Abstract: The invention is a turbomachinery module (10) whose forwardmost vanes, which are the most damage susceptible vanes in the module, are easily removable and replaceable without substantial disassembly of the module. The module includes a case (12) and a forwardmost array (1V) of vanes. Each vane (34) of the forwardmost array has an axially proximal and distal end (90, 92) relative to the forward end (16) of the case. The distal end of each vane has a foot (102) that abuts but is not connected to a vane guide (32) on the case. The proximal end of each vane has an attachment bracket (110) that can be secured to or disengaged from a vane support (28) on the case. Vane removal is accomplished by disengaging the attachment bracket (110) from the vane support (28) and withdrawing the vane through the forward end of the case. The invention improves upon conventional turbine modules in which the forwardmost vane array is removable only from the aft end of the case after the module has been substantially disassembled.

Abstract: A ceramic turbine inlet vane(s) is resiliently mounted to stator portions (10) and (15) of a gas turbine engine by outer and inner resilient mounts (20) and (25). The resilient mounts each include springs, which accommodate varying rates of radial and axial thermal expansion between the vane and adjacent metallic stator structure.