The present invention provides an apparatus for providing a balancing weight in a groove on a rotor disk in a gas turbine engine. The apparatus comprises an elongate reservoir for housing a hardenable material and an inflatable balloon in fluid communication with the distal end of the elongate reservoir. An actuator is provided for forcing the hardenable material from the elongate reservoir to inflate the inflatable balloon with hardenable material within the groove on the rotor disk. A sealing device for sealing the inflated inflatable element to form the balancing weight is also provided.

A gas turbine engine having a fan and a bypass duct for discharging airflow from the fan to generate engine thrust. The bypass duct includes a first component and a second component each having a gas washed surface, the first component being positioned adjacent the second component with a gap therebetween. A sealing strip is positioned in the gap between the first component and the second component distal to the gas washed surfaces of the first and second components. A sealant is positioned between the first and second component proximal to the gas washed surfaces of the first and second components, so as to seal the gap between the first component and the second component from airflow through the bypass duct.

The device (20) comprises two outer and inner concentric rings (22, 23), one of which is connected to an oil supply from one of the repositories, the other ring being connected to the other repository, the oil flowing between said rings, and bearings between the rings in order to change repositories between the two rings. According to the invention, the device (20) further comprises a flexible means (31) forming a shock absorber, provided between a first of said rings and an intermediate ring (41) that is separated from a second of said rings by said bearings (25), said flexible means (31) defining a deformable sealed chamber (32) in which oil travels between the two repositories.

A fan section for a gas turbine engine is provided. The fan section having a fan hub with a slot and a fan blade with an airfoil extending from a root to a tip, the airfoil having a leading edge and the root is received in the slot, wherein a first platform is secured to the fan hub and arranged between adjacent fan blades of the fan section, the first platform having a first platform seal including a platform seal leading edge and a base is secured to a side of the first platform and a first winglet extends from the platform seal leading edge and contacts the airfoil leading edge.

A fan blade platform is provided. The fan blade platform may include a wall, a first sidewall extending from the flowpath to a circular member, and a second sidewall extending from the flowpath to the circular member. A stiffening member may also extend from the circular member to the flowpath and be formed integrally with the first sidewall, the second sidewall, and the flowpath.

A stator assembly for a stator of a gas turbine engine is provided. The stator assembly having: a shroud defining a cavity; a plurality of inserts located within the cavity, each of the plurality of inserts defining a cavity; a plurality of vanes secured to the shroud, wherein each of the plurality of vanes has a tab portion located in the cavity of the shroud; and a rubber material disposed in the cavity of the shroud, the rubber material securing the tab portion of each of the plurality of vanes to the shroud.

A method of making a rub strip includes resin transfer molding an arcuate composite structure. The resin transfer molding step includes inserting a honeycomb core into a mold cavity having an arcuate base so that the honeycomb core assumes an arcuate shape. The resin transfer molding step further includes directing liquid resin into the mold cavity to form the composite structure comprising the liquid resin and the honeycomb core, and curing the liquid resin for a sufficient period of time. The resin transfer molding step further includes removing the composite structure from the mold. The method further includes repeating the resin transfer molding step until a sufficient number of arcuate composite structures are produced. The method further includes coupling a plurality of the arcuate composite structures together to form the rub strip.

A stator assembly for a gas turbine engine includes an arcuate shroud including a shroud pocket, the shroud pocket having a shroud slot extending therethrough. A stator vane is insertable into the shroud pocket and includes a vane slot extending therethrough. A strap extends through the shroud slot and the vane slot to retain the vane to the shroud. A gas turbine engine includes a combustor and a stator and case assembly in in fluid communication with the combustor. The stator and case assembly includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly secured at the case.

A repair process includes providing a gas turbine engine article that has an elastomeric coating that has an eroded region, plasma etching the elastomeric coating in the eroded region, and applying an elastomeric repair coating on the eroded region.

A sealing structure seals a space between first and second parts of a fan duct and a fairing of an aircraft engine. The sealing structure comprises first and second seal portions for positioning between the first and second parts of the fan duct and the fairing. The first seal portion includes an elongated middle region and a first coupling mechanism. The elongated middle region can be secured to the first part of the fan duct and abutting the fairing and includes a forward end from which the first coupling mechanism extends. The second seal portion includes an elongated middle region and a second coupling mechanism. The elongated middle region can be secured to the second part of the fan duct and abutting the fairing and includes a forward end from which the second coupling mechanism extends. The second coupling mechanism is operable to couple to the first coupling mechanism.