Abstract: The invention is a method for allocating shroud or airseal segments among various positions in a turbomachinery case when the segments to be allocated differ in radial dimension or thickness and when the requirement for segment thickness varies around the circumference of the case. According to the inventive method, segment thicknesses are preliminarily assigned to positions on the case without regard for whether or not the thickness of each assigned segment satisfies the thickness requirement of its assigned position. Each thickness is then compared to the requirement of its assigned position and thicknesses that fail to satisfy the minimum thickness requirement of their assigned positions are consigned to a pool of noncompliant thickness values, thereby vacating zero or more positions Members of the pool are then systematically evaluated for suitability in the vacated positions.

Abstract: A method for forming a stator assembly 28 of a rotary machine 10 which includes masking the stator assembly during a machining operation on a seal member 70 is disclosed. Various detailed steps of the method are disclosed which decrease the cost of the method. In one embodiment of the method, the method includes disposing a shield assembly 98 about the stator assembly 28 to such an extent that individual members of the stator assembly need not be disassembled for cleaning.

Abstract: A shield assembly 98 is disclosed which has one or more shield elements 102, 104, 106 which block, during machining of a seal member 70 for a rotary machine 10, seal particles from entering a vane cluster 58. Various construction details are developed which increase the effectiveness of the shield assembly. In one embodiment, the shield assembly has an upper shield element 102 having a U-shaped cross sectional shape which fits over a stator assembly 28 that includes the seal member.

Abstract: The invention is a method for repairing a protectively coated, locally damaged turbomachinery vane without removing the vane from its parent turbomachinery module. The method includes applying a diffusible coating precursor to the damaged region of the vane and diffusing the coating precursor into the vane in the presence of a nonreactive atmosphere. The nonreactive atmosphere is confined to a chamber that contains the damaged vane, the chamber being bounded in part by the turbomachinery module itself. A conventional stress relief machine is used to heat only the damaged region of the vane to a temperature sufficient to promote diffusion of the precursor into the vane. The method uses equipment and supplies that are routinely available or easily fabricated from common, inexpensive materials. Use of the method avoids the expense and delay of removing the vane from its parent module.