A pressure reduction system may include an alternator with a casing and a rotor positioned, at least in part, within a cavity defined by the casing. The pressure reduction system may also include a mass management system that includes a control tank configured to be maintained at a tank pressure lower than a cavity pressure within the cavity of the alternator, thereby forming a pressure differential. A first transfer conduit may transfer a working fluid from the cavity of the alternator to the control tank via the pressure differential. The mass management system may be positioned at an elevation above the alternator, and include a refrigeration loop configured to cool the working fluid contained within the control tank. A second transfer conduit may fluidly couple the alternator and the mass management system, and may transfer the cooled working fluid from the control tank to the cavity via gravitational force.

A system for liquefying natural gas that includes a process and apparatus for enhancing the performance of one or more gas turbines. Gas turbine power output can be stabilized or even enhanced using the interstage cooling system configured according to one or more embodiments of the present invention. In one embodiment, partially compressed air from a lower compression stage of a gas turbine is cooled via indirect heat exchange with a primary coolant before being returned to a higher compression stage of the same gas turbine. Optionally, the interstage cooling system can employ one or more secondary coolants to remove the rejected heat from the primary coolant system.

An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.

An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.

A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

A turbomachine having a rotor assembly, a stator assembly and a toroidal inductor. The rotor assembly includes an impeller. The inductor is located between the impeller and the stator assembly, and is exposed to an airflow generated by or acting upon the impeller.

A turbomachine having a rotor assembly, a stator assembly and a toroidal inductor. The rotor assembly includes an impeller. The inductor is located between the impeller and the stator assembly, and is exposed to an airflow generated by or acting upon the impeller.

An electromechanical is provided which includes an electromagnetic rotor, a housing with an interior opening with a stop, a first bearing mount for supporting a first bearing rotatably mounting the rotor in the housing, a cover connected with the housing having a boss having an interior providing a second bearing mount supporting a second bearing rotatably mounting the rotor in the housing, a stator having a clearance fit within the housing interior opening, the stator being axially limited in a direction toward such first bearing mount by the housing stop, the stator having an axial clearance in a direction toward the cover boss, and an elastomeric spacer connected on an extreme end of the boss compliantly filling the axial clearance between the stator and the boss positioning the stator in an axial direction and restricting movement of the stator in an angular direction within the housing opening.

An electromechanical is provided which includes an electromagnetic rotor, a housing with an interior opening with a stop, a first bearing mount for supporting a first bearing rotatably mounting the rotor in the housing, a cover connected with the housing having a boss having an interior providing a second bearing mount supporting a second bearing rotatably mounting the rotor in the housing, a stator having a clearance fit within the housing interior opening, the stator being axially limited in a direction toward such first bearing mount by the housing stop, the stator having an axial clearance in a direction toward the cover boss, and an elastomeric spacer connected on an extreme end of the boss compliantly filling the axial clearance between the stator and the boss positioning the stator in an axial direction and restricting movement of the stator in an angular direction within the housing opening.