A gas turbine engine includes a fan section that has fan blades that drive air along a bypass flow path in a bypass duct. A fan shaft is drivingly connected to the fan. A turbine section includes a turbine drive shaft. A gear system is connected to the turbine draft shaft through an input and connected to the fan shaft through an output. At least one of the input and the output include a flexible coupling. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the turbine drive shaft during operation. The gear system flex mount arrangement includes a gear mesh that defines a gear mesh lateral stiffness and a ring gear that defines a ring gear lateral stiffness that is less than 12% of the gear mesh lateral stiffness.

The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first heat exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

A multi-ring spacer includes a first ring having a first clocking position, a second ring coaxial with the first ring, and having a second clocking position. A total kink angle of the multi ring spacer is dependent on an angular deviation of the second ring's clocking position relative to the first ring's clocking position.

A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.

The method comprises the steps of: a) cutting the shaft of the rotor at a section plane perpendicular to the axis of rotation of the shaft so as to separate the end portion of the shaft on which the bladed discs to be replaced are mounted from the remaining portion of the shaft; b) providing, for each bladed disc to be replaced, a corresponding new bladed disc with a respective hub having a solid cross-section; c) providing a new end portion of the shaft with a solid cross-section; and d) clamping the new bladed discs between the remaining portion of the shaft and the new end portion of the shaft, securing them to the remaining portion of the shaft by anchor bolts.

In a vacuum pump, a portion of a lower end portion of a rotating cylindrical body is cut in an axial direction thereof to form an imbalance correction portion (removal portion). Preferably, the removal portion is formed so as to minimize an axial width of the rotating cylindrical body and set a circumferential width of the rotating cylindrical body to a value of not less than a thickness (width in a radial direction) of the rotating cylindrical body. Additionally, a corner formed in the removal portion is formed to have a large. With this configuration, in the rotating cylindrical body, the removal portion is formed to have a shape in which a removal width (depth) in the axial direction of the rotating cylindrical body is small and a removal width in the circumferential direction thereof is large.

A system for rotating a turbomachine rotor relative to a stator casing, the rotor including an annular row of blades, the rotating system including a supporting arm including a first end arranged for gripping a leading edge of a first blade of the annular row and a second end arranged for gripping a trailing edge of the first blade; an electric motor including a shaft and a body attached to the supporting arm; and a wheel coupled to the shaft of the motor and provided with a rolling strip, the wheel, furthermore, being arranged so that the rolling strip can come into contact with an annular wall of the stator casing when the supporting arm is mounted on the first blade.

An ammonia plant synthesis gas compressor train includes a steam turbine; and a compression unit that compresses a synthesis gas by being rotationally driven by the steam turbine. The compression unit includes a rotary shaft that rotates around an axis, and a plurality of impellers that are provided on the rotary shaft at intervals in a direction of the axis and are rotated integrally with the rotary shaft to pump a gas outward in a radial direction to compress the gas. In at least one of the impellers, a maximum operating peripheral speed at a radially outermost position of the impeller is within a range of 290 m/s to 390 m/s, a yield strength is 827 MPa or less, and a Brinell hardness is 311 or less.

A turbofan engine according to an example of the present disclosure includes, among other things, a fan section including a plurality of fan blades, a gear train, a low pressure turbine driving the fan section through the gear train, a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle, a fan bypass flow path defined between the core nacelle and the fan nacelle, and a fan variable area nozzle in communication with the fan bypass flow path, and defining a fan nozzle exit area between the fan nacelle and the core nacelle. The fan variable area nozzle includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movably mounted relative the first fan nacelle section and moveable axially along an engine axis of rotation relative the first fan nacelle section, defining an auxiliary port that extends between the first fan nacelle section and the second fan nacelle section.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor that delivers flow to a core flowpath and a compressor section including first and second compressors. The core flowpath passes through the first compressor. The core flowpath in the first compressor has an outer diameter relative to the engine longitudinal axis. The outer diameter has a slope angle relative to the axis.