A method for installing a gas turbine assembly of a first type at a position of an existing power plant where previously a gas turbine assembly of a second type was installed on a foundation specially designed for said second type. The gas turbine assembly includes at least one housing, a compressor, a combustion chamber, a gas turbine, and a plurality of venting and removal lines guided along the exterior of the housing. Modifications to the venting and/or removal lines of the gas turbine assembly of the first type are carried out in a first step, and the modified gas turbine assembly is installed on the existing foundation in a second step.

A foundation temperature control system for use with a rotary machine is positioned between the rotary machine and a foundation. The foundation temperature control system includes a heat shield, an insulation pack positioned below the heat shield, and an air gap at least partially defined by the heat shield and the insulation pack. The heat shield, the insulation pack, and the air gap are oriented to facilitate maintaining a temperature of the foundation supporting the rotary machine below a maximum rated operating temperature of the foundation.

An air supply device, a gas turbine system and a using method thereof are disclosed. In the air supply device, an air intake compartment includes a connection end; a combustion air intake filter is located in the air intake compartment and connected with the combustion air intake filter; a combustion air intake interface is located on a tail plate and is connected with the combustion air silencer; and a sound insulation turnover mechanism includes a sound insulation flap and a turnover mechanism, the air intake compartment includes a first bottom plate and the tail plate that is located at the connection end, the sound insulation flap is located at the connection end, and the turnover mechanism is connected with the sound insulation flap, and is configured to drive the sound insulation flap to rotate relative to the tail plate.

A method for installing a compressor and a gas turbine of a first type at a position of an existing power plant where previously a compressor and a gas turbine of a second type were installed on a foundation specially designed for the second type. The two types differ from each other at least with respect to the position and/or the number of anchoring points at which the compressor and the gas turbine are connected to the foundation via support structures. The installation of the new compressor and the new gas turbine is carried out using an adapter structure on the existing foundation. A corresponding adapter structure is provided.

An apparatus is provided for an aircraft propulsion system. This apparatus includes an acoustic panel and a mount. The acoustic panel includes a perforated face skin, a back skin, a perforated intermediate layer, a first cellular core and a second cellular core. The first cellular core includes a first section and a second section. The first section is between and is connected to the perforated face skin and the perforated intermediate layer. The second section is between and is connected to the perforated face skin and the back skin. The second cellular core is between and is connected to the perforated intermediate layer and the back skin. The mount is attached to the back skin along the second section.

A turbofan engine includes an outer bypass duct and a gas turbine engine having an outer casing. The gas turbine engine is disposed in the outer bypass duct such that a bypass airflow passage is formed between the outer casing of the gas turbine engine and the outer bypass duct. The turbofan engine includes a turbine rear frame link assembly including a set of links coupled between the outer bypass duct and the outer casing to support the gas turbine engine relative to the outer bypass duct. The links are arranged around the gas turbine engine on a plane that is perpendicular to a centerline axis of the turbofan engine. None of the links extends through the bypass airflow passage at a position that intersects a radius extending in a vertically downward direction from the centerline axis.

An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.

A system and method that uses one or more jet engines to remove unmanned aircraft from restricted airspace. Generally, the force created by a jet engine can be used to remove drones or other unwanted objects from the restricted airspace. Once the system determines the presence of an unauthorized aircraft or object within the restricted airspace, the jet engine(s) can be activated and used to pull the drone or flying object towards the jet engine though the force created by the intake of the jet engine(s), or to expel the drone or object from the restricted area through the force created by the exhaust of the jet engine(s).

A tube spacing and fastening system for a gas turbine engine includes a plurality of tubular structures, a wear sleeve, a spacer element, and a fastening element. The plurality of tubular structures provides a fluid flow to a component of the gas turbine engine. The wear sleeve is located around each of the plurality of tubular structures. The spacer element receives the plurality of tubular structures. The fastening element extends around the wear sleeves and is configured to secure the plurality of tubular structures to the spacer element. An interference between the fastening element and wear sleeves is configured to allow the fastening element to slide with respect to the wear sleeves and to provide a damping effect under gas turbine engine vibrations and operating conditions. A method of damping vibrations in the plurality of tubular structures includes allowing the fastening element to slide with respect to the wear sleeve.

Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.