公开(公告)号：US10677260B2

公开(公告)日：2020-06-09

申请号：US15438284

申请日：2017-02-21

Applicant: General Electric Company

Inventor： Veeraraju Vanapalli ,  Nitesh Jain ,  Viswanadha Gupta Sakala ,  Bhaskar Nanda Mondal ,  Nicholas Joseph Kray

IPC: F04D29/52 ,  F04D29/02 ,  F01D25/26 ,  F01D9/04 ,  F01D25/24 ,  F04D29/40 ,  F01D11/08 ,  F02K3/06

Abstract: A turbine engine that includes a rotor assembly including a plurality of rotor blades, an outer case positioned radially outward from the plurality of rotor blades, and an annular ring coupled to the outer case and positioned between the plurality of rotor blades and the outer case. The annular ring is configured to restrict thermal contraction of the outer case towards the plurality of rotor blades.

公开(公告)号：US10677090B2

公开(公告)日：2020-06-09

申请号：US15591275

申请日：2017-05-10

Applicant: General Electric Company

Inventor： Viswanadha Gupta Sakala ,  Wendy Wenling Lin ,  Raghuveer Chinta

IPC: F01D25/00 ,  F02C7/04 ,  F01D5/28 ,  F01D5/14

Abstract: An annular rotatable component for a machine includes a first element formed of a composite material, is ring-shaped, and is formed of one or more first ring segments. The first element includes a first interface surface. A second element is formed of a metallic material, is ring-shaped, and is formed of one or more second ring segments. The second element includes a second interface surface complementary to the first interface surface. The annular rotatable component also includes an interface comprising an interface material disposed between the first interface surface and the second interface surface. The interface material, the first element and the second element are co-bonded together to form a unitary structure of the annular rotatable component.

公开(公告)号：US20180355796A1

公开(公告)日：2018-12-13

申请号：US15620451

申请日：2017-06-12

Applicant: General Electric Company

Inventor： Richa Awasthi ,  Bhanu Kishore Battu ,  Viswanadha Gupta Sakala ,  Michael Jason Bishop

IPC: F02C7/04 ,  F16B41/00 ,  F16B33/00

CPC classification number: F02C7/04 ,  F05D2220/32 ,  F05D2250/10 ,  F16B33/004 ,  F16B41/002

Abstract: A fastener cover assembly is disclosed. The cover assembly includes a turbomachinery component having an outer surface exposed to an air flow path; at least one recess formed in the outer surface; a fastener contained in the at least one recess; and a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the component to minimize air flow disruption.