A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

In this method for mounting a combustor component, a component hanging step for attaching a string material to a hanging jig mounted on a combustor component and hanging the combustor component with the string material together with the hanging jig, and a component mounting step for mounting a mounting flange of the combustor component at a combustor mounting position of a gas turbine casing are executed. The hanging jig has a hanging tool having a portion which becomes a suspension point contacted by the string material when the string material is attached and hanging the combustor component. The suspension point is positioned on the distal end side of the center of gravity of the combustor component in the combustor axial line direction when the hanging jig has been mounted to the mounting flange.

A component according to the disclosure may include a body having an aperture therein for receiving one of a turbomachine shaft or a lathe chuck, wherein in response to the body being coupled to the lathe chuck, the aperture is oriented substantially axially relative to an axis of rotation of the body with the lathe chuck; and a flange coupled to and in direct axial contact with the body, the flange including a surface that extends axially relative to the axis of rotation of the body, wherein the surface of the flange comprises a matingly engageable face configured to contact an axially aligned surface during operation of the component and having a sanding indentation thereon, wherein a surface roughness of the surface of the flange is less than a surface roughness of a remainder of the component.

A gas turbine engine maintenance stand for a gas turbine engine that comprises modules including an engine core module that houses a high pressure compressor and a turbine module that houses a low pressure turbine. The gas turbine engine maintenance stand has a pair of base beams, each base beam having a first end, a midsection and a second end. The stand has an engine core module support that straddles the pair of base beams at their midsection, the engine core module support having engine core module support arms that are configured to engage opposing sides of the engine core module of the gas turbine engine. The stand also has a turbine module support that straddles the pair of beams adjacent their second ends, the turbine module support having turbine module support arms that are configured to engage opposing sides of the turbine module of the gas turbine engine. The gas turbine engine maintenance stand is useful for disassembling and reassembling modules of a gas turbine engine in order to maintain the gas turbine engine for safety and performance purposes.

A component which is configured to be joined to a further component in a preselected relative orientation is disclosed. The further component has an interface surface and the component is configured to contact the interface surface when joined to the further component. The component includes a surface disposed on a side of the component intended to face the interface surface when the components are joined, a plurality of recesses formed in the surface, and a plurality of spacer elements. Each recess has a preselected orientation relative to the component, the preselected orientation being selected in dependence on the preselected relative orientation. Each spacer element comprises a contact surface configured to contact the interface surface when the components are joined. Each spacer element is disposed in one of the recesses such that the orientation of a given contact surface is defined by the orientation of the corresponding recess.

A method for modifying an existing single shaft combined cycle power plant having a steam turbine part and a gas turbine part which are connected to each other rigidly by an intermediate shaft. The gas turbine part is supported by two pin-ended supports allowing a certain axial displacement of the casing by rotating about corresponding axes. The old gas turbine part is replaced by a new gas turbine part having a different structure, namely a rigid support and a flexible support. Relative thermal expansion or displacement of the intermediate shaft is compensated by a hydraulic unit comprising a double-acting piston for displacing the gas turbine rotor with respect to the gas turbine stator. The hydraulic unit is controlled based on a displacement measurement in the steam turbine.

A method for modifying an existing single shaft combined cycle power plant having a steam turbine part and a gas turbine part which are connected to each other rigidly by an intermediate shaft. The gas turbine part is supported by two pin-ended supports allowing a certain axial displacement of the casing by rotating about corresponding axes. The old gas turbine part is replaced by a new gas turbine part having a different structure, namely a rigid support and a flexible support. Relative thermal expansion or displacement of the intermediate shaft is compensated by a hydraulic unit comprising a double-acting piston for displacing the gas turbine rotor with respect to the gas turbine stator. The hydraulic unit is controlled based on a displacement measurement in the steam turbine.

A method and system for aligning a component within a turbine casing, and a related turbine casing. In a top-on position, a location of an optical target and another, vertically spaced optical target on the joint flange are measured. After removing at least the upper casing, the optical targets' locations are measured again, and the locations of a pair of reference points on an upper surface of the horizontal joint flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a horizontal joint flange surface distortion adjustment. Support position is adjusted by the prediction offset value to improve alignment.

A method and system for aligning a component within a turbine casing, and a related turbine casing. In a top-on position, a location of an optical target and another, vertically spaced optical target on the joint flange are measured. After removing at least the upper casing, the optical targets' locations are measured again, and the locations of a pair of reference points on an upper surface of the horizontal joint flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a horizontal joint flange surface distortion adjustment. Support position is adjusted by the prediction offset value to improve alignment.