公开(公告)号：US20220220854A1

公开(公告)日：2022-07-14

申请号：US17529685

申请日：2021-11-18

Applicant: GE Avio S.r.l. ,  GENERAL ELECTRIC COMPANY

Inventor： Pratish Patil ,  Amit Goyal ,  Mahendran Manoharan ,  Francesco Bertini ,  Jaikumar Loganathan

IPC: F01D5/14

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

公开(公告)号：US11933193B2

公开(公告)日：2024-03-19

申请号：US17529685

申请日：2021-11-18

Applicant: GE Avio S.r.l. ,  GENERAL ELECTRIC COMPANY

Inventor： Pratish Patil ,  Amit Goyal ,  Mahendran Manoharan ,  Francesco Bertini ,  Jaikumar Loganathan

IPC: F01D5/14

CPC classification number: F01D5/145 ,  F05D2240/31

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

公开(公告)号：US20240318570A1

公开(公告)日：2024-09-26

申请号：US18189379

申请日：2023-03-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  David Raju Yamarthi ,  Chandrashekhar Kandukuri ,  Deepak Trivedi ,  Narendra Anand Hardikar ,  Vidyashankar Ramasastry Buravalla ,  Steven Douglas Johnson ,  Amit Goyal ,  Grant Robert Portune ,  Himanshu Gupta ,  Srinivasan Swaminathan ,  Shalini Thimmegowda ,  Guru Venkata Dattu Jonnalagadda ,  Shalabh Saxena ,  Prateek Jalan

IPC: F01D11/02

CPC classification number: F01D11/025 ,  F05D2240/53 ,  F05D2240/55 ,  F05D2260/38

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.

公开(公告)号：US12241375B2

公开(公告)日：2025-03-04

申请号：US18189379

申请日：2023-03-24

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  David Raju Yamarthi ,  Chandrashekhar Kandukuri ,  Deepak Trivedi ,  Narendra Anand Hardikar ,  Vidyashankar Ramasastry Buravalla ,  Steven Douglas Johnson ,  Amit Goyal ,  Grant Robert Portune ,  Himanshu Gupta ,  Srinivasan Swaminathan ,  Shalini Thimmegowda ,  Guru Venkata Dattu Jonnalagadda ,  Shalabh Saxena ,  Prateek Jalan

IPC: F01D11/02

Abstract: A turbine engine is provided. The turbine engine defines an axial direction and a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly defining a high-pressure side and a low-pressure side and comprising a plurality of seal segments, the plurality of seal segments including a seal segment having a seal face forming a fluid bearing with the rotor, a lip, and a body, the lip extending from the body along the axial direction of the turbine engine on the high-pressure side and including an outer pressurization surface along the radial direction of the turbine engine; and a seal support assembly, the seal support assembly comprising a spring arrangement extending between the carrier and the first seal segment to counter a pressure on the outer pressurization surface during operation of the turbine engine.