公开(公告)号：US20190353051A1

公开(公告)日：2019-11-21

申请号：US15979982

申请日：2018-05-15

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Shuvajyoti Ghosh ,  Amit Zutshi ,  Raghavendra Muralidhar ,  Rangasai Madoor Comandore

IPC: F01D25/16

Abstract: A turbine engine including a first static structure comprising a first material defining a first thermal expansion coefficient and a second static structure comprising a second material defining a second thermal expansion coefficient different from the first thermal expansion coefficient. The first static structure and the second static structure are together disposed in adjacent arrangement along a load direction. The first static structure and the second static structure together selectively define a gap therebetween along the load direction based at least on a load difference between the first static structure and the second static structure.

公开(公告)号：US20250146422A1

公开(公告)日：2025-05-08

申请号：US19009183

申请日：2025-01-03

Applicant: General Electric Company

Inventor： Santosh Potnuru ,  Pradeep Hemant Sangli ,  Ravindra Shankar Ganiger ,  Praveen Sharma ,  Scott Alan Schimmels

IPC: F01D11/08 ,  F01D11/02 ,  F03G7/06

Abstract: A seal assembly for a rotary machine. The seal assembly includes a rotor and a stator. The rotor is rotatable about a rotational axis and has a rotor seal face. The stator has a stator seal face. The stator seal face is positioned opposite the rotor seal face and faces the rotor seal face with a gap therebetween. A portion of one of the rotor and the stator is formed of (i) a shape memory alloy or (ii) a first metal and a second metal with the second metal having a coefficient of thermal expansion different from the first metal. The seal assembly is characterized by a seal clearance compliance ratio (SCCR) from 20% to 90%.

公开(公告)号：US20240401494A1

公开(公告)日：2024-12-05

申请号：US18325621

申请日：2023-05-30

Applicant: General Electric Company

Inventor： Santosh Potnuru ,  Pradeep Hemant Sangli ,  Ravindra Shankar Ganiger ,  Praveen Sharma ,  Scott Alan Schimmels

IPC: F01D11/08 ,  F03G7/06

Abstract: A seal assembly for a rotary machine. The seal assembly includes a rotor and a stator. The rotor is rotatable about a rotational axis and has a rotor seal face. The stator has a stator seal face. The stator seal face is positioned opposite the rotor seal face and faces the rotor seal face with a gap therebetween. A portion of one of the rotor and the stator is formed of (i) a shape memory alloy or (ii) a first metal and a second metal with the second metal having a coefficient of thermal expansion different from the first metal. The seal assembly is characterized by a seal clearance compliance ratio (SCCR) from 20% to 90%.

公开(公告)号：US12055046B2

公开(公告)日：2024-08-06

申请号：US17704581

申请日：2022-03-25

Applicant: General Electric Company

Inventor： Praveen Sharma ,  Ravindra Shankar Ganiger ,  Milind Chandrakant Dhabade

IPC: F01D11/12 ,  F01D25/04

CPC classification number: F01D11/127 ,  F01D25/04 ,  F05D2240/11 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/96

Abstract: Curved beams stacked structures-compliant shrouds for gas turbine engines are disclosed. An example shroud assembly comprising a plurality of concave curved beams, a plurality of convex curved beams, and a plurality of bumpers, wherein a first concave curved beam of the plurality of concave curved beams is inversely coupled to a first convex curved beam of the plurality of convex curved beams, a second concave curved beam of the plurality of concave curved beams, inversely coupled to a second convex curved beam of the plurality of convex curved beams, the first and second concave curved beams configured to stack on top of the first and second convex curved beams, a first bumper of the plurality of bumpers coupled to the first and second concave curved beams, and a second bumper of the plurality of bumpers coupled to the first and second convex curved beams.

公开(公告)号：US20240110504A1

公开(公告)日：2024-04-04

申请号：US17955713

申请日：2022-09-29

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

Inventor： Ranganayakulu Alapati ,  Peeyush Pankaj ,  Sanjeev Sai Kumar Manepalli ,  Bhaskar Nanda Mondal ,  Thomas Moniz ,  N V Sai Krishna Emani ,  Shishir Paresh Shah ,  Anil Soni ,  Praveen Sharma ,  Randy T. Antelo ,  Antonio Giuseppe D'Ettole

IPC: F02C3/067 ,  F02C3/10

CPC classification number: F02C3/067 ,  F02C3/10 ,  F05D2220/323 ,  F05D2240/24

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.

公开(公告)号：US20230417149A1

公开(公告)日：2023-12-28

申请号：US18463970

申请日：2023-09-08

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Jeffrey D. Carnes ,  Herbert Chidsey Roberts

IPC: F01D11/12 ,  F01D11/14

CPC classification number: F01D11/127 ,  F01D11/14 ,  F05D2240/11 ,  F05D2270/42 ,  F05D2260/38 ,  F05D2270/114 ,  F05D2250/183

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.

公开(公告)号：US11852027B2

公开(公告)日：2023-12-26

申请号：US17329220

申请日：2021-05-25

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Bhujabal Prashant Mahadeo ,  Shivam Mittal

IPC: F01D25/16 ,  F16C35/06 ,  F01D25/00

CPC classification number: F01D25/164 ,  F01D25/005 ,  F16C35/06 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2260/96 ,  F05D2300/17 ,  F05D2300/505 ,  F16C2360/23

Abstract: A support assembly for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The support assembly includes an outer race positioned radially exterior to the bearing such that the outer race supports the bearing. Additionally, the support assembly includes a shape memory alloy damper positioned radially exterior to the outer race and at least partially supporting the outer race. Moreover, the shape memory alloy damper includes a plurality of sleeves. One or more sleeves of the plurality of sleeves include a shape memory alloy material.

公开(公告)号：US11668317B2

公开(公告)日：2023-06-06

申请号：US17408986

申请日：2021-08-23

Applicant: General Electric Company

Inventor： Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas Joseph Kray ,  Ravindra Shankar Ganiger ,  Praveen Sharma

IPC: F04D29/36 ,  F04D19/00 ,  F03G7/06

CPC classification number: F04D29/368 ,  F03G7/0614 ,  F04D19/002

Abstract: An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

公开(公告)号：US20230008743A1

公开(公告)日：2023-01-12

申请号：US17368961

申请日：2021-07-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Abhijeet Jayshingrao Yadav ,  Nitesh Jain ,  Nicholas Joseph Kray

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/30

Abstract: An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

公开(公告)号：US11549392B2

公开(公告)日：2023-01-10

申请号：US15842168

申请日：2017-12-14

Applicant: General Electric Company

Inventor： Milind Chandrakant Dhabade ,  Kudum Shinde ,  Thomas Edward Agin ,  Weize Kang ,  Praveen Sharma ,  Shivam Mittal

IPC: F01D21/12 ,  F01D17/10 ,  F01D5/02 ,  F01D25/36 ,  F01D19/02 ,  F02C7/32 ,  F02C7/268 ,  F02C6/14 ,  F02C7/275

Abstract: A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.