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公开(公告)号：US20190063749A1
公开(公告)日：2019-02-28
申请号：US15683965
申请日：2017-08-23
发明人： Mark F. Zelesky , Carey Clum
CPC分类号： F23R3/002 , F02C7/12 , F23R3/06 , F23R3/26 , F23R2900/03042
摘要： Combustors and panels for use in combustor sections of gas turbine engines, the panels having a panel body having a first wall with a first sidewall and a second sidewall extending each extending from the first wall in the same direction at edges of the first wall and a plurality of cavity walls arranged between the first sidewall and the second sidewall and extending from the panel in the direction of the first and second sidewalls, wherein a plurality of cooling cavities are defined by the cavity walls, the first wall, and at least one of the first sidewall and the second sidewall, wherein each cooling cavity extends from an inlet hole to an outlet hole, wherein the outlet hole is formed in the first wall.
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公开(公告)号：US20180274786A1
公开(公告)日：2018-09-27
申请号：US15762679
申请日：2016-09-13
CPC分类号： F23R3/44 , F02C7/22 , F05D2220/76 , F05D2240/35 , F23C9/006 , F23C2900/03001 , F23L15/04 , F23R3/005 , F23R3/06 , F23R3/16 , F23R3/20 , F23R3/26 , F23R3/36 , Y02E20/348 , Y02T50/675
摘要： A combustion chamber (18) of a thermodynamic cycle turbine with a recuperator, for electrical energy production, comprising a casing (56) housing a flame tube (64) with a perforated diffuser for passage of the hot compressed air, a primary zone (ZP) that receives part of the hot compressed air flow and where combustion takes place, and a dilution zone (ZD) where the burnt gases from the primary zone mix with the remaining part of the hot compressed air flow, said chamber further comprising an injection means (76) for injecting at least one fuel. The flame tube carries a flame stabilizer (82) comprising perforated diffuser (88), at least one combustion gas recirculation passage (98) and a mixing tube (94).
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公开(公告)号：US10082086B2
公开(公告)日：2018-09-25
申请号：US14653082
申请日：2013-06-04
发明人： Mats Andersson , Alessio Bonaldo
IPC分类号： F02C9/18 , F02C9/48 , F02C9/28 , F02C9/16 , F23R3/26 , F23N3/04 , F23N5/02 , F23N5/24 , F23R3/50 , F02C3/13 , F02C6/08
CPC分类号： F02C9/18 , F02C3/13 , F02C6/08 , F02C9/16 , F02C9/28 , F02C9/48 , F05D2270/0831 , F23N3/042 , F23N5/022 , F23N5/242 , F23N2025/08 , F23N2037/02 , F23N2037/20 , F23N2041/20 , F23R3/26 , F23R3/50
摘要： A method to operate a combustor of a gas turbine is provided. The method includes monitoring the combustion gas temperature by temperature measurements downstream said combustor to measure a respective combustion gas temperature at different locations at respectively equal flow-distances to the burner of the combustion gas, comparing the temperature measurements, opening a valve or increasing the opening position of the valve to control the portion of oxygen containing gas to be tapped off when the comparison reveals that a difference between the temperature measurements exceeds a temperature difference threshold ΔT1.
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公开(公告)号：US10054313B2
公开(公告)日：2018-08-21
申请号：US12832099
申请日：2010-07-08
CPC分类号： F23R3/286 , F23R3/14 , F23R3/26 , F23R3/54 , F23R2900/00013
摘要： A combustor (10) including: a first premix main burner (14) comprising a first swirler airfoil section (38); a second premix main burner (15) comprising a second swirler airfoil section (40); and a supply air reversing region upstream of the premix burners (14), (15). The first swirler airfoil section (38) and the second swirler airfoil section (40) are effective to impart swirl to a first airflow and a second airflow characterized by a same swirl number as the airflows exit respective burners (14), (15). The combustor (10) is effective to generate a first airflow volume through the first premix main burner (14) that is different than a second airflow volume through the second premix main burner (15).
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公开(公告)号：US20180216827A1
公开(公告)日：2018-08-02
申请号：US15417601
申请日：2017-01-27
CPC分类号： F23R3/26 , F02C3/04 , F05D2240/35 , F05D2270/08 , F23R3/283 , F23R2900/00001 , Y02E20/16
摘要： A flow modulator for a fuel nozzle, including: a fixed outer tube, the fixed outer tube including a set of apertures; a movable inner tube concentrically positioned within the fixed outer tube, the movable inner tube including a set of apertures; and a pneumatically actuated component for displacing the movable inner tube within the fixed outer tube to selectively align the set of apertures of the fixed outer tube with the set of apertures of the movable inner tube.
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公开(公告)号：US20180216536A1
公开(公告)日：2018-08-02
申请号：US15876203
申请日：2018-01-22
发明人： Alexander BOGRAD
CPC分类号： F02C7/185 , F02C7/14 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2260/211 , F05D2260/601 , F23R3/005 , F23R3/04 , F23R3/26 , F23R3/46
摘要： Provided is a gas turbine including: a combustor positioned between a compressor and a turbine of a gas turbine; a cooling air discharge unit configured to receive compressed air from the compressor, receive cooling water from a power plant, and discharge cooling air having exchanged heat with the compressed air; and a supply unit configured to supply the cooling air discharged from the cooling air discharge unit to the turbine and the combustor.
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公开(公告)号：US20180149361A1
公开(公告)日：2018-05-31
申请号：US15365420
申请日：2016-11-30
发明人： STEVEN W. BURD
CPC分类号： F23R3/26 , F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/00017 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
摘要： A combustor of a gas turbine engine includes a combustor shell having a diffuser side facing a diffuser chamber and a combustor side facing a combustor chamber. The combustor may include a first combustor panel coupled to the combustor side of the combustor shell and a second combustor panel coupled to the combustor side of the combustor shell. A gap may be defined between the first combustor panel and the second combustor panel and the combustor shell may include a gap impingement hole that is directly open to and is configured to deliver cooling air directly to the gap. In various embodiments, the combustor further includes a throttle plate coupled to the diffuser side of the combustor shell.
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公开(公告)号：US09927123B2
公开(公告)日：2018-03-27
申请号：US14517962
申请日：2014-10-20
发明人： Benjamin F. Hagan
摘要： A fluid transport system for a gas turbine engine includes a plenum configured to provide a fluid, an airfoil having an internal cavity, and a transfer tube arranged to transfer the fluid between the plenum and the internal cavity of the airfoil. The transfer tube includes an inlet, an outlet, a cavity extending from the inlet to the outlet, and at least one partition wall dividing the cavity into multiple flow passages.
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公开(公告)号：US09903588B2
公开(公告)日：2018-02-27
申请号：US14444601
申请日：2014-07-28
IPC分类号： F02C3/34 , F23C9/00 , F23N1/02 , F23R3/00 , F23R3/16 , F23R3/26 , F23C9/08 , F02C1/00 , F23R3/40
CPC分类号： F23N1/02 , F02C1/005 , F02C3/34 , F05D2260/61 , F05D2270/08 , F05D2270/083 , F23C9/00 , F23C9/08 , F23C2202/20 , F23C2202/30 , F23N2021/12 , F23N2041/20 , F23R3/002 , F23R3/16 , F23R3/26 , F23R3/40 , Y02E20/16 , Y02T50/677
摘要： In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.
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公开(公告)号：US09845731B2
公开(公告)日：2017-12-19
申请号：US14749438
申请日：2015-06-24
发明人： Michael J. Birnkrant , Carey Clum
IPC分类号： G05D23/02 , F02C7/18 , F01D25/12 , F01D5/18 , F02C7/20 , F01D9/04 , F01D11/08 , F02C7/25 , F01D11/14 , F01D11/24 , F23R3/00 , F23R3/06 , F23R3/26
CPC分类号： F02C7/20 , F01D5/182 , F01D5/186 , F01D9/041 , F01D11/08 , F01D11/14 , F01D11/24 , F01D25/12 , F02C7/18 , F02C7/25 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2240/55 , F05D2260/202 , F05D2300/134 , F05D2300/16 , F05D2300/5021 , F05D2300/50212 , F23R3/002 , F23R3/06 , F23R3/26 , F23R2900/03042 , G05D23/02 , G05D23/021 , G05D23/022
摘要： Systems and methods are disclosed herein for passively managing cooling air in a gas turbine engine. A cooling air supply line may supply cooling air to a component in the gas turbine engine. A metering coupon may have a negative coefficient of thermal expansion. The metering coupon may allow more airflow through the metering coupon and through the component in response to an increase in temperature.
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