Siemens Energy, Inc.

Gennadiy Afanasiev

Ronald J Rudolph

Robert W Sunshine

Dieter Brillert

John N Strain

Robert D Barker

Jeffrey B Stewart

A turbine engine vane assembly assembled using an anti-rotation pin method can include a vane assembly having a vane supported on a shroud ring and a cavity seal coupled to the vane assembly by a securement mechanism. The cavity seal defines a securement receiving portion through which the securement mechanism is inserted. The securement receiving portion also includes a deformation receiver. The securement mechanism has a deformable rim at a first end and a key at a second end. The securement mechanism is rotatable between a first configuration and a second configuration where the key matingly engages the shroud ring and the cavity seal to reduce axial movement of the vane assembly. The deformable rim can be deformed into the deformation receiver to prevent rotation of the securement mechanism and disengagement of the securement mechanism from the vane assembly and cavity seal.

Anti-rotation pin retention system

A turbine section having a plurality flow path components forming a plurality of guide vane rings and ring segments arranged in axial succession to define a boundary of a hot gas duct. A vane carrier located around the gas duct, and sealing elements extend radially between circumferentially extending grooves in the vane carrier and respective grooves in the flow path components. The sealing elements include radially inner and outer edges, and at least one axially facing side defining a chamfered portion extending to one of the edges to accommodate axial movement of the sealing element about the one edge within a respective groove.

Gas turbine engine sealing structure

A seal assembly for an axial flow gas turbine engine includes a rotatable component having a radially extending mate face, a seal slot formed in the mate face, and a seal member slidably disposed in the seal slot. The seal slot includes a radially outer wall and an opposing radially inner wall extending into the component in a circumferential direction from the mate face. The radially outer wall is angled radially inwardly from the mate face toward an inner end portion of the seal slot. Rotation of the seal assembly during operation of the engine produces a centrifugal force on the seal member to effect movement of the seal member in the circumferential direction out of the seal slot.

Turbine blade seal assembly

A cooling fluid metering system for a turbine blade of a gas turbine engine is disclosed. The cooling fluid metering system may include a cooling channel positioned between a root of a turbine blade and an offset rotor sealing plate for supplying cooling fluids to turbine blades. At one point, a portion of the cooling channel may include a gap between the root and the offset rotor sealing plate. The gap may be sealed with teardrop shaped seal positioned within a teardrop shaped cavity at the gap. The cavity and seal may be positioned such that during operation, the seal is forced radially outward and into the gap, thereby effectively metering cooling fluid flow through the cooling channel.

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Windermere, FL, United States of America

Gennadiy Afanasiev