Turbine shroud with forward case and full hoop blade track
AssigneeRolls-Royce North American Technologies Inc.
InventorsEdward C. Rice, Daniel K. Vetters
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.
Claims20
A turbine shroud assembly for a gas turbine engine, the turbine shroud assembly comprising
- an annular turbine case arranged around a central axis of the turbine shroud assembly,
- a full hoop blade track comprising ceramic matrix composite materials located radially between the turbine case and the central axis, the blade track having a leading edge and a trailing edge axially spaced apart from the leading edge, and
- a forward case coupled to the turbine case and arranged to extend radially inwardly away from the turbine case toward the central axis and interlocked with the leading edge of the blade track to block circumferential and axial movement of the blade track relative to the turbine case while allowing radial movement of the blade track relative to the turbine case.
A turbine assembly for a gas turbine engine, the turbine assembly comprising
- an annular turbine case arranged around a central axis of the turbine assembly,
- a blade track located radially between the turbine case and the central axis, the blade track having a leading edge and a trailing edge axially spaced apart from the leading edge,
- a vane assembly located radially between the turbine case and the central axis and located axially aft of the blade track, the vane assembly arranged to engage the trailing edge of the blade track to block axially aft movement of the blade track relative to the turbine case, and
- a forward case coupled to the turbine case and arranged to interlock with the leading edge of the blade track to block circumferential and forward axial movement of the blade track relative to the turbine case while allowing radial movement of the blade track relative to the central axis.
A method of assembling a turbine assembly for use in a gas turbine engine, the method comprising
- providing an annular turbine case arranged around a central axis of the turbine case, a full hoop blade track having a leading edge and a trailing edge axially spaced apart from the leading edge, and a forward case having an axially extending axial runner and a radially inwardly extending locator flange,
- fastening the axial runner of the forward case to the turbine case, and
- interlocking the leading edge of a blade track with the locator flange of the forward case.
Dependencies are inferred from the claim text.