公开(公告)号：US11480111B2

公开(公告)日：2022-10-25

申请号：US16412771

申请日：2019-05-15

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： David K. Jan ,  Dietmar Giebert ,  Thomas G. Cunningham, Jr.

IPC: F01D17/08 ,  F02C9/22 ,  F01D17/16 ,  F01D17/14 ,  F02C9/54 ,  F01D17/06 ,  F01D17/04 ,  F01D19/02

Abstract: A gas turbine engine with a compressor supplying compressed air. A combustor receives the compressed air and fuel and generates a flow of combusted gas. A turbine receives a core flow of the combusted gas to rotate a turbine rotor. A turbine inlet nozzle directs the combusted gas to the turbine rotor. Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes. The vanes adjust a pressure ratio of the gas turbine engine to compensate for changing operational requirements of the gas turbine engine by rotating to positions matching the changing operational requirements.