LOW THERMAL STRESS CERAMIC TURBINE NOZZLE

摘要

A turbine nozzle vane assembly (70) having a preestablished rate of thermal expansion is positioned in a gas turbine engine (10) and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly (70). The turbine nozzle vane assembly (70) includes an outer shroud (72) and an inner shroud (78) having a plurality of vanes (88) therebetween. Each of the plurality of vanes (88) have a device for heating (250) and cooling (252) a portion of each of the plurality of vanes (88). Furthermore, the inner shroud (78) has a plurality of bosses (120) attached thereto. A cylindrical member (124) has a plurality of grooves (137) formed therein and each of the plurality of bosses (120) are positioned in correpsonding ones of the plurality of grooves (137). The turbine nozzle vane assembly (70) provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being greater than the preestablshed rate of thermal expansion of the other component.