A flow cavity arrangement for gas turbine engine

摘要

It is known with regard to particularly cavities 33, 43 below high pressure turbine discs 34, 44 that mixing of hot gas leakage flows BB through an inner seal 48 with cooling flows AA can diminish the effectiveness of that cooling flow AA when presented to other parts for cooling. By providing a path 51 within a wall 41 which is particularly shaped in portions 42, 43 it is possible to provide entrainment of a hot leakage gas flow BB away from entry into the cavity (43). Thus, the cooling flow AA retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow BB occurred.