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公开(公告)号：US20230340888A1
公开(公告)日：2023-10-26
申请号：US18341905
申请日：2023-06-27
CPC分类号： F01D19/02 , F01D25/12 , F05D2220/323 , F05D2260/232 , F05D2260/85 , F05D2270/112 , F05D2270/3032
摘要： An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.
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公开(公告)号：US10208607B2
公开(公告)日：2019-02-19
申请号：US15239940
申请日：2016-08-18
摘要： A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.
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公开(公告)号：US20180051574A1
公开(公告)日：2018-02-22
申请号：US15239940
申请日：2016-08-18
CPC分类号： F01D5/187 , F01D5/147 , F01D9/02 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2240/303 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/205
摘要： A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.
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公开(公告)号：US12104535B2
公开(公告)日：2024-10-01
申请号：US17717402
申请日：2022-04-11
CPC分类号： F02C7/18 , F01D25/12 , F02C7/141 , F05D2220/32 , F05D2260/213
摘要： A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.
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公开(公告)号：US11702952B2
公开(公告)日：2023-07-18
申请号：US17524196
申请日：2021-11-11
CPC分类号： F01D19/02 , F01D25/12 , F05D2220/323 , F05D2260/232 , F05D2260/85 , F05D2270/112 , F05D2270/3032
摘要： An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.
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公开(公告)号：US20180363470A1
公开(公告)日：2018-12-20
申请号：US15624252
申请日：2017-06-15
发明人： Zachary John Snider , Daniel Burnos , Lana Maria Osusky , Brian Gene Brzek , Gregory Thomas Foster
IPC分类号： F01D5/18
摘要： A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.
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公开(公告)号：US20180051573A1
公开(公告)日：2018-02-22
申请号：US15239930
申请日：2016-08-18
CPC分类号： F01D5/187 , F01D25/12 , F05D2250/185 , F05D2260/201 , F05D2260/202
摘要： A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the central cavity; a second leading edge cavity located forward of the first leading edge cavity; at least one impingement opening for fluidly coupling the first leading edge cavity to the second leading edge cavity; and at least one channel for fluidly coupling the central cavity to a tip of the multi-wall blade.
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8.发明公开公开(公告)号：US20230349329A1
公开(公告)日：2023-11-02
申请号：US18315075
申请日：2023-05-10
CPC分类号： F02C7/12 , F02C7/36 , F05D2260/20 , F05D2260/4031
摘要： A turbofan engine having one or more heat exchangers tied to a power gearbox is provided. The power gearbox mechanically couples a low pressure spool and a fan of the turbofan engine. The one or more heat exchangers have a heat exchanger capacity defined by a resultant heat transfer surface area density associated with the one or more heat exchangers multiplied by a heat conductance factor that relates a power gearbox heat load, a fan power consumption function, a fan diameter of the fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 0.77 and 298.17 for a rotational speed of the low pressure spool between 2,000 and 16,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 3,000 m2/m3 and 13,000 m2/m3.
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公开(公告)号：US20230141059A1
公开(公告)日：2023-05-11
申请号：US17524196
申请日：2021-11-11
CPC分类号： F01D19/02 , F01D25/12 , F05D2220/323 , F05D2260/232 , F05D2260/85 , F05D2270/3032 , F05D2270/112
摘要： An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.
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公开(公告)号：US10221696B2
公开(公告)日：2019-03-05
申请号：US15239930
申请日：2016-08-18
摘要： A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the central cavity; a second leading edge cavity located forward of the first leading edge cavity; at least one impingement opening for fluidly coupling the first leading edge cavity to the second leading edge cavity; and at least one channel for fluidly coupling the central cavity to a tip of the multi-wall blade.
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