公开(公告)号：US10767485B2

公开(公告)日：2020-09-08

申请号：US15864925

申请日：2018-01-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew E Bintz ,  Enzo DiBenedetto ,  Paul E Coderre

IPC: F01D5/06 ,  F01D5/08 ,  F02C7/18 ,  F02C7/141 ,  F04D29/58 ,  F04D29/32 ,  F01D11/02 ,  F01D11/00

Abstract: A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.