A method for separating a first mechanical part from a second mechanical part is described, wherein the second mechanical part is bonded to the first mechanical part by an adhesive film along a connecting area, the first mechanical part having a first specific thermal conductivity and the second mechanical part having a second thermal conductivity that is higher than the first thermal conductivity. The method includes at least one cooling step during which the second mechanical part is cooled to a negative temperature and at least one stressing step during which the second mechanical part is subjected to mechanical stress in order to cause the adhesive film to break.

An apparatus for removing or installing a turbine blade from a turbine of a turbomachine is disclosed. The apparatus can include: an operative head configured to engage an axial sidewall of a turbine blade base. An actuator is configured to move the operative head to selectively engage the axial sidewall of the turbine blade base and impart an axial force against the turbine blade base to remove or install the turbine blade. A support gantry is configured to position the actuator substantially vertically above the turbine blade in position in the turbomachine. Among other advantages, the support gantry allows adjustment of the apparatus for different turbines, and use of the head on more than one stage of any given turbine.

A method for restoring a blade or vane platform of a gas turbine assembly configured for a power plant by: providing a blade or a vane having a platform with an edge deterioration zone; removing the deterioration zone by electro discharging machining technology; and rebuilding a removed zone by additive manufacturing technology. The removing can be performed to create a recessed plane along a platform edge, the recessed plane being connected to a platform plane by an enter inclined plane and an exit inclined plane arranged opposed along the platform edge.

A method of servicing a gas turbine engine is disclosed. According to the method, a component including a titanium alloy is removed from the gas turbine engine after operating the gas turbine engine with the component in service. The removed component is subjected to heat treatment, and the heat-treated component is re-installed into the gas turbine engine or installed into a different gas turbine engine.

A method of servicing equipment, the method comprising: recording information associated with servicing of the equipment in view of a workscope at a first location; sending the recorded information to a node; receiving service input from a third party located at a second location different from the first location, the third party having prepared the service input in response to the recorded information on the node; and performing the service using the received service input.

A motor assembly comprises a stator, a rotor configured to be rotated about a shaft by electromagnetically interacting with the stator, an impeller configured to be rotated with the rotor about the shaft by being coupled to the rotor and configured to suction air in response to a rotation, a housing configured to cover between the impeller and the stator by being coupled to the stator, a cover comprising an inlet through which air sucked by the impeller is introduced, and configured to cover the impeller, a guide member configured to guide the air discharged from the impeller and configured to be coupled to the housing, and a plurality of first vanes protruding from one of the cover and the guide member to an axial direction and coupled to the other of the cover and the guide member. The cover and the guide member are configured to be movable in the axial direction in response to not being coupled to the housing, and the cover comprises a contact portion in contact with the impeller according to a position of the cover. The contact portion is spaced apart from the impeller in response to coupling between the guide member and the housing.

A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.

A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.

A multi-piece part includes multiple pieces fabricated via different types of fabrication processes, wherein the multiple parts are configured to be coupled to one another to form the assembly. At least one of the multiple parts is fabricated via an additive manufacturing method. The multi-piece part also includes a holder assembly that couples and holds together the multiple pieces of the multi-piece part, wherein the holder assembly comprises a reversible, mechanical-type coupling.

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 1.01-1.15 inch (25.7-29.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.54-0.66 inch (13.6-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2033 ± 15% Hz, a second mode with a frequency of 7023 ± 15% Hz, a third mode with a frequency of 12082 ± 15% Hz and a fourth mode with a frequency of 19769 ± 15% Hz.