Siemens Energy, Inc.

Paul J Gear

Brian J Wessell

Allister William James

Daniel M Eshak

Anand A Kulkarni

Christian X Campbell

John Joseph Marra

Jan H Marsh

Christian X Campbell, Jr

Alamgir T Islam

A vane assembly () having: an airfoil () and a shroud () held together without metallurgical bonding there between; a channel () disposed circumferentially about the airfoil (), between the airfoil () and the shroud (); and a seal () disposed in the channel (), wherein during operation of a turbine engine having the vane assembly () the seal () has a sufficient ductility such that a force generated on the seal () resulting from relative movement of the airfoil () and the shroud () is sufficient to plastically deform the seal ().

Ductile alloys for sealing modular component interfaces

Bi-casting a platform () onto an end portion () of a turbine airfoil () after forming a coating of a fugitive material () on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (A,B) onto the end portion in opposite directions parallel to a chord line () of the airfoil or parallel to a mid-platform length () of the platform to form respective layers tapering in thickness from the leading () and trailing () edges along the suction side () of the airfoil.

Turbine airfoil to shroud attachment method

A vane structure for a gas turbine engine. The vane structure includes a radially outer platform and a radially inner platform, and an airfoil having an outer wall extending radially between the outer platform and the inner platform. A cooling passage is defined within the outer wall and has a plurality of radially extending channels. An outer end turn structure is located at the outer platform to conduct cooling fluid in a chordal direction between at least two of the channels. The outer end turn structure includes an enlarged portion wherein the enlarged portion is defined by an enlarged dimension, in a direction transverse to the chordal direction, between the at least two channels.

Gas turbine vane with cooling channel end turn structure

A turbine vane for a turbine machine comprising an intermediate section having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial distance along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z.

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Longwood, FL, United States of America

Paul J Gear