the chamber; injecting a second reactant into the chamber; reacting second reactant with the first monolayer gas thin film; removing the second reactant from the chamber; and forming a protective barrier coating on the outer surface.

A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.

A method for balancing a set of blades intended to be arranged on a bare disc of an aircraft engine, the bare disc comprising a defined number of numbered cells (ai) intended to receive the same defined number of blades, which can have a spread of mass, the method comprising the following steps:—sorting the blades by monotonic order of their mass (mi) to form an ordered set of blades,—separating the ordered set of blades in a balanced manner into four lobes constituted by a first large lobe, by a second large lobe, by a first small lobe and by a second small lobe, the blades being classified into each lobe according to a current placement order, and—arranging the four lobes on the bare disc by making the current placement order of the blades correspond to the numbered cells of the bare disc.

The present invention relates to a high-speed dewatering and pulverizing turbine (1) for obtaining solid pulverized particles and dissociating the water present, which is formed by: a) a stator (6) having circular geometry with a duct at one end (7) for the outlet of the solid pulverized particles and a duct in the bottom part (10) for the inlet of solid particles to be pulverized; b) a wheel or rotor with vanes or blades, located inside the stator; and c) a central securing assembly for adjusting and securing all the elements that form the wheel or rotor. Also described is a method for obtaining solid pulverized and dewatered particles, wherein the water present is separated.

The present invention relates to a high-speed dewatering and pulverizing turbine (1) for obtaining solid pulverized particles and dissociating the water present, which is formed by: a) a stator (6) having circular geometry with a duct at one end (7) for the outlet of the solid pulverized particles and a duct in the bottom part (10) for the inlet of solid particles to be pulverized; b) a wheel or rotor with vanes or blades, located inside the stator; and c) a central securing assembly for adjusting and securing all the elements that form the wheel or rotor. Also described is a method for obtaining solid pulverized and dewatered particles, wherein the water present is separated.

A steam turbine includes a rotor, a casing, a partition plate, and a center guide pin. The center guide pin has a positioning portion. In a state of being attached to a pin attachment portion formed in one of the casing and the partition plate, the positioning portion is disposed in a groove portion formed in the other of the casing and the partition plate. The positioning portion includes a plurality of abutment portions capable of abutting on an inner side surface of the groove portion, around a pin axis. The plurality of abutment portions is formed to have different horizontal distances from the pin axis.

A steam turbine includes a rotor, a casing, a partition plate, and a center guide pin. The center guide pin has a positioning portion. In a state of being attached to a pin attachment portion formed in one of the casing and the partition plate, the positioning portion is disposed in a groove portion formed in the other of the casing and the partition plate. The positioning portion includes a plurality of abutment portions capable of abutting on an inner side surface of the groove portion, around a pin axis. The plurality of abutment portions is formed to have different horizontal distances from the pin axis.

A method for converting a turbofan engine including providing a turbofan engine and converting the turbofan engine. The turbofan engine includes a core engine (including at least one high pressure spool assembly and a combustion chamber), and an unmodified fan configured for providing at least a bypass flow bypassing the core engine, the fan being mechanically coupled to a low pressure turbine that is in turn driven by the core engine. The conversion includes modifying or replacing the unmodified fan to provide a modified fan, the modified fan configured for generating a reduced bypass flow with respect to said fan bypass flow during operation of the converted turbofan engine corresponding to at least one set of engine conditions, enabling said low pressure turbine to generate an excess shaft power above a baseline shaft power required for driving the modified fan during operation of the converted turbofan engine.

A method for converting a turbofan engine including providing a turbofan engine and converting the turbofan engine. The turbofan engine includes a core engine (including at least one high pressure spool assembly and a combustion chamber), and an unmodified fan configured for providing at least a bypass flow bypassing the core engine, the fan being mechanically coupled to a low pressure turbine that is in turn driven by the core engine. The conversion includes modifying or replacing the unmodified fan to provide a modified fan, the modified fan configured for generating a reduced bypass flow with respect to said fan bypass flow during operation of the converted turbofan engine corresponding to at least one set of engine conditions, enabling said low pressure turbine to generate an excess shaft power above a baseline shaft power required for driving the modified fan during operation of the converted turbofan engine.