TURBINE SHROUD WITH AXIALLY SEPARATED PRESSURE COMPARTMENTS

摘要

A turbine shroud for a gas turbine engine includes an annular metallic carrier and a blade track. One or more cavities are formed between the carrier and blade track to provide cooling air to the blade track.

主权项

1. A turbine shroud for use in a gas turbine engine, the turbine shroud comprising
a carrier comprising metallic materials and adapted to be coupled to a turbine case, a blade track comprising ceramic-matrix composite materials and coupled to the carrier, the blade track extending at least a portion of the way around a central axis so that the blade track is adapted to block hot gasses from passing over a turbine wheel surrounded by the turbine shroud, and at least one bulkhead that radially interconnects the carrier and the blade track to divide a space between the carrier and the runner into at least a first cooling-air cavity and a second cooling-air cavity, the at least one bulkhead formed to include a plurality of pressure-control holes sized to cause the first cooling-air cavity to have a first pressure and the second cooling-air cavity to have a second pressure, lower than the first pressure.