| 摘要 |
A turbine section (50) of a gas turbine engine (10) includes first and second rotor stages (54A,54B) connected by an arm (68A). The first rotor stage (54A) has a first set of blades (56A) connected to a first rotor disk (58A) at a first blade attachment (60A). The second rotor stage (54B) has a second set of blades (56B) connected to a second rotor disk (58B) at a second blade attachment (60B). A cover plate (80A) extends from a downstream side of the first blade attachment (60A) to an upstream side of the second blade attachment (60B). The cover plate (80A) is spaced from the arm (68A) so as to define a flow path (94A) from the first blade attachment (60A) to the second blade attachment (60B). |
