公开(公告)号：US20230235679A1

公开(公告)日：2023-07-27

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：US11702940B2

公开(公告)日：2023-07-18

申请号：US17844578

申请日：2022-06-20

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Viswanadha Gupta Sakala ,  Nicholas Joseph Kray ,  Ambika Shivamurthy ,  Kirti Arvind Petkar

IPC: F01D5/02 ,  F01D5/14 ,  G06F30/17

CPC classification number: F01D5/147 ,  F01D5/02 ,  G06F30/17 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2240/24

Abstract: Methods, apparatus, systems and articles of manufacture corresponding to a fan blade with intrinsic damping characteristics are disclosed. An example fan blade comprises an exterior body including a first side and a second side; a first hairpin structure in contact with (a) the first side of the exterior body and (b) the second side of the exterior body; and a second hairpin structure in contact with (a) the first side and (b) the second side, wherein the first hairpin structure and the second hairpin structure are made from different materials.

公开(公告)号：US20230212954A1

公开(公告)日：2023-07-06

申请号：US17962243

申请日：2022-10-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Anusrita Raychaudhuri ,  Apostolos Karafillis

IPC: F01D11/00 ,  F16J15/08

CPC classification number: F01D11/005 ,  F16J15/0887 ,  F05D2220/32 ,  F05D2240/55

Abstract: A sealing apparatus for a gas turbine engine includes: a first component; a second component positioned in proximity to the first component such that cavity is defined between the first and second components; a resilient seal disposed in the cavity so as to block gas flow between the first and second components, the resilient seal having a first contact surface contacting the first component and a second contact surface contacting the second component; and wherein the resilient seal is configured so as to produce a rolling movement in response to relative movement of the first and second components.

公开(公告)号：US20230160310A1

公开(公告)日：2023-05-25

申请号：US18090197

申请日：2022-12-28

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Sam J. Stoughton ,  Kevin Lee Kirkeng ,  Jacob P. Miller ,  Reddi Hari Prasad Reddy Mylapalli ,  Paul Trimby ,  Jaeyong Kim

IPC: F01D5/22 ,  F02C7/28

CPC classification number: F01D5/225 ,  F02C7/28 ,  F05D2260/96 ,  F05D2250/283 ,  F05D2260/31 ,  F05D2240/55

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An inner shroud damper for a gas turbine engine includes: at least one carrier including a joint to couple to an inner shroud, the at least one carrier having a first side and a second side, and at least one mass damper coupled to the at least one carrier.

公开(公告)号：US11639688B1

公开(公告)日：2023-05-02

申请号：US17658134

申请日：2022-04-06

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

Inventor： Bugra H. Ertas ,  Ravindra Shankar Ganiger ,  Andrea Piazza

IPC: F02C7/36 ,  F16H57/00 ,  F16H57/023 ,  F01D25/04

Abstract: A planetary gear system includes a sun gear, a plurality of planet gears connected to a carrier and engaging with the sun gear, and a ring gear assembly including a damper housing, and a ring gear connected to the damper housing and engaging with the plurality of planet gears. The ring gear includes a geared wall having a plurality of gear teeth engaging with the plurality of planet gears, and a damper housing attachment member radially spaced outward of the geared wall and attaching the ring gear to the damper housing. A first end of the geared wall and the damper housing engage each other via a plurality of squeeze film damping members, and a second end of the geared wall is connected to the damper housing attachment member via a flexible damping wall that is configured to provide a radial damping of the second end of the geared wall.

公开(公告)号：US11608747B2

公开(公告)日：2023-03-21

申请号：US17143855

申请日：2021-01-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Sam J. Stoughton ,  Kevin Lee Kirkeng ,  Jacob P. Miller ,  Reddi Hari Prasad Reddy Mylapalli ,  Paul Trimby ,  Jaeyong Kim

IPC: F01D5/22 ,  F02C7/28 ,  F01D25/04 ,  F01D5/16 ,  F01D25/06 ,  F01D5/26 ,  F01D17/16 ,  F04D29/66 ,  F01D11/00 ,  F04D29/56

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A split shroud for an inner shroud of a gas turbine engine includes: at least one forward shroud segment and at least one aft shroud segment to couple to the at least one forward shroud segment, the at least one forward shroud segment and the at least one aft shroud segment forming a split line.

公开(公告)号：US20230008935A1

公开(公告)日：2023-01-12

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 ,  F03G7/06 ,  F04D19/00

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：US20220213794A1

公开(公告)日：2022-07-07

申请号：US17143851

申请日：2021-01-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Sam J. Stoughton ,  Kevin Lee Kirkeng ,  Jacob P. Miller ,  Reddi Hari Prasad Reddy Mylapalli ,  Paul Trimby ,  Jaeyong Kim

IPC: F01D5/22 ,  F02C7/28

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An inner shroud damper for a gas turbine engine includes: at least one carrier including a joint to couple to an inner shroud, the at least one carrier having a first side and a second side, and at least one mass damper coupled to the at least one carrier.

公开(公告)号：US20220195931A1

公开(公告)日：2022-06-23

申请号：US17130040

申请日：2020-12-22

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Michael Anthony Benjamin ,  Rajendra Mahadeorao Wankhade ,  Gurunath Gandikota

IPC: F02C7/24 ,  F02C7/22 ,  F23R3/28

Abstract: A combustor for a gas turbine engine includes an inner liner and an outer liner positioned outward of the inner liner along the radial direction such that a combustion chamber is defined between the inner and outer liners. Furthermore, the combustor includes a fuel nozzle configured to supply fuel to the combustion chamber. Moreover, the combustor includes a bristle pack having a base plate and a plurality of bristles extending outward from the base plate such that the bristle pack forms at least a portion of at least one of a heat shield coupled to the fuel nozzle, a deflector of the combustor, or a flare of the combustor.

公开(公告)号：US20220098999A1

公开(公告)日：2022-03-31

申请号：US17387002

申请日：2021-07-28

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Shivam Mittal ,  Bhujabal Prashant Mahadeo ,  Weize Kang ,  Richard Schmidt

IPC: F01D25/16 ,  F02C7/36 ,  F01D25/18 ,  F02C7/06 ,  F16C27/04 ,  F16C35/077 ,  F16C19/26 ,  F16C19/06 ,  F03G7/06

Abstract: A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.