The invention relates to a method for determining a balancing removal process for a balancing device for balancing a rotationally symmetrical component, particularly a rotor component, particularly of a turbomachine, a combination of machining lengths and depths being calculated, taking into account a pre-defined maximum machining length and minimum machining depth, in such a way that, with reliable combinations for compensating the same unbalance, the machining length of the calculated combination is longer than the machining length of at least one other permissible combination and, at the same time, the machining depth of the calculated combination is shallower than the machining depth of said other combination.

A compressor blade of a gas turbine includes a root member; an airfoil that is disposed on the root member and includes a first interior wall and a second interior wall forming a hollow space defined between the first and second interior walls; and an organic vibration stiffener (OVS) formed on at least one of the first interior wall and the second interior wall. The OVS is formed by 3D printing performed with respect to a surface of the at least one of the first interior wall and the second interior wall and includes an uneven surface formed on at least part of the at least one of the first interior wall and the second interior wall. The OVS may include a protruded or recessed portion protruding from or recessed into at least part of the at least one of the first interior wall and the second interior wall.

A balancing assembly for a rotating component of a gas turbine engine includes a balance weight configured for insertion into a complimentary balance weight slot in the rotating component. The balance weight has a dovetail shaped cross-section and the balance weight slot has a complimentary dovetail shaped cross-section. A retaining ring configured for installation to the rotating component axially retains the balance weight in the balance weight slot. A method of correcting an imbalance of a rotating assembly includes inserting a balance weight into a balance weight slot in a rotating component of the rotating assembly, and installing a retaining ring at the rotating component to retain the balance weight in the balance weight slot in an axial direction. The balance weight has a dovetail shaped cross section, and the balance weight slot has a complimentary dovetail shaped cross section to retain the balance weight at the balance weight slot.

The present application provides a steam turbine system. The steam turbine system may include a rotor, a high pressure section positioned about the rotor, one or more high pressure extraction conduits extending from the high pressure section, a high pressure control valve positioned on each of the high pressure extraction conduits, an intermediate pressure section positioned about the rotor, one or more intermediate pressure extraction conduits extending from the intermediate pressure section, an intermediate pressure control valve positioned on each of the intermediate pressure extraction conduits, and a controller in communication with the high pressure control valves and the intermediate pressure control valves and operable to selectively adjust respective positions of the high pressure control valves and the intermediate pressure control valves to balance thrust acting on the rotor.

A blower (100) includes a blower attachment housing (112), a power head housing (122) having a handle (130) operably coupled thereto, a motor (140) disposed in the power head housing (122), a fan (160) disposed in the blower attachment housing (112), a battery (150), and an intake chamber (174) disposed between the motor (140) and the fan (160) to enable the air to enter the blower (100) between the motor (140) and the fan (160).

A journal bearing for a gas turbine engine is described. The journal extends along a central axis from a first axial end face to a second axial end face thereof, and has at least one undercut defined circumferentially about the central axis in one of the first and second axial end faces. The undercut extends toward the other one of the first and second axial end faces of the journal. A stiffening member extends across the undercut to interconnect opposite surfaces thereof. Also described, a journal bearing comprising a tubular body extending axially along a central axis, where the tubular body has a first and a second opposite axial end faces with holes projecting into the first axial end face toward the second axial end face and having a finite depth. The holes are circumferentially disposed about the central axis, and respective webs of material are defined between adjacent holes. A method of operating a journal bearing is also provided.

There is disclosed a bearing assembly for a gas turbine engine. The bearing assembly has a central axis and includes at least two bearings being axially spaced from one another relative to the central axis and configured to rotatably support a rotating component of the gas turbine engine. A bearing housing includes bearing supports supporting the at least two bearings. The bearing housing is securable to a casing of the gas turbine engine via hairpin structures being axially spaced from one another.

Rotor thrust balancing systems for turbomachines and methods of using the same are generally disclosed. For example, a rotor thrust balancing system for a turbomachine, wherein the turbomachine defines a centerline extending the length of the turbomachine. The system includes a rotating drive shaft, a thrust bearing, and a first waveguide sensor. The rotating drive shaft couples a turbine section and a compressor section of the turbomachine. The thrust bearing supports the rotating drive shaft of the turbomachine. The thrust bearing includes a plurality of ball bearings, an inner race coupled to the rotating drive shaft, and an outer race coupled to a fixed structure. The first waveguide sensor is coupled to the outer race at a first end of the waveguide sensor. The waveguide sensor communicates a vibrational frequency from the thrust bearing to a second end of the waveguide sensor.

A single-unit nose cone for a ram air including: a dome portion located at a forward end of the single unit nose cone; a dome stand portion adjacent to the dome portion; a seat portion adjacent to the dome stand portion; and a stem portion adjacent to the seat portion and located at an aft end of the single-unit nose cone, wherein the dome portion, the dome stand portion, the seat portion, and the stem portion are composed from a single piece of material having a density of about 0.286 pound/cubic inch (7916 kilogram/cubic meter).

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.