公开(公告)号：US20230250730A1

公开(公告)日：2023-08-10

申请号：US17667793

申请日：2022-02-09

Applicant: General Electric Company

Inventor： Subramanya Shankar ,  Marc Christopfel ,  Brian G. Quinn ,  Omar A. Ramirez ,  Sean M. O'Melia

IPC: F01D21/00 ,  F01D11/14

CPC classification number: F01D21/003 ,  F01D11/14 ,  F05D2260/30 ,  F05D2260/80 ,  F05D2270/305 ,  F05D2270/804 ,  G01C9/02

Abstract: A system and method for inspecting fan blade clearances in a fan stator module are presented. The method includes rotating a fan rotor assembly that includes an attached bracket situated between adjacent fan blades connected to the fan rotor assembly. The bracket includes a laser module and an inclinometer configured to measure a circumferential position of the laser module. The method further includes projecting a laser beam from the laser module to the fan case to determine a distance measurement between the laser module and the fan case at multiple circumferential points around the fan case. The distance measurement and circumferential position data is processed by a computing device to determine a clearance distance between a fan blade and the fan case.

公开(公告)号：US20240377193A1

公开(公告)日：2024-11-14

申请号：US18339370

申请日：2023-06-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Subramanya Shankar ,  Kirti Arvind Petkar ,  Nagamohan G P ,  Ravindra Shankar Ganiger

IPC: G01B21/16

Abstract: A gas turbine engine includes a fan assembly, a compressor section, a combustor section, and a turbine section in serial flow arrangement, and defining an engine centerline. Sets of fan blades within the fan assembly can be rotatably driven about the engine centerline within a casing wall. A fan blade tip clearance is defined as a gap between the set of fan blades and the fan casing assembly. A clearance measurement system including a pad with one or more integrated sensors provides for measuring the gap.

公开(公告)号：US11885228B2

公开(公告)日：2024-01-30

申请号：US17667793

申请日：2022-02-09

Applicant: General Electric Company

Inventor： Subramanya Shankar ,  Marc Christopfel ,  Brian G. Quinn ,  Omar A. Ramirez ,  Sean M. O′Melia

IPC: F01D21/00 ,  F01D11/14 ,  G01B11/14 ,  G01C9/02

CPC classification number: F01D21/003 ,  F01D11/14 ,  F05D2260/30 ,  F05D2260/80 ,  F05D2270/305 ,  F05D2270/804 ,  G01B11/14 ,  G01C9/02

Abstract: A system and method for inspecting fan blade clearances in a fan stator module are presented. The method includes rotating a fan rotor assembly that includes an attached bracket situated between adjacent fan blades connected to the fan rotor assembly. The bracket includes a laser module and an inclinometer configured to measure a circumferential position of the laser module. The method further includes projecting a laser beam from the laser module to the fan case to determine a distance measurement between the laser module and the fan case at multiple circumferential points around the fan case. The distance measurement and circumferential position data is processed by a computing device to determine a clearance distance between a fan blade and the fan case.

公开(公告)号：US10801361B2

公开(公告)日：2020-10-13

申请号：US15260641

申请日：2016-09-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nagamohan Govinahalli Prabhakar ,  Steven Andrew Strang ,  Charles Stanley Orkiszewski ,  Subramanya Shankar ,  Nitesh Jain ,  Michael Riehle

IPC: F01D21/04 ,  F01D11/00 ,  F01D5/30 ,  F01D21/02 ,  F02K3/06

Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.

公开(公告)号：US20180073388A1

公开(公告)日：2018-03-15

申请号：US15260641

申请日：2016-09-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nagamohan Govinahalli Prabhakar ,  Steven Andrew Strang ,  Charles Stanley Orkiszewski ,  Subramanya Shankar ,  Nitesh Jain ,  Michael Riehle

IPC: F01D21/04 ,  F01D5/30 ,  F01D21/02 ,  F02K3/06

Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.