Multi-piece turbine vane assembly

A modular vane assembly comprising:

• a radially inner shroud;
• a radially outer shroud;
• an airfoil formed by at least two airfoil segments including at least a forward airfoil segment and an aft airfoil segment, the forward airfoil segment defining the leading edge of the airfoil assembly, the aft airfoil segment defining the trailing edge of the airfoil assembly, the airfoil having a radial inner end and a radially outer end, the airfoil including an outer peripheral surface defining a leading edge and a trailing edge, wherein at least one of the inner shroud, the outer shroud and the airfoil is a separate part;
• and
• a fastener extending substantially radially through the at least one airfoil segment and into engagement with the inner and outer shrouds, wherein the airfoil is secured between the inner and outer shrouds,
• wherein each airfoil segment includes an interface surface, wherein the airfoil segments are positioned such that interface surfaces are substantially proximate to each other so as to define a gap therebetween, and further comprising a seal placed within the gap, whereby flow migration through the gap is substantially minimized.

A modular vane assembly comprising:

• a radially inner shroud;
• a radially outer shroud;
• an airfoil formed by at least two airfoil segments including at least a forward airfoil segment and an aft airfoil segment, the forward airfoil segment defining the leading edge of the airfoil assembly, the aft airfoil segment defining the trailing edge of the airfoil assembly, the airfoil having a radial inner end and a radially outer end, the airfoil including an outer peripheral surface defining a leading edge and a trailing edge, wherein at least one of the inner shroud, the outer shroud and the airfoil is a separate part;
• and
• a fastener extending substantially radially through the at least one airfoil segment and into engagement with the inner and outer shrouds, wherein the airfoil is secured between the inner and outer shrouds,
• wherein each airfoil segment includes an interface surface, wherein the airfoil segments are positioned such that interface surfaces are substantially proximate to each other so as to define a gap therebetween, wherein the interface surfaces of the airfoil segments are substantially correspondingly stepped, whereby a tortuous flow path through the gap is formed.

A modular vane assembly comprising:

• a radially inner shroud;
• outer shroud;
• an airfoil formed by at least two airfoil segments including at least a forward airfoil segment and an aft airfoil segment, the forward airfoil segment defining the leading edge of the airfoil assembly, the aft airfoil segment defining the trailing edge of the airfoil assembly, the airfoil having a radial inner end and a radially outer end, the airfoil including an outer peripheral surface defining a leading edge and a trailing edge, wherein at least one of the inner shroud, the outer shroud and the airfoil is a separate part;
• and
• a fastener extending substantially radially through the at least one airfoil segment and into engagement with the inner and outer shrouds, wherein the airfoil is secured between the inner and outer shrouds,
• wherein each airfoil segment includes an interface surface, wherein the airfoil segments are positioned such tat interface surfaces are substantially proximate to each other so as to define a gap therebetween, wherein the substantially proximate airfoil segments define a radial seam, wherein the airfoil segments are welded along the radial seam, whereby flow ingress into the gap is substantially impeded.

A vane assembly comprising:

• a radially inner shroud;
• a radially outer shroud;
• and
• an airfoil having a radially inner end and a radially outer end, the airfoil being formed by at least an arcuate forward airfoil segment and a second airfoil segment, the forward airfoil segment defining the leading edge of the airfoil, wherein the forward airfoil segment is positioned substantially proximate to and attached to the second airfoil segment, wherein the airfoil is secured between the radially outer shroud and the radially inner shroud,
• wherein each of the inner and outer shrouds includes a recess shaped to receive the respective radial ends of the airfoil, wherein the radial ends of the airfoil are received within the recesses, wherein a fastener extends though the second segment and engages the shrouds, and further including a retainer and a fastener, wherein at least one end of the fastener is closed with the retainer and the radial spring is disposed between the retainer and one of the shrouds.