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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：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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3.发明申请公开(公告)号：US20170167729A1
公开(公告)日：2017-06-15
申请号：US15325672
申请日：2014-07-30
CPC分类号： F23R3/005 , F02C7/18 , F23R3/002 , F23R3/06 , F23R2900/03043
摘要： A hot gas path cooling system (10) for a combustor of a gas turbine engine, whereby the cooling system (10) is positioned within a combustor basket (18) is disclosed. The cooling system (10) may include a platefin cooling system (24) formed from a platefin member (26) positioned radially inward from an outer wall (28) forming a combustor basket (18). At least first and second cooling circuits (34, 36) may be formed between the platefin member (26) and the combustor basket (18) and may be separated from each other by a first rib section (38). The second cooling circuit (36), thus, may be positioned downstream from the first cooling circuit (34) and may receive fresh cooling fluid through one or more inlets (52), not from the first cooling circuit (34). As such, the downstream second cooling circuit (36) may be cooled similarly to the first cooling circuit (34).
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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：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：US10533750B2
公开(公告)日：2020-01-14
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 for connecting adjacent combustors together in a gas turbine to guard against flameout conditions within the combustors, whereby the cross-flame duct includes first and second ducts forming a slip joint to prevent stress from developing within the cross-flame duct is disclosed. The cross-flame duct remains flexible during turbine operation due to the slip joint, thereby preventing damaging thermal and mechanical stresses from developing within the cross-flame duct and enhancing the useful life of the cross-flame duct and associated components. The first and second ducts include cooling chambers positioned between outer sleeves and inner housings and maintained with one or more standoffs to reduce thermal stress and gradients or prevent material loss due to overheating or burning. The cooling chambers are supplied with cooling fluids via one or more fluid ports extending through the outer sleeves enabling air to flow through the cooling chambers and into the combustors.
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公开(公告)号：US20170204785A1
公开(公告)日：2017-07-20
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
CPC分类号： F02C3/30 , F02C7/22 , F23C2900/07021 , F23D11/108 , F23D17/002 , F23D2204/10 , F23L7/002 , F23R3/286 , F23R3/36
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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