公开(公告)号：US12012859B2

公开(公告)日：2024-06-18

申请号：US17894881

申请日：2022-08-24

Applicant: General Electric Company

Inventor： Raghuveer Chinta ,  Abhijit Roy ,  Vaishnav Raghuvaran ,  Srinivas Nuthi ,  Ravindra Shankar Ganiger

IPC: F01D11/22

CPC classification number: F01D11/22 ,  F05D2220/32 ,  F05D2240/55

Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction; a second annular substrate positioned radially inward relative to the first annular substrate, the second annular substrate movably coupled to the first annular substrate; and an actuator coupled to the second annular substrate such that a force applied by the actuator moves the second annular substrate relative to the first annular substrate to adjust a tip clearance.

公开(公告)号：US11795827B1

公开(公告)日：2023-10-24

申请号：US17712701

申请日：2022-04-04

Applicant: General Electric Company

Inventor： Raghuveer Chinta ,  Srinivas Nuthi ,  Gary Willard Bryant, Jr. ,  Nicholas Joseph Kray

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2230/10 ,  F05D2230/50 ,  F05D2250/283 ,  F05D2300/612

Abstract: An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.

公开(公告)号：US20180328176A1

公开(公告)日：2018-11-15

申请号：US15591275

申请日：2017-05-10

Applicant: General Electric Company

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

IPC: F01D5/02 ,  F02C3/04 ,  F01D25/00

CPC classification number: F01D25/005 ,  F01D5/147 ,  F01D5/28 ,  F01D5/282 ,  F02C7/04 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2300/10 ,  F05D2300/2102 ,  F05D2300/50212 ,  F05D2300/603

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：US20240301802A1

公开(公告)日：2024-09-12

申请号：US18657420

申请日：2024-05-07

Applicant: General Electric Company

Inventor： Raghuveer Chinta ,  Abhijit Roy ,  Vaishnav Raghuvaran ,  Srinivas Nuthi ,  Ravindra Shankar Ganiger

IPC: F01D11/22

CPC classification number: F01D11/22 ,  F05D2220/32 ,  F05D2240/55

Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction; a second annular substrate positioned radially inward relative to the first annular substrate, the second annular substrate movably coupled to the first annular substrate; and an actuator coupled to the second annular substrate such that a force applied by the actuator moves the second annular substrate relative to the first annular substrate to adjust a tip clearance.

公开(公告)号：US12044172B2

公开(公告)日：2024-07-23

申请号：US18148559

申请日：2022-12-30

Applicant: General Electric Company

Inventor： Vaishnav Raghuvaran ,  Sesha Subramanian ,  Hari Krishna Meka ,  Vishnu Vardhan Venkata Tatiparthi ,  Raghuveer Chinta ,  Daniel O'Brien ,  Sai Raju Ippili ,  Michael Thomas Hogan

IPC: F01D25/12 ,  F01D25/14 ,  F02C7/18 ,  F02C7/28

CPC classification number: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/201

Abstract: A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

公开(公告)号：US20240011408A1

公开(公告)日：2024-01-11

申请号：US17894881

申请日：2022-08-24

Applicant: General Electric Company

Inventor： Raghuveer Chinta ,  Abhijit Roy ,  Vaishnav Raghuvaran ,  Srinivas Nuthi ,  Ravindra Shankar Ganiger

IPC: F01D11/22

CPC classification number: F01D11/22 ,  F05D2220/32 ,  F05D2240/55

Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction; a second annular substrate positioned radially inward relative to the first annular substrate, the second annular substrate movably coupled to the first annular substrate; and an actuator coupled to the second annular substrate such that a force applied by the actuator moves the second annular substrate relative to the first annular substrate to adjust a tip clearance.

公开(公告)号：US20240141834A1

公开(公告)日：2024-05-02

申请号：US18148559

申请日：2022-12-30

Applicant: General Electric Company

Inventor： Vaishnav Raghuvaran ,  Sesha Subramanian ,  Hari Krishna Meka ,  Vishnu Vardhan Venkata Tatiparthi ,  Raghuveer Chinta ,  Daniel O'Brien ,  Sai Raju Ippili ,  Michael Thomas Hogan

IPC: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F02C7/28

CPC classification number: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/201

Abstract: A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

公开(公告)号：US20230313687A1

公开(公告)日：2023-10-05

申请号：US17712701

申请日：2022-04-04

Applicant: General Electric Company

Inventor： Raghuveer Chinta ,  Srinivas Nuthi ,  Gary Willard Bryant, JR. ,  Nicholas Joseph Kray

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2250/283 ,  F05D2230/50 ,  F05D2230/10 ,  F05D2300/612

Abstract: An airfoil assembly comprising a central spar extending along the radial direction; a blade skin positioned around the central spar to define an airfoil that has a pressure side and a suction side extending in the axial direction between a leading edge and a trailing edge, wherein at least one cavity is defined between the blade skin and the central spar; and a support structure positioned at least partially within the at least one cavity. The support structure comprises: a foam; and a foam reinforcement structure embedded within the foam.

公开(公告)号：US20230020608A1

公开(公告)日：2023-01-19

申请号：US17375433

申请日：2021-07-14

Applicant: General Electric Company

Inventor： Nitesh Jain ,  Raghuveer Chinta ,  Nicholas Joseph Kray ,  Wendy Wenling Lin

IPC: F01D5/28

Abstract: A fan platform for gas turbine engine is provided. The fan platform incudes a body portion and a flow path surface coupled to the body portion. The body portion and the flow path surface define at least a portion of a flow path extending through the engine. The body portion and/or the flow path surface include an impact region including hybrid composite plies including one or more metallic tows. A gas turbine engine including the fan platform and methods for forming the fan platform are also disclosed.

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.