-
公开(公告)号：US20240291008A1
公开(公告)日：2024-08-29
申请号：US18404083
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: H01M8/0612 , F02C7/22
CPC classification number: H01M8/0618 , F02C7/22 , H01M8/0625 , H01M2250/20
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.
-
公开(公告)号：US12270340B2
公开(公告)日：2025-04-08
申请号：US18404364
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: F02C7/22 , H01M8/04089 , H01M8/04111 , H01M8/0612
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly having a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both.
-
公开(公告)号：US12261334B2
公开(公告)日：2025-03-25
申请号：US18404083
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: H01M8/0612 , F02C7/22
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell; a fuel delivery assembly including a fuel line; and a reformer in communication with the fuel line and the output products from the fuel cell during operation of the gas turbine engine to convert a fuel flow through the fuel line to a hydrogen rich gas.
-
公开(公告)号：US20240287938A1
公开(公告)日：2024-08-29
申请号：US18404322
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: F02C7/232 , H01M8/04014 , H01M8/04089 , H01M8/04111 , H01M8/0612
CPC classification number: F02C7/232 , H01M8/04014 , H01M8/04097 , H01M8/04111 , H01M8/0618 , H01M2250/20
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell, an inlet line in fluid communication with an inlet of the fuel cell, and an output products line in fluid communication with an outlet of the fuel cell for receiving output products from the fuel cell, wherein the inlet line is positioned to be in thermal communication with the output products during operation of the gas turbine engine.
-
Patent Agency Ranking
公开(公告)号：US20240286754A1
公开(公告)日：2024-08-29
申请号：US18404258
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: B64D37/32 , B64D27/355
CPC classification number: B64D37/32 , B64D27/355
Abstract: A system for an aircraft including: a fuel tank defining an interior; and a fuel cell assembly having a fuel cell defining an air outlet, wherein the air outlet of the fuel cell is in airflow communication with the interior of the fuel tank for providing an inerting airflow from the fuel cell to the interior of the fuel tank to reduce an oxygen content of the interior of the fuel tank.
-
公开(公告)号：US20240291000A1
公开(公告)日：2024-08-29
申请号：US18404188
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: H01M8/04111 , H01M8/04014 , H01M8/04701 , H01M8/04746
CPC classification number: H01M8/04111 , H01M8/04022 , H01M8/04731 , H01M8/04761
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly including a fuel cell positioned aft of the combustor of the turbomachine, defining an exhaust in fluid communication with a location forward of the fuel cell to provide output products to the location, or both.
-
公开(公告)号：US20240287936A1
公开(公告)日：2024-08-29
申请号：US18404364
申请日：2024-01-04
Applicant: General Electric Company
Inventor： Honggang Wang , Brandon Wayne Miller , Michael Anthony Benjamin , Richard L. Hart , Randy M. Vondrell , Ryan St. Pierre
IPC: F02C7/22 , H01M8/04089 , H01M8/04111 , H01M8/0612
CPC classification number: F02C7/22 , H01M8/04097 , H01M8/04111 , H01M8/0618
Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section arranged in serial flow order, the turbomachine further including an outer casing and, during operation of the gas turbine engine, an exhaust gas flow from the turbine section; and a fuel cell assembly positioned within the outer casing of the turbomachine, the fuel cell assembly having a fuel cell defining an inlet positioned to receive a portion of the exhaust gas flow, an outlet positioned to provide output products directly to the exhaust gas flow, or both
-
公开(公告)号：US12037943B2
公开(公告)日：2024-07-16
申请号：US17961667
申请日：2022-10-07
Applicant: General Electric Company
Inventor： Ryan St. Pierre , Kevin Edward Hinderliter , Michael Vadnais
CPC classification number: F02C7/10 , F02C3/04 , F05D2220/323 , F05D2260/213
Abstract: A gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath. The gas turbine engine also includes a turbine rear frame extending through the core air flowpath at a location downstream of the turbine section and defining a leading edge within the core air flowpath. The gas turbine engine also includes a waste heat recovery system operable to separate, at or upstream of the leading edge of the turbine rear frame, a core airflow exiting the turbine section into a primary exhaust airflow and a waste heat recovery airflow. The waste heat recovery system comprises a heat source exchanger positioned to receive the waste heat recovery airflow.
-
公开(公告)号：US20240117766A1
公开(公告)日：2024-04-11
申请号：US17961667
申请日：2022-10-07
Applicant: General Electric Company
Inventor： Ryan St. Pierre , Kevin Edward Hinderliter , Michael Vadnais
CPC classification number: F02C7/10 , F02C3/04 , F05D2220/323 , F05D2260/213
Abstract: A gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath. The gas turbine engine also includes a turbine rear frame extending through the core air flowpath at a location downstream of the turbine section and defining a leading edge within the core air flowpath. The gas turbine engine also includes a waste heat recovery system operable to separate, at or upstream of the leading edge of the turbine rear frame, a core airflow exiting the turbine section into a primary exhaust airflow and a waste heat recovery airflow. The waste heat recovery system comprises a heat source exchanger positioned to receive the waste heat recovery airflow.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.016 seconds)
