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公开(公告)号：US10041377B2
公开(公告)日：2018-08-07
申请号：US14951090
申请日：2015-11-24
发明人： Deepesh Dinesh Nanda , Robert Jamiołkowski , Robert Jacek Zreda , Eric Yves Bracquemart , Daniel Tomasz Ożga
摘要： A system includes a diffuser configured to receive exhaust gas from a turbine. The diffuser includes an outer barrel, an inner barrel, a seal interface, an outer aft plate, an inner aft plate, and poles. An upstream end of the outer barrel includes an upstream lip interfacing with a downstream lip of an outer wall of the turbine outlet, forming a lap joint. The outer barrel includes a plurality of axial segments disposed between the upstream end of the outer barrel and the outer aft plate, and the axial segments. The inner barrel includes a plurality of axial segments disposed between an upstream end of the inner barrel and the seal interface. The seal interface includes a groove configured to receive the inner aft plate. The poles are spaced about the turbine axis and couple an end of the outer aft plate to an end of the inner aft plate.
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公开(公告)号：US10036283B2
公开(公告)日：2018-07-31
申请号：US15152264
申请日：2016-05-11
发明人： Deepesh Dinesh Nanda , Robert Jamiolkowski , Robert Jacek Zreda , Eric Yves Bracquemart , Daniel Tomasz Ozga
CPC分类号： F01D25/30 , F01D25/24 , F02C3/04 , F05D2220/32 , F05D2230/64 , F05D2240/40 , F05D2260/33 , F05D2260/36
摘要： A method includes inserting axially a radially interior surface of an aft plate assembly into a circumferential groove of an inner barrel of a diffuser section of a gas turbine, where the aft plate assembly is inserted into a first circumferential orientation relative to the circumferential groove, and the circumferential groove is disposed on a radially exterior surface of the inner barrel. The method includes rotating the aft plate assembly circumferentially within the circumferential groove from the first circumferential orientation to a second circumferential orientation, where the inner barrel is configured to axially retain the aft plate assembly when the aft plate assembly is disposed in the second circumferential orientation.
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公开(公告)号：US20180202319A1
公开(公告)日：2018-07-19
申请号：US15744182
申请日：2015-08-12
摘要： A diffuser for a turbine engine includes a first wall that extends circumferentially about a centerline axis of the turbine engine. The diffuser also includes a second wall that extends circumferentially about the centerline axis. At least a portion of the second wall is positioned radially outwardly from at least a portion of the first wall. A flow path is defined by the first wall and the second wall. The flow path extends from an inlet configured to receive an axial flow of a fluid, to a circumferentially extending outlet configured to emit the fluid in a substantially radial direction. The outlet extends asymmetrically about the centerline axis.
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公开(公告)号：US10006309B2
公开(公告)日：2018-06-26
申请号：US14498201
申请日：2014-09-26
CPC分类号： F01D25/30 , F01D9/02 , F01D25/28 , F02C7/20 , F02K1/04 , F05B2250/711 , F05B2250/712 , F05B2250/713 , F05D2240/90
摘要： An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.
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公开(公告)号：US09982564B2
公开(公告)日：2018-05-29
申请号：US14654953
申请日：2013-12-11
CPC分类号： F01D25/162 , F01D25/145 , F01D25/26 , F01D25/30 , F05D2220/32 , F05D2230/00 , F05D2240/15 , F05D2260/231 , F05D2300/171 , F05D2300/175 , Y10T29/49321
摘要： A structural case assembly comprises a frame, fairing and heat shield. The frame is fabricated from a material having a temperature limit below an operating point of a gas turbine engine, and comprises an outer ring, an inner ring and a plurality of struts extending therebetween to define a flow path. The fairing is fabricated from a material having a temperature limit above the operating point of the gas turbine engine, and comprises a ring-strut-ring structure that lines the flow path. The heat shield is disposed between the frame and the fairing to inhibit radiant heat transfer therebetween. The heat shield may block all line-of-sight between the fairing and the frame. The frame may be produced from CA-6NM alloy. A method for designing a turbine case structure includes selecting a frame material having a temperature limit below the operating point of an engine.
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公开(公告)号：US09976479B2
公开(公告)日：2018-05-22
申请号：US14969142
申请日：2015-12-15
发明人： Alston Ilford Scipio , Sanji Ekanayake , Jason Brian Shaffer , Joseph Philip Klosinski , George Vargese Mathai
CPC分类号： F02C6/08 , F01D25/305 , F01K17/02 , F01K17/06 , F01K23/10 , F02C3/04 , F02C6/18 , F02C7/141 , H02K7/1823 , Y02E20/14 , Y02E20/16
摘要： A power plant includes a compressor, a combustor downstream from the compressor and a turbine disposed downstream from the combustor. The compressor includes a compressor extraction port. The turbine includes a turbine extraction port that is in fluid communication with a hot gas path of the turbine and which provides a flow path for a stream of combustion gas to flow out of the turbine. An exhaust duct is disposed downstream from the turbine and receives exhaust gas from the turbine. A static mixer coupled to the turbine extraction port and to the compressor extraction port cools the stream of combustion gas upstream from the exhaust duct. The cooled combustion gas flows into the exhaust duct at a higher temperature than the exhaust gas and mixes with the exhaust gas within the exhaust duct to provide a heated exhaust gas mixture to a heat exchanger downstream from the exhaust duct.
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87.发明申请公开(公告)号：US20180135556A1
公开(公告)日：2018-05-17
申请号：US15803269
申请日：2017-11-03
CPC分类号： F02K1/386 , F01D25/005 , F01D25/30 , F02K1/48 , F05D2300/6033 , F05D2300/6034 , Y02T50/672
摘要： It is provided a mixer for an engine, that for the mixing of fluid flows from a primary flow channel and a secondary flow channel of the engine, respectively has multiple first and second guide elements that alternate along a circumferential direction and extend along a central axis, wherein the first guide elements are formed in a diffusor-like manner with at least one radially outwardly extending section, and the second guide elements are formed in a nozzle-like manner with at least one radially inwardly extending section, and the mixer is made of a composite material with at least two separate material layers. The at least two material layers are arranged with their edges along the central axis in an overlapping manner and/or edge to edge, and namely in an area of the mixer in which the first and second guide elements are provided.
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公开(公告)号：US20180135515A1
公开(公告)日：2018-05-17
申请号：US15354514
申请日：2016-11-17
发明人： Eric YuHang Fung , Richard Lynn Loud , Valery Ivanovich Ponyavin , Dinesh Venugopal Setty , Dariusz Nowak , Michal Tadeusz Bialkowski
CPC分类号： F02C7/045 , F05D2220/32 , F05D2230/60 , F05D2250/283 , F05D2260/96
摘要： An acoustic treatment assembly includes a fluid passage and a first panel disposed within the fluid passage. Additionally, at least a portion of a fluid flow through the acoustic treatment assembly is configured to flow across a first micro-perforated surface of the first panel. Further, the first panel includes at least one module, and each module of the at least one module includes the first micro-perforated surface and a respective back surface offset from the first micro-perforated surface opposite the fluid flow across the first micro-perforated surface. The first micro-perforated surface and the back surface form a first cavity configured to promote resonance within a first frequency range of the fluid flow.
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89.发明授权公开(公告)号：US09951656B2
公开(公告)日：2018-04-24
申请号：US14493993
申请日：2014-09-23
发明人： Wuyin Wang , Vasileios Stefanis , Julie Clavier , Mirco Colombo , Felix Guethe
IPC分类号： F01D25/30 , F02C3/28 , F02C6/18 , F01N3/08 , F01N5/02 , F01N13/00 , F02C6/04 , F02C7/14 , F02C7/16
CPC分类号： F01D25/30 , F01N3/08 , F01N5/02 , F01N13/002 , F02C3/28 , F02C6/04 , F02C6/18 , F02C7/14 , F02C7/16 , F05D2220/32 , F05D2270/082 , Y02P80/154
摘要： The invention relates to a method for operating a gas turbine system, wherein the gas turbine system includes a compressor, a combustor, a heat recovery steam generator, a scrubber, a direct contact cooler. The method includes introducing the scrubbing fluid discharged from the scrubber into the direct contact cooler, contacting the scrubbing fluid in the direct contact cooler with the exhaust gas discharged from the heat recovery steam generator in order to remove a portion of nitrogen oxide therefrom; feeding the exhaust gas discharged from the direct contact cooler into the compressor. With the technical solution of the present invention, nitrogen oxide in the exhaust gas is reduced to a certain extent by means of used scrubbing fluid from the scrubber. This solution may improve the efficiency in reduction of nitrogen oxide with a simple and feasible manner.
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公开(公告)号：US09945251B2
公开(公告)日：2018-04-17
申请号：US14443818
申请日：2013-12-17
发明人： William Yeager , John S. Tu
CPC分类号： F01D25/14 , F01D9/065 , F01D25/162 , F01D25/24 , F01D25/30 , F02C7/12 , F02C7/20 , F05D2250/185 , F05D2260/20 , Y02T50/675
摘要： Cooling a turbine exhaust case (TEC) employed in an industrial gas turbine engine includes supplying cooling airflow from an outer diameter (OD) to an inner diameter (ID) cavity, supplying a secondary airflow having a pressure greater than the pressure of the cooling airflow to the ID cavity for mixing with the cooling airflow to provide a mixed airflow, and directing the mixed airflow in a serpentine cooling path that includes first directing the mixed airflow radially outward via hollow struts to an OD cavity, then radially inward via hollow fairings that surround the hollow struts.
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