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公开(公告)号：US20180306440A1
公开(公告)日：2018-10-25
申请号：US15569523
申请日：2015-06-24
CPC分类号： F23M5/085 , F01D9/023 , F23R3/002 , F23R2900/03045
摘要： A cooling ring (102) of a combustor basket system (110) has a transition zone 108 that extends to a cooling channel (106) at a cooling channel entrance (104). The transition zone (108) has the substantially the same material strength throughout the length of the transition zone (108). By having the same material strength throughout the length of the transition zone (108), the cooling ring (102) is able to withstand greater stresses than previously used cooling rings. One way in which this is accomplished is by having a uniform thickness.
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公开(公告)号：US20170211810A1
公开(公告)日：2017-07-27
申请号：US15328525
申请日：2014-08-14
CPC分类号： F23R3/283 , F23D11/38 , F23D14/76 , F23D14/78 , F23D2214/00 , F23D2900/00018 , F23R3/36
摘要： A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. A nozzle cap (50) may be disposed at a downstream end of the nozzle. A heat shield (60) is mounted onto the nozzle cap. A plurality of cooling channels (62) is arranged between a forward face of the nozzle cap and a corresponding back side of the heat shield. The plurality of cooling channels may be arranged to discharge cooling air over a forward face of an atomizer assembly in the multi-functional fuel nozzle.
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公开(公告)号：US20170211805A1
公开(公告)日：2017-07-27
申请号：US15329639
申请日：2014-08-14
发明人： Stephen A. Ramier , Vinayak V. Barve , Richard L. Thackway , Charalambos Polyzopoulos , Khalil Farid Abou-Jaoude
CPC分类号： F23C1/08 , F23D11/24 , F23L7/002 , F23L2900/07008 , F23R3/28
摘要： A nozzle cap (82) is disposed at a downstream end of the nozzle. The nozzle cap includes a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis (18) of the nozzle. The downstream portion of the fluid-injecting lance includes a centrally-located atomizer (80) to form a first atomized ejection cone. An array of atomizers (84) is disposed in the nozzle cap. The array of atomizers is circumferentially disposed about the longitudinal axis of the lance. The array of atomizers may be positioned radially outwardly relative to the centrally-located atomizer to form an array of respective second atomized ejection cones.
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公开(公告)号：US10132240B2
公开(公告)日：2018-11-20
申请号：US15328228
申请日：2014-08-14
发明人： Stephen A. Ramier , Vinayak V. Barve , Richard L. Thackway , Charalambos Polyzopoulos , Khalil Farid Abou-Jaoude
摘要： A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. An annular fuel-injecting lance (12) may include a first fluid circuit (14) and a second fluid circuit (16). One of the first and second fluid circuits during a liquid fuel operating mode of the combustion turbine engine may convey a liquid fuel. The other of the first and second fluid circuits may convey a selectable non-fuel fluid. An atomizer (30) is disposed at the downstream end of the lance. The atomizer may have a first ejection orifice (32) responsive to the first fluid circuit to form a first atomized ejection cone (34), and a second ejection orifice (36) responsive to the second fluid circuit to form a second atomized ejection cone (38). The first and second ejection cones (34, 38) formed with the atomizer may be concentric cones that intersect with one another over a predefined angular range.
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公开(公告)号：US10125991B2
公开(公告)日：2018-11-13
申请号：US15328525
申请日：2014-08-14
摘要： A multi-functional fuel nozzle (10) for a combustion turbine engine is provided. A nozzle cap (50) may be disposed at a downstream end of the nozzle. A heat shield (60) is mounted onto the nozzle cap. A plurality of cooling channels (62) is arranged between a forward face of the nozzle cap and a corresponding back side of the heat shield. The plurality of cooling channels may be arranged to discharge cooling air over a forward face of an atomizer assembly in the multi-functional fuel nozzle.
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公开(公告)号：US09958152B2
公开(公告)日：2018-05-01
申请号：US15329639
申请日：2014-08-14
发明人： Stephen A. Ramier , Vinayak V. Barve , Richard L. Thackway , Charalambos Polyzopoulos , Khalil Farid Abou-Jaoude
CPC分类号： F23C1/08 , F23D11/24 , F23L7/002 , F23L2900/07008 , F23R3/28
摘要： A nozzle cap (82) is disposed at a downstream end of the nozzle. The nozzle cap includes a bore arranged to accommodate a downstream portion of a fluid-injecting lance that extends along a longitudinal axis (18) of the nozzle. The downstream portion of the fluid-injecting lance includes a centrally-located atomizer (80) to form a first atomized ejection cone. An array of atomizers (84) is disposed in the nozzle cap. The array of atomizers is circumferentially disposed about the longitudinal axis of the lance. The array of atomizers may be positioned radially outwardly relative to the centrally-located atomizer to form an array of respective second atomized ejection cones.
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公开(公告)号：US20190309952A1
公开(公告)日：2019-10-10
申请号：US16317715
申请日：2016-09-27
IPC分类号： F23R3/34
摘要： A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zone. The feeding of the fuel through the air scoop allows atomization of the fuel. The mixture can then enter the secondary combustion zone and mix with the products from the first combustion zone.
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公开(公告)号：US20170227228A1
公开(公告)日：2017-08-10
申请号：US15502638
申请日：2014-09-05
发明人： Daniel W. Garan , Richard L. Thackway , David P. Holzapfel , Stephen A. Ramier , Charalambos Polyzopoulos , Kevin J. Spence , Joseph Scott Markovitz
摘要： A cross-flame duct (100) for connecting adjacent combustors (1, 2) together in a gas turbine to guard against flameout conditions within the combustors (1, 2), whereby the cross-flame duct (100) may include first and second ducts (102, 106) forming a slip joint to prevent stress from developing within the cross-flame duct (100) is disclosed. The cross-flame duct (100) remains flexible during turbine operation due to the slip joint, thereby preventing damaging thermal and mechanical stresses from developing within the cross-flame duct (100) and enhancing the useful life of the cross-flame duct (100) and associated components. The first and second ducts (102, 106) may also include cooling chambers (138, 156, 174) positioned between outer sleeves (122, 140) and inner housings (128, 146) and maintained with one or more standoffs (134, 152, 170) to reduce thermal stress and gradients or prevent material loss due to overheating or burning. The cooling chambers (138, 156, 174) may be supplied with cooling fluids via one or more fluid ports (176) extending through the outer sleeves (122, 140) enabling air to flow through the cooling chambers (1138, 156, 174) and into the combustors (1, 2).
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公开(公告)号：US20150345795A1
公开(公告)日：2015-12-03
申请号：US14294526
申请日：2014-06-03
摘要： A fuel nozzle assembly (10) is presented for a gas turbine engine (12). The fuel nozzle assembly (10) includes a rocket unit (14) and a swirler (16) with an aft end (18) in threaded engagement with a forward end (20) of the rocket unit (14). The fuel nozzle assembly (10) may include an oil tip (36) including a clocking feature with a mechanical constraint to orient the oil tip (36) at a predetermined angular orientation (42) relative to the swirler (16). The fuel nozzle assembly (10) may include one or more gas stage inlets (13, 15), one or more oil stage inlets (17, 19), and a flexible hose (26) to direct the oil to a plurality of rocket units (14).
摘要翻译： 为燃气涡轮发动机（12）提供燃料喷嘴组件（10）。 燃料喷嘴组件（10）包括具有与火箭单元（14）的前端（20）螺纹接合的后端（18）的火箭单元（14）和旋流器（16）。 燃料喷嘴组件（10）可以包括油嘴（36），其包括具有机械约束的计时特征，以使油嘴（36）相对于旋流器（16）以预定的角度取向（42）定向。 燃料喷嘴组件（10）可以包括一个或多个气台入口（13,15），一个或多个油台入口（17,19）和柔性软管（26），以将油引导到多个火箭单元 （14）。
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公开(公告)号：US11181273B2
公开(公告)日：2021-11-23
申请号：US16317715
申请日：2016-09-27
IPC分类号： F23R3/34
摘要： A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zone. The feeding of the fuel through the air scoop allows atomization of the fuel. The mixture can then enter the secondary combustion zone and mix with the products from the first combustion zone.
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