Abstract: The present disclosure relates generally to the field of variable geometry guide vanes for gas turbine engines. More specifically, the present disclosure relates to a plastic variable inlet guide vane for a gas turbine engine.

Abstract: A clamp connector includes a first clamping member configured to apply a clamping force to a material, the first clamping member having a first portion including a first and second cam surfaces, a first cammed body adjacent the first cam surface, and a second cammed body adjacent the second cam surface. A second clamping member is configured to apply a clamping force to the material. The second clamping member having a second portion including a third and fourth cam surfaces, a third cammed body adjacent the third cam surface, and a fourth cammed body adjacent the fourth cam surface. When each cam surface is forced against the adjacent cammed body a clamping force between the first clamping member and the second clamping member is increased.

Abstract: The present disclosure relates generally to the field of variable geometry guide vanes for gas turbine engines. More specifically, the present disclosure relates to a plastic variable inlet guide vane for a gas turbine engine.

Abstract: The present disclosure is applicable to all applications where two adjoining portions of material are to be joined together. A clamp connector couples the two adjoining portions of material together such that increased clamping pressure is applied in response to forces attempting to separate the two adjoining portions of material. In an embodiment, two adjoining edges of a metal grid material are joined together in a silencer of a gas turbine engine.

Abstract: A turbine assembly has a casing, a turbine ring and a blade. The blade has a root portion having an axially extending first shape, an airfoil attaching to the root portion and having a trailing edge and a radially outward tip. The tip has a first portion disposed in parallel to the axis of rotation for minimizing escape of air between the tip and the casing and a second portion extending aft from the first portion at an inward angle. The ring has a cut-out having a second shape mating with the first shape.

Abstract: A turbine blade assembly has a turbine blade with a root section and an airfoil section. The root section has one of a radially extending groove or flange, and a retainer element has the other of the groove and the flange. The groove receives the flange to hold the retainer element and the blade together. The retainer element has axial ends extending radially inwardly to secure a turbine blade assembly within a disk slot in a turbine rotor disk. A method is also disclosed.

Abstract: A turbine assembly has a casing, a turbine ring and a blade. The blade has a root portion having an axially extending first shape, an airfoil attaching to the root portion and having a trailing edge and a radially outward tip. The tip has a first portion disposed in parallel to the axis of rotation for minimizing escape of air between the tip and the casing and a second portion extending aft from the first portion at an inward angle. The ring has a cut-out having a second shape mating with the first shape.

Abstract: A turbine blade assembly has a turbine blade with a root section and an airfoil section. The root section has one of a radially extending groove or flange, and a retainer element has the other of the groove and the flange. The groove receives the flange to hold the retainer element and the blade together. The retainer element has axial ends extending radially inwardly to secure a turbine blade assembly within a disk slot in a turbine rotor disk. A method is also disclosed.

Abstract: A method for joining a cast metal material blade ring having therein an initial interior ring passageway formed by a ring interior wall thereabout and a metal material hub structure, having therein a disk part thereof with a disk side configured such that at least a portion of a disk side is positionable against a portion of the ring interior wall so as to be assembleable into an assembled structure for a turbine rotor through mounting one of the blade ring and the hub structure in a holder and also mounting the remaining one of the blade ring and the hub structure in a rotation holder for being rotated by a rotatable portion of that rotation holder.

Abstract: A sealing arrangement improves sealing of a shaft in a control system on a gas turbine engine. The sealing arrangement includes a first plate and a non-metallic plate. The non-metallic plate has a glass transition temperature above an operating temperature range. The non-metallic plate and the first plate are disposed between a high temperature, high pressure fluid and a low pressure fluid.