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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：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：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：US20180229298A1
公开(公告)日：2018-08-16
申请号：US15388105
申请日：2016-12-22
摘要： Casting method and cast manifold are provided. The method allows configuring conduits, such as conduits (46, 48) in a fuel feed boss (20) and/or a base rocket (13), which are part of the manifold for removing a ceramic core (44) from the cast without forming extraneous holes in the body of the manifold. Absence of such extraneous holes in turn allows eliminating sealing plugs and welds, which otherwise would be needed for sealing the extraneous holes.
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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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7.发明申请公开(公告)号：US20180230910A1
公开(公告)日：2018-08-16
申请号：US15388133
申请日：2016-12-22
CPC分类号： F02C7/222 , B22D17/24 , B22D25/02 , B22D29/002 , B33Y80/00 , F05D2230/21 , F23R3/283 , F23R2900/00017 , F23R2900/00018
摘要： A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) in a combustor of a gas turbine engine is provided. The fuel manifold includes stage fuel galleries (16, 18), and fuel feed bosses (20, 22) may be configured to connect to respective tubes arranged to deliver gas fuel to the stage fuel galleries (16. 18). Fuel feed bosses (20, 22) are integrally formed with base support structure (12) and this allows the body of fuel manifold (10) to be free of weld joints for affixing the fuel feed boss to the base support structure.
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8.发明申请公开(公告)号：US20180179957A1
公开(公告)日：2018-06-28
申请号：US15388155
申请日：2016-12-22
摘要： A fuel manifold (10) configured to form a base support structure (12) to support a plurality of fuel nozzles (14) including a pilot fuel nozzle is provided. A restraining element (30) is arranged in the base support structure (12) to support the pilot fuel nozzle. Restraining element (30) is integrally formed with the base support structure. The restraining element being integrally formed with the base support structure is effective to arrange for an incremental thickness (34) in a portion (39) of a wall (34) interposed between the inner diameter (36) of restraining element (30) and respective proximate edges (40) of a number of pilot bolt holes (32) disposed around the restraining element.
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公开(公告)号：US09739160B2
公开(公告)日：2017-08-22
申请号：US14457504
申请日：2014-08-12
发明人： Jeffrey A. Kain , Mohit Gupta , Leonard J. Meyer , Ryan S. Yamane , James A. Chonody , Charalambos Polyzopoulos
CPC分类号： F01D5/323 , F01D5/16 , F01D5/26 , F01D5/30 , F01D5/3007 , F05D2220/32
摘要： An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root fir tree, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes an accordion-shaped spring which is compressed by a bolt and a coil spring. When the accordion spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the accordion spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The device can be inserted into the space without scraping against the blade root or the rotor disk, and expanded once it is in position.
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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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