Turbine shroud with axially separated pressure compartments

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 retainer comprising metallic materials and adapted to be coupled to the turbine case, the retainer being coupled to the carrier,
• a blade track comprising ceramic-matrix composite materials and extending around a central axis so that the blade track is adapted to block hot gasses from passing over a turbine wheel, the blade track positioned to engage with the carrier and retainer to maintain alignment of the blade track with the turbine wheel, 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,
• wherein the at least one bulkhead is configured to provide means for creating a pressure differential between subsequent cooling-air cavities such that the each subsequent cooling-air cavity has a pressure lower than the upstream cooling-air cavity.

A method of assembling a turbine shroud for use in a gas turbine engine, the method comprising

• engaging a forward hanger of a blade track with a forward bracket of a carrier,
• engaging a runner of the blade track with a bulkhead of the carrier, the runner being coupled to the forward hanger, and
• engaging an aft bracket of a retainer with an aft hanger coupled to the runner of the blade track,
• wherein the bulkhead divides a spaced defined by the carrier, blade track, and retainer into an axially forward first cavity and an axially aft second cavity, the first and second cavities being in fluid communication with one another by a plurality of pressure-control holes formed through the bulkhead and sized to cause the first cavity to have a first pressure and the second cavity to have a second pressure, lower than the first pressure.