Patent ID: 9708920
Date: 2017-07-18
CPC Classifications: F01D,F02C,F23R

Claim:
1. A gas turbine, comprising: a combustor comprising a combustor shell and a combustor outlet; a turbine disposed downstream of the combustor, the turbine comprising an inlet separated from the combustor outlet by a transition region, the transition region defining a gap between the combustor and the turbine; and a plurality of support elements fixedly attached along an inner circumference of the combustor shell, each support element comprising a pivot bearing configured to support a pivotable transition element that extends in a direction away from the support element and is configured to movably bridge the gap defined by the transition region between the combustor and the turbine; wherein a rotor cover of the gas turbine defines a conical contour surface that is configured to slideably engage a bevel surface portion of each support element upon thermal expansion of the combustor shell; and further comprising a pressure bolt acted on by a compression spring that is configured to press a free end of the pivotable transition element against a wall of the inlet of the turbine, another end of the pivotable transition element being coupled to the pivot bearing.