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公开(公告)号：US20210262363A1
公开(公告)日：2021-08-26
申请号：US16798506
申请日：2020-02-24
摘要： An exhaust plume control structure includes a mounting member configured to mount to an exhaust flow source. At least one divider member operatively couples to the mounting member and is positioned in fluid communication with the exhaust flow source. A diverter member operatively couples to the divider member(s) to radially direct an initial exhaust flow from the exhaust plume towards the divider member(s). Each divider member separates the initial exhaust flow into a plurality of exhaust flows. A number of peripherally spaced, radially extending vanes may also separate the exhaust flows into additional exhaust flows. Each of the additional exhaust flows has a slower velocity than the initial exhaust flow. The structure reduces exhaust flow velocity and may provide back pressure to the initial exhaust flow. A power generating plant including the structure is also disclosed.
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公开(公告)号：US20210231021A1
公开(公告)日：2021-07-29
申请号：US15734947
申请日：2019-06-07
摘要： An exhaust apparatus for a gas turbine includes an annular duct with struts extending from an outer duct-wall to an inner duct-wall of the annular duct. Each strut is encapsulated in a respective strut shield. An interface of the strut shield with a respective duct-wall includes a collar extending along a partial length of the perimeter of the strut shield at the respective interface. The collar includes a first section extending radially and aligned with the strut shield, and a second section oriented at an angle to the first section and aligned with the respective duct-wall. The first section is attached to the strut shield along a first joint and the second section is attached to the respective duct-wall along a second joint. An intersection of the first and second sections is formed by a smooth curve defined by a radius configured to distribute stresses at the respective interface.
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公开(公告)号：US20210190000A1
公开(公告)日：2021-06-24
申请号：US16721157
申请日：2019-12-19
申请人： The Boeing Company
发明人： Luke D. Torjesen
摘要： Flexible aft cowls are disclosed. In some examples, an aircraft engine having a flexible aft cowl is disclosed. In some examples, the aircraft engine comprises an aft cowl having a flexible portion defining a throat area adjacent an engine core nozzle of the aircraft engine. In some examples, the flexible portion to move radially between a first radial position in response to pressure within a nacelle not exceeding a pressure threshold and a second radial position in response to pressure within the nacelle exceeding the pressure threshold. In some examples, the throat area defined by the flexible portion is greater when the flexible portion is in the second radial position than when the flexible portion is in the first radial position.
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公开(公告)号：US11028732B2
公开(公告)日：2021-06-08
申请号：US16561782
申请日：2019-09-05
摘要： An exhaust assembly for use with a gas turbine engine includes an exhaust duct and a damper system coupled to the exhaust duct. The exhaust duct is configured for fluid communication with the gas turbine engine to receive hot exhaust gases produced by the gas turbine engine. The exhaust duct includes a plurality of panels that define an exhaust passageway. The damper system is coupled to one of the plurality of panels and is configured to dampen vibration of the exhaust duct during use of the gas turbine engine.
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公开(公告)号：US10961914B1
公开(公告)日：2021-03-30
申请号：US16948290
申请日：2020-09-11
摘要： A mobile fracking system and methods may include a gas turbine housed at least partially inside a trailer and an exhaust attenuation system configured to receive exhaust gas from the gas turbine. The exhaust attenuation system may include a lower elongated plenum configured to receive exhaust gas from the gas turbine and an upper noise attenuation system that is movably connected relative to a distal end of the lower elongated plenum.
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36.发明申请公开(公告)号：US20210054751A1
公开(公告)日：2021-02-25
申请号：US16982866
申请日：2018-03-27
摘要： A sealing arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.
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公开(公告)号：US10907508B2
公开(公告)日：2021-02-02
申请号：US15013182
申请日：2016-02-02
申请人： ROHR, INC.
发明人： Michael Knight , Fadi Iskander , Narek Geghamyan
摘要： A ceramic matrix composite (“CMC”) center body may be positioned around an austenitic nickel-chromium-based superalloy attachment ring. The attachment ring may be integrally formed with a turbine engine case. The attachment ring may have a greater coefficient of thermal expansion than the center body. A plurality of pins may be inserted through apertures in the center body and coupled to the attachment ring. The pins may slide within the apertures, allowing the attachment ring to expand without applying a load on the center body.
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公开(公告)号：US10815832B2
公开(公告)日：2020-10-27
申请号：US16012396
申请日：2018-06-19
摘要： A turbine exhaust case is provided for a gas turbine engine. This turbine exhaust case includes a first gas turbine engine exhaust case, a second gas turbine engine exhaust case, a strut and a fastener. The second gas turbine engine exhaust case includes a flange and a bracket. The strut is coupled to the first case and the second case. The fastener fastens the flange and the strut. The second gas turbine engine exhaust case is co-axial with the first gas turbine engine exhaust case. The strut contacts the bracket when the engine is powered-on.
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公开(公告)号：US20200318495A1
公开(公告)日：2020-10-08
申请号：US16382930
申请日：2019-04-12
发明人： RABIH KASSAB
IPC分类号： F01D25/30
摘要： A turbine exhaust case (TEC) mixer for an aircraft engine is disclosed. The aircraft engine has an inner shroud, a nacelle, a fan assembly, a compressor assembly and a turbine assembly. The TEC mixer includes struts extending from the mixer and is adapted to connect to the inner shroud at a shroud-strut interface. A plurality of the struts are narrower in a middle portion thereof than at the shroud-strut interface.
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公开(公告)号：US20200277879A1
公开(公告)日：2020-09-03
申请号：US16756384
申请日：2018-10-17
申请人： ABB Turbo Systems AG
发明人： Stephan SENN , Christoph MATHEY
摘要： The invention relates to an exhaust gas turbine, comprising a turbine rotor (12) having a plurality of turbine rotor blades (2) with a turbine rotor blade height H. The exhaust gas turbine further comprises a diffuser arrangement (20) having a transverse diffuser (1) and an exhaust gas collection chamber (9). The transverse diffuser (1) is arranged downstream of the turbine rotor blades (2). The transverse diffuser (1) has a curved diffuser channel (13) which opens into the exhaust gas collection chamber (9) at a diffuser channel outlet (17). A M/H ratio between an axial extension M of the exhaust gas collection chamber (9) and the turbine rotor blade height H has a value of 1.0≤M/H≤4.6 and a P/H ratio between a radial extension P of the diffuser arrangement (20) and the turbine rotor blade height H has a value of 2.7≤P/H≤4.9. A D/H ratio between a radial expansion D of the diffuser channel section (13) and the turbine rotor blade height H has a value of 2.5≤D/H≤3.0 and a R/H ratio between a turbine hub radius R and the turbine rotor blade height H has a value of 1.1≤R/H≤1.5.
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