-
公开(公告)号：US20230003382A1
公开(公告)日：2023-01-05
申请号：US17363088
申请日：2021-06-30
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Rajendra Mahadeorao Wankhade , Daniel J. Kirtley , Michael Anthony Benjamin
Abstract: A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.
-
公开(公告)号：US20220390113A1
公开(公告)日：2022-12-08
申请号：US17340816
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Daniel J. Kirtley , Shai Birmaher , Pradeep Naik
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.
-
公开(公告)号：US20220390112A1
公开(公告)日：2022-12-08
申请号：US17340703
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Perumallu Vukanti , Daniel J. Kirtley , Karthikeyan Sampath , Shai Birmaher , Pradeep Naik , Rajendra Mahadeorao Wankhade , Michael Anthony Benjamin , Veeraraju Vanapalli , Deepak Ghiya
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.
-
公开(公告)号：US20220390111A1
公开(公告)日：2022-12-08
申请号：US17340654
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Kumar Nath , Daniel J. Kirtley , Shai Birmaher , Veeraraju Vanapalli , Karthikeyan Sampath , Deepak Ghiya , Perumallu Vukanti , Rajendra Mahadeorao Wankhade , Pradeep Naik
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.
-
公开(公告)号：US11466583B2
公开(公告)日：2022-10-11
申请号：US16673293
申请日：2019-11-04
Applicant: General Electric Company
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.
-
Patent Agency Ranking
公开(公告)号：US11193390B2
公开(公告)日：2021-12-07
申请号：US17062876
申请日：2020-10-05
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Thomas Ory Moniz , Satish Kumar Yadav , Ambika Shivamurthy , Praveen Sharma , Bhujabal Prashant Mahadeo
Abstract: A support assembly for a bearing of a gas turbine engine including a spring finger ring positioned radially exterior to an outer race of the bearing. The spring finger ring includes an outer ring positioned radially exterior to the outer ring, an inner ring positioned radially interior to the outer ring, and a plurality of spring fingers extending between the inner and outer rings. One or more spring fingers configured as two-sided spring fingers including a first ligament coupled to the outer ring and extending at a first circumferential angle to a first radial bumper proximate to the inner ring and a second ligament coupled to the inner ring and extending at a different second circumferential angle to a second radial bumper proximate to the outer ring. The first and second radial bumpers define first and second radial gaps between the bumpers and the inner and outer rings, respectively.
-
公开(公告)号：US11105223B2
公开(公告)日：2021-08-31
申请号：US16535254
申请日：2019-08-08
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 , F03G7/06 , F02C7/06 , F16C27/04 , F16C35/077 , F16C19/26 , F16C19/06
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.
-
公开(公告)号：US20210040865A1
公开(公告)日：2021-02-11
申请号：US16535254
申请日：2019-08-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Shivam Mittal , Bhujabal Prashant Mahadeo , Weize Kang , Richard Schmidt
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.
-
公开(公告)号：US20210040864A1
公开(公告)日：2021-02-11
申请号：US16535231
申请日：2019-08-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Bhujabal Prashant Mahadeo , Shivam Mittal
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：US10823002B2
公开(公告)日：2020-11-03
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.
-
-
-
-
-
-
-
-
-
Search Results
329
records
(took 0.023 seconds)
