| 摘要 |
A turbine section of a gas turbine engine includes first and second rotor stages connected by an arm. The first rotor stage has a first set of blades connected to a first rotor disk at a first blade attachment. The second rotor stage has a second set of blades connected to a second rotor disk at a second blade attachment. A cover plate extends from a downstream side of the first blade attachment to an upstream side of the second blade attachment. The cover plate is spaced from the arm so as to define a flow path from the first blade attachment to the second blade attachment.
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