公开(公告)号：US20240254884A1

公开(公告)日：2024-08-01

申请号：US18635858

申请日：2024-04-15

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Francesco Bertini ,  Davide Torzo ,  Pratish Patil ,  John Joseph ,  Mahendran Manoharan ,  Ganesh Seshadri

IPC: F01D5/14

CPC classification number: F01D5/142 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/30

Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.

公开(公告)号：US20230296024A1

公开(公告)日：2023-09-21

申请号：US17951653

申请日：2022-09-23

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Francesco Bertini ,  Davide Torzo ,  Pratish Patil ,  John Joseph ,  Mahendran Manoharan ,  Ganesh Seshadri

IPC: F01D5/14

CPC classification number: F01D5/142 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/30

Abstract: Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.

公开(公告)号：US20180355763A1

公开(公告)日：2018-12-13

申请号：US15620264

申请日：2017-06-12

Applicant: General Electric Company

Inventor： Chaitanya Venkata Rama Krishna Ongole ,  John Joseph ,  Ganesh Seshadri ,  Ravikanth Avancha

IPC: F01D25/28 ,  F02C3/04 ,  F01D9/04

CPC classification number: F01D25/28 ,  F01D9/041 ,  F02C3/04

Abstract: An apparatus and method for diffusing an airflow in a turbine engine can include a turbine center frame positioned between a high pressure turbine and a low pressure turbine of a turbine section of the engine. The turbine center frame can include two or more diffusion sections for diffusing the airflow. A stabilization section can be provided between the two or more diffusion sections to stabilize the airflow.