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公开(公告)号：US10473328B2
公开(公告)日：2019-11-12
申请号：US15509286
申请日：2014-09-09
摘要： An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include resonator chambers (26) that may be welded in place within resonator chamber (26) receivers (24) but easily replaceable without exposing the resonator housing (18) to damage. In another embodiment, an inner surface (32) of the resonator chamber (26) may be offset radially outward from an inner surface (34) of the resonator housing (18), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (26). The acoustic damping resonator system (14) may mitigate dynamics thereby increasing an engine operating envelope and decreasing emissions.
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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：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：US20170276350A1
公开(公告)日：2017-09-28
申请号：US15509286
申请日：2014-09-09
CPC分类号： F23M20/005 , F02C7/24 , F05D2260/96 , F23D2210/00 , F23R3/002 , F23R3/04 , F23R3/06 , F23R2900/00014
摘要： An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include resonator chambers (26) that may be welded in place within resonator chamber (26) receivers (24) but easily replaceable without exposing the resonator housing (18) to damage. In another embodiment, an inner surface (32) of the resonator chamber (26) may be offset radially outward from an inner surface (34) of the resonator housing (18), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (26). The acoustic damping resonator system (14) may mitigate dynamics thereby increasing an engine operating envelope and decreasing emissions.
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