Patent ID: 11098605

Abstract:
A seal arrangement for a turbine stage includes a vane assembly including radially inner and outer vane platforms and an airfoil. The seal arrangement further includes a rim seal feature including forward and aft rim seal legs extending radially inward from a radially inward surface of the radially inner vane platform. An impingement plate covers the radially inward facing surface of the radially inner vane platform and extends axially aft up to the aft rim seal leg. A rim seal containment structure is located radially inward of the impingement plate and extends axially over the aft portion of the radially inner vane platform up to the aft rim seal leg. A cooling cavity is defined between the rim seal containment structure and the impingement plate and extends axially aft up to the aft rim seal leg to provide cooling to an aft portion of the radially inner vane platform.