公开(公告)号：US12065947B2

公开(公告)日：2024-08-20

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 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/31 ,  F05D2260/96

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：US20240271565A1

公开(公告)日：2024-08-15

申请号：US18644554

申请日：2024-04-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/06 ,  F01D25/16 ,  F16C19/54 ,  F16C25/08 ,  F16C27/06

CPC classification number: F02C7/06 ,  F01D25/16 ,  F01D25/162 ,  F01D25/164 ,  F05D2220/32 ,  F05D2240/52 ,  F16C19/54 ,  F16C19/541 ,  F16C25/083 ,  F16C27/066 ,  F16C2360/23

Abstract: A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.

公开(公告)号：US12060798B2

公开(公告)日：2024-08-13

申请号：US18199249

申请日：2023-05-18

Applicant: General Electric Company

Inventor： Arundhati Sengupta ,  Ravindra Shankar Ganiger ,  Anand Madihalli Srinivasan ,  Scott Francis Wolfer

IPC: F01D11/00 ,  F01D11/02

CPC classification number: F01D11/003 ,  F01D11/00 ,  F01D11/02 ,  F05D2240/55 ,  F05D2300/611

Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. In some examples, seal assembly includes an oleophilic coating disposed between the stationary and rotating components. The seal assembly may include a surface texture to enhance the oleophilicity of the surface coating disposed between the stationary and rotating components. In other examples, the seal assembly includes an oleophobic coating disposed between the stationary and rotating components. The seal assembly may include a surface texture to enhance the oleophobicity of the surface coating. During operation, the oleophilic seal assembly features retain lubricant between the stationary and rotating components and the oleophobic seal assembly features inhibit the escape of lubricant from the contact regions between the stationary and rotating components.

公开(公告)号：US20240247803A1

公开(公告)日：2024-07-25

申请号：US18324313

申请日：2023-05-26

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Nath ,  Asim Ghosal ,  Sripathi Mohan ,  Nageswar Ganji

IPC: F23R3/14 ,  F23R3/00 ,  F23R3/60

CPC classification number: F23R3/14 ,  F23R3/002 ,  F23R3/60

Abstract: A dome-deflector assembly for a combustor of a gas turbine includes a dome portion having a dome-side swirler opening therethrough, and a deflector portion having a deflector-side swirler opening therethrough. The dome portion and the deflector portion are connected together to form a dome-deflector cavity therebetween. The deflector portion includes a first-side surface and a second-side surface, the second-side surface being arranged within the dome-deflector cavity, and the second-side surface including a plurality of stress-relief contours arranged in a pattern about the deflector-side swirler opening.

公开(公告)号：US12018722B1

公开(公告)日：2024-06-25

申请号：US18305139

申请日：2023-04-21

Applicant: General Electric Company

Inventor： Arman Mohammad Khan ,  Souvik Math ,  Ravindra Shankar Ganiger ,  Arundhati Sengupta ,  Santosh Prasad ,  Duane H Anstead

IPC: F16C33/66 ,  F01M11/00 ,  F02C7/06

CPC classification number: F16C33/6685 ,  F01M11/0004 ,  F02C7/06 ,  F01M2011/0091 ,  F16C2360/23

Abstract: Oleophobic and/or oleophilic coatings to reduce heat loads on a gas turbine engine thermal management system are disclosed herein. An example method to reduce heat load in a gas turbine engine includes applying an oleophobic coating to an internal wall of a sump, the sump located in proximity to a heat generating element of the gas turbine engine, and applying an oleophilic coating to the heat generating element of the gas turbine engine, the heat generating element positioned in a cavity of the sump.

公开(公告)号：US20240133342A1

公开(公告)日：2024-04-25

申请号：US18049112

申请日：2022-10-23

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Kudum Shinde ,  Surender Reddy Bhavanam ,  Weize Kang

IPC: F02C7/06 ,  F01D25/16

CPC classification number: F02C7/06 ,  F01D25/16 ,  F05D2220/32 ,  F05D2240/52

Abstract: A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.

公开(公告)号：US20240125271A1

公开(公告)日：2024-04-18

申请号：US18071368

申请日：2022-11-29

Applicant: General Electric Company

Inventor： David Raju Yamarthi ,  Adam Joesph Wangler ,  Santosh Kumar Pattnaik ,  Brian G. Brzek ,  Ravindra Shankar Ganiger

IPC: F02C7/14 ,  F02C9/00

CPC classification number: F02C7/14 ,  F02C9/00 ,  F05D2220/36 ,  F05D2260/213 ,  F05D2270/303

Abstract: Example pump systems having dual-function annular heat exchangers are disclosed. An example pump system to pressurize a fluid within a closed loop transport bus includes a pump to move the fluid, a conduit in fluid connection with the pump, a heat exchanger positioned around at least a portion of the conduit, the heat exchanger to receive a first electrical signal transmitted in a first direction at a first time and a second electrical signal transmitted in a second direction at a second time different from the first time, the second direction opposite the first direction.

公开(公告)号：US11927349B2

公开(公告)日：2024-03-12

申请号：US17812897

申请日：2022-07-15

Applicant: General Electric Company

Inventor： Vijayaraj Sukumar ,  Perumallu Vukanti ,  Pradeep Naik ,  Ajoy Patra ,  Karthikeyan Sampath ,  Rimple Rangrej ,  Hiranya Nath ,  Krishnendu Chakraborty ,  Narasimhan S. Sahana ,  Saket Singh ,  Ravindra Shankar Ganiger

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/10 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R3/04 ,  F23R3/10 ,  F23R2900/00017 ,  F23R2900/03045

Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.

公开(公告)号：US20240076989A1

公开(公告)日：2024-03-07

申请号：US18081151

申请日：2022-12-14

Applicant: General Electric Company

Inventor： David Raju Yamarthi ,  Ravindra Shankar Ganiger ,  Vasanth Kumar Balaramudu ,  Vishnu Vardhan Venkata Tatiparthi ,  Nitesh Jain ,  Vidyashankar Ramasastry Buravalla

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2230/60

Abstract: An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.

公开(公告)号：US20240027066A1

公开(公告)日：2024-01-25

申请号：US18060808

申请日：2022-12-01

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Ravindra Shankar Ganiger ,  Ajoy Patra ,  Rajendra Wankhade

IPC: F23R3/00 ,  F23R3/46 ,  F23R3/16

CPC classification number: F23R3/002 ,  F23R3/46 ,  F23R3/16 ,  F05D2220/32 ,  F05D2240/35

Abstract: An annular combustor includes a combustion liner defining a combustion chamber, the combustion liner having an outer liner and an inner liner and a plurality of dimples in the combustion liner. The combustion liner is characterized by a performance factor greater than or equal to one and less than or equal to seven. An engine includes the annular combustor.