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公开(公告)号：US12104529B2
公开(公告)日：2024-10-01
申请号：US18533447
申请日：2023-12-08
申请人： BAE SYSTEMS plc
发明人： James William Spain
摘要： A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).
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公开(公告)号：US11846232B2
公开(公告)日：2023-12-19
申请号：US17412934
申请日：2021-08-26
发明人： Brock Alan Forrest
摘要： The present disclosure provides systems and methods for power production. In particular, the systems and methods utilize the addition of heat to an expanded turbine exhaust stream in order to increase the available quantity of heat for recuperation and use therein for heating a compressed carbon dioxide stream for recycle back to a combustor of the power production system and method.
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公开(公告)号：US20230076757A1
公开(公告)日：2023-03-09
申请号：US17470032
申请日：2021-09-09
发明人： Jeffrey Douglas Rambo , Brandon Wayne Miller , William Joseph Bowden , Matthew Thomas Beyer , Michael John Simonetti
IPC分类号： F02C7/10
摘要： A gas turbine engine having a waste heat recovery system is provided. The 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 exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.
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公开(公告)号：US20230003170A1
公开(公告)日：2023-01-05
申请号：US17363155
申请日：2021-06-30
发明人： Gurudatta Srinivasa Murthy Sirigere , Gordon Tajiri , Dattu Guru Venkata Jonnalagadda , Rajapriyan Rajendran , Udaya Bhaskar Pamidimarri
摘要： An electroformed heat exchanger suitable for use between rotating blades and seals in a stationary casing of a turbine engine. The heat exchanger comprising a non-electroformed carrier plate having a radial outer surface and a radial outer surface, an electroformed duct provided along the radial outer surface, an electroformed rail provided on the radial inner surface, and an electroformed stiffener formed by a portion of the electroformed duct and the electroformed rail.
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公开(公告)号：US11378010B2
公开(公告)日：2022-07-05
申请号：US16830470
申请日：2020-03-26
发明人： John T. Schmitz
IPC分类号： F02C7/18 , B23P15/26 , F02C7/14 , F28F7/02 , F02C7/10 , B22F5/00 , B33Y80/00 , F28F13/08 , F28D21/00 , F28D1/02
摘要： A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.
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公开(公告)号：US20220120515A1
公开(公告)日：2022-04-21
申请号：US17151534
申请日：2021-01-18
发明人： Joseph Borghese , Quang Do , David Berukhim , Rafael Maldonado
摘要： A heat exchanger includes a shell housing a plurality of tubes and defining an exhaust fluid flow path within a first volume enclosed by the shell. The outer surfaces of the plurality of tubes are in fluid communication with the exhaust fluid flow path. The heat exchanger includes a cap attached to a first end of the shell and defining a second volume. A header is configured to separate the first volume from the second volume, flex with thermal expansion, and define tube inlet and outlet positions. The tube inlets and outlets are in fluid communication with a source fluid flow path, and each tube is substantially U-shaped and defines a flow path of the source fluid within the exhaust fluid flow path. The heat exchanger includes at least one longitudinal flow baffle within the shell configured to reduce an amount of exhaust fluid that may bypass the tubes.
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公开(公告)号：US11162422B2
公开(公告)日：2021-11-02
申请号：US16328764
申请日：2017-07-11
摘要： The present invention relates to a combustion chamber (10) of a turbine, in particular a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, in particular electrical energy, comprising a casing (12) with an injection means (52) for injecting at least one fuel, and a hot compressed air intake (32), said casing housing a flame tube (22) with a perforated diffuser (26) for the passage of the hot compressed air and the fuel, and a flame stabiliser (54). According to the invention, the chamber comprises an air deflector (36) arranged facing the hot compressed air intake (32) in order to circulate this hot air in a single axial direction from this intake.
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公开(公告)号：US20210324806A1
公开(公告)日：2021-10-21
申请号：US17269127
申请日：2019-08-19
发明人： Marco De Later , Victor Kornilov , Paul Smeets , Ilian Doutchev
摘要： A fuel/air supply device including a fuel supply arrangement designed to convey fuel to a fuel outlet of the fuel/air supply device, a primary air supply arrangement designed to convey air to an air outlet of the fuel/air supply device, and a secondary air supply arrangement connecting the primary air supply arrangement to the fuel supply arrangement at a position upstream of a fuel compressor that is included in the fuel supply arrangement. The secondary air supply arrangement includes an air conduit that has a restricted portion for defining a relatively small air passage in the air conduit, and can be used for realizing a fuel/air mixture of low calorific value if so desired on the basis of a supply of air to the fuel without needing complex control measures.
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公开(公告)号：US20210277827A1
公开(公告)日：2021-09-09
申请号：US16813491
申请日：2020-03-09
发明人： Douglas David Dierksmeier , Douglas Boyd , Douglas J. Snyder , Graham Burkholder , William Barry Bryan
IPC分类号： F02C7/10
摘要： A system includes a housing for a gas turbine engine, and a fan disposed in the housing to rotate coaxially with a gas turbine included in the housing. The system also includes an inlet guide vane disposed in the housing in axial alignment with the fan and configured to have an open position where a first flow of air is received by the fan through the inlet guide vane, and a closed position where airflow through the inlet guide vane is obstructed. The system further includes a heat exchanger disposed in a supply passage in fluid communication with a second flow of air received by the fan. The second flow of air is received by the fan via the supply passage with the inlet guide vane in the open position or in the closed position.
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公开(公告)号：US20210246827A1
公开(公告)日：2021-08-12
申请号：US16972870
申请日：2019-06-07
摘要： The invention relates to an aircraft propulsion system, comprising a main transmission unit (12) and at least two turbojet engines connected to the main transmission unit (12), respectively a first turbojet engine (14a) and a second turbojet engine (14b), each turbojet engine comprising a free turbine (24a, 24b), characterized in that the first turbojet engine (14a) comprises a heat exchanger (30) configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer (28a, 28b) configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine (14a) when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger (30).
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