Gas turbine engines with abradable turbine seal assemblies

摘要

A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.

主权项

1. A turbine section of a gas turbine engine, comprising:
a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow; a rotor assembly including a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path; a first stator assembly positioned adjacent to the rotor assembly on a downstream side and forming a first turbine disk cavity with the rotor disk of the rotor assembly, the first stator assembly including a first stator platform with a first stator vane that extends from the first stator platform into the mainstream hot gas flow path; a second stator assembly positioned adjacent to the rotor assembly on an upstream side and forming a second turbine disk cavity with the rotor disk of the rotor assembly, the second stator assembly including a second stator platform with a second stator vane that extends from the second stator platform into the mainstream hot gas flow path; and a seal assembly comprising
a first flow discourager extending in a downstream direction from the rotor platform,a second flow discourager extending in an upstream direction from the first stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction,a first hard coating applied to the first flow discourager,a first abradable coating applied to the second flow discourager,a third flow discourager extending in the upstream direction from the rotor platform,a fourth flow discourager extending in the downstream direction from the second stator platform, the fourth flow discourager axially overlapping the third flow discourager such that the third flow discourager is interior to the fourth flow discourager in the radial direction,a second hard coating applied to the fourth flow discourager, anda second abradable coating applied to the third flow discourager.