Patent ID: 9068469
Filing Date: 2015-06-30
Classification: F01D,F05D,Y02T,Y10T

Abstract:
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