Abstract: A turbine engine vane arrangement and a method for manufacturing a turbine engine vane arrangement are provided. The vane arrangement includes a plurality of vane arrangement segments arranged circumferentially around an axial centerline. Each of the vane arrangement segments includes an airfoil that extends radially between a first platform segment and a second platform segment. The first platform segment extends circumferentially between a first mate face and a second mate face. The first mate face of a first of the vane arrangement segments is bonded to the second mate face of a second of the vane arrangement segments.

Abstract: A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.

Abstract: A turbine engine vane arrangement and a method for manufacturing a turbine engine vane arrangement are provided. The vane arrangement includes a plurality of vane arrangement segments arranged circumferentially around an axial centerline. Each of the vane arrangement segments includes an airfoil that extends radially between a first platform segment and a second platform segment. The first platform segment extends circumferentially between a first mate face and a second mate face. The first mate face of a first of the vane arrangement segments is bonded to the second mate face of a second of the vane arrangement segments.

Abstract: A mid-turbine frame (MTF) system for a gas turbine engine is disclosed. The MTF includes an inner case, an outer case and a fairing sandwiched between the inner and outer cases. The fairing includes an inner ring spaced apart from and coupled to an outer ring by a plurality of hollow struts. The hollow struts accommodate support rods that connect the inner case to the outer case. Further, the hollow struts act as turning vanes for turning the flow of gases passing from a high pressure turbine (HPT) to a low pressure turbine (LPT) for purposes of providing the correct incidence angle to the first vane of the LPT. The outer ring of the fairing includes a plurality of bosses which receive attachment pins that pass through the outer case for correctly locating the fairing with respect to the outer case and for permitting radial expansion in contraction of the fairing.

Abstract: A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis.

Abstract: A seal land for a gas turbine engine can include a seal body that can extend between a leading edge portion, a trailing edge portion, a radially outer surface and a radially inner surface. A notch can extend at least partially through the seal body between the radially outer surface and the radially inner surface.

Abstract: A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.

Abstract: An assembly for connecting a coverplate and a rotor includes a first rotor for use in a rotating engine; a first cover mounted to the first rotor, wherein the rotor and the cover create a space there between, the space for having cooling air therein; and a lock assembly for preventing the cover from rotating circumferentially or moving axially away from the rotor if mounted to the to the rotor wherein the cover is sealed against the rotor.

Abstract: A static structure of a gas turbine engine includes a multiple of airfoil segments and at least one structural reinforcement ring mounted to the multiple of airfoil segments.

Abstract: A turbine engine vane arrangement and a method for manufacturing a turbine engine vane arrangement are provided. The vane arrangement includes a plurality of vane arrangement segments arranged circumferentially around an axial centerline. Each of the vane arrangement segments includes an airfoil that extends radially between a first platform segment and a second platform segment. The first platform segment extends circumferentially between a first mate face and a second mate face. The first mate face of a first of the vane arrangement segments is bonded to the second mate face of a second of the vane arrangement segments.

Abstract: A mid-turbine frame (MTF) system for a gas turbine engine is disclosed. The MTF includes an inner case, an outer case and a fairing sandwiched between the inner and outer cases. The fairing includes an inner ring spaced apart from and coupled to an outer ring by a plurality of hollow struts. The hollow struts accommodate support rods that connect the inner case to the outer case. Further, the hollow struts act as turning vanes for turning the flow of gases passing from a high pressure turbine (HPT) to a low pressure turbine (LPT) for purposes of providing the correct incidence angle to the first vane of the LPT. The outer ring of the fairing includes a plurality of bosses which receive attachment pins that pass through the outer case for correctly locating the fairing with respect to the outer case and for permitting radial expansion in contraction of the fairing.

Abstract: An assembly for dampening vibration movement between a cylinder and a concentric duct, where the cylinder is positioned radially inside the duct, includes a damper attached to the duct. The damper includes a housing attached to the duct, a contact member positioned at least partially inside the housing and having a contact surface adjacent an outer surface of the cylinder, and a cap threadedly engaged with the housing for applying a load on the contact member in a direction toward the cylinder.

Abstract: An assembly for connecting a coverplate and a rotor includes a first rotor for use in a rotating engine; a first cover mounted to the first rotor, wherein the rotor and the cover create a space there between, the space for having cooling air therein; and a lock assembly for preventing the cover from rotating circumferentially or moving axially away from the rotor if mounted to the to the rotor wherein the cover is sealed against the rotor.

Abstract: A seal land for a gas turbine engine can include a seal body that can extend between a leading edge portion, a trailing edge portion, a radially outer surface and a radially inner surface. A notch can extend at least partially through the seal body between the radially outer surface and the radially inner surface.

Abstract: A seal land for a gas turbine engine can include a seal body circumferentially extending about a longitudinal centerline axis. The seal body includes at least one sealing surface that extends in a plane that is transverse to the longitudinal centerline axis.

Abstract: A static structure of a gas turbine engine includes a multiple of airfoil segments and at least one structural reinforcement ring mounted to the multiple of airfoil segments.

Abstract: An example turbomachine load management assembly includes a support rod extending from a first rod end to a second rod end that is moveable radially relative to a fan duct, a bearing housing, or both, when the support rod is coupling the fan duct and the bearing housing.

Abstract: An assembly for dampening vibration movement between a cylinder and a concentric duct, where the cylinder is positioned radially inside the duct, includes a damper attached to the duct. The damper includes a housing attached to the duct, a contact member positioned at least partially inside the housing and having a contact surface adjacent an outer surface of the cylinder, and a cap threadedly engaged with the housing for applying a load on the contact member in a direction toward the cylinder.