A gas turbine engine is disclosed having a turbine, one or more hydrocarbon gas combustors, and a compressor. The compressor has a rotor assembly with one or more rotor blade rows extending radially outward from an inner wheel disk. The compressor also has a stator assembly with one or more stator vane rows extending radially inward from an inner casing and positioned between adjacent rotor blade rows. The inner casing extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy.

A clearance adjusting apparatus disposed in front of a compressor of a gas turbine to axially move a compressor disk back and forth to adjust a tip clearance formed between a compressor blade and a compressor casing is provided. The clearance adjusting apparatus includes a hollow fastening part disposed in front of the compressor casing, a shaft disposed in the fastening part and coupled to a front side of the compressor disk, an adjusting part disposed between the fastening part and the shaft to axially move the shaft back and forth to adjust the tip clearance, and a biasing part disposed on the fastening part to bias the adjusting part back and forth to adjust a position of the adjusting part and the shaft.

The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.

A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical bushings, each being put into place in a chimney of the inner ring from the inside and each serving to receive a guide pivot of a stator vane, a plurality of reconstitution ring angular sectors arranged end-to-end in order to form a reconstitution ring and put into place radially from the inside against the inner ring, and a plurality of blocking elements passing axially through the inner and reconstitution rings in order to assemble the rings together.

A clearance adjusting apparatus disposed in front of a compressor of a gas turbine to axially move a compressor disk back and forth to adjust a tip clearance formed between a compressor blade and a compressor casing is provided. The clearance adjusting apparatus includes a hollow fastening part disposed in front of the compressor casing, a shaft disposed in the fastening part and coupled to a front side of the compressor disk, an adjusting part disposed between the fastening part and the shaft to axially move the shaft back and forth to adjust the tip clearance, and a biasing part disposed on the fastening part to bias the adjusting part back and forth to adjust a position of the adjusting part and the shaft.

The invention relates to a bearing preload force gauge for indicating the bearing preload force on a turbomolecular pump rotor bearing. The gauge comprises a housing, an indicator for indicating the bearing preload force, and actuator coupled to an impeller engagement surface by a member configured to provide a resilient bias between the actuator and the impeller engagement surface. The invention also relates to a bearing preload tool and methods for measuring the bearing preload force on a turbomolecular pump.

A method of installing a diffuser in an air cycle machine includes placing a first housing on a shaft, placing a seal plate on the shaft, and placing a diffuser on the shaft. Next, the diffuser and the seal plate are aligned with an alignment tool. The alignment tool has a first annular surface to align with a radially outer surface of the seal plate and a second annular surface to align with an annular flange on the diffuser. Finally, the diffuser is fastened to the seal plate and the alignment tool is removed from the diffuser and the seal plate.

An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.

A system for the active setting of a radial clearance size between a blade tip of at least one compressor stage and/or at least one turbine stage of an aircraft engine and a housing that surrounds the at least one compressor stage and/or the at least one turbine stage is provided. The system comprises a model-based setting device, wherein the time-dependent clearance size can be approximated by the model-based setting device, with only those influencing variables being taken into account that have a time-dependent deformation behavior which is equal to or slower than the time-dependent deformation behavior of the housing. The clearance size in the cold state serves as the set point, with the clearance size being reduced by at least one previously saved value of a clearance proportion, which is determined at maximal thrust of the aircraft engine.

An example axial pump for delivering liquid coolant to cool an electronic device comprises a conduit defining a flow path from an inlet of the conduit to an outlet of the conduit and an impeller in the conduit. The impeller is rotatable about an axis of rotation parallel to the flow path. The pump also has a motor stator configured to drive rotation of the impeller body about the axis of rotation. In addition, the pump comprises an adjustment mechanism coupling the impeller to the conduit. The adjustment mechanism is actuatable to cause translation of the impeller relative to the conduit. This may allow for adjustment of a clearance between a blade tip of a blade of the impeller and a wall of the conduit.