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公开(公告)号：US11927101B1
公开(公告)日：2024-03-12
申请号：US17901769
申请日：2022-09-01
发明人： Megan K. Waller , Jeffrey B. Stewart , George Prater , James Maleski , Victor Antonio Chagala Galicia , Antonio Fajardo Celis , Marius Dumitrascu , Jeffrey Tarczy
CPC分类号： F01D11/08 , F02C7/28 , F05D2260/30
摘要： Tip shrouds or other shrouds with multi-slope geometries are generally implemented using segments, since performing the necessary cut for an alternative split-ring design is difficult given conventional cutting processes. However, a segmented design generally results in more leakage, relative to a split-ring design. Accordingly, a split-ring multi-slope design is disclosed that can be more easily manufactured. In particular, a continuous ring may be cut along a linear path to produce a split ring, and then the ends of the split ring may be machined to form complementary shiplap portions. The split ring may then be compressed for installation by overlapping the shiplap portions, to form a seal against leakage through the shroud.
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公开(公告)号：US20220389826A1
公开(公告)日：2022-12-08
申请号：US17337221
申请日：2021-06-02
发明人： Phillip O. BOURNE , Morgan PROFFITT
摘要： In a gas turbine engine, coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case, the nozzle of the turbine, and the exhaust diffuser. Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces of a combustor flange and diffuser flange. In addition, one or more contact sealing lands may be used between the combustor flange and diffuser flange and one or more seals may be provided between various components of the interface to provide additional sealing.
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公开(公告)号：US11428166B2
公开(公告)日：2022-08-30
申请号：US17096046
申请日：2020-11-12
发明人： Scott L. Stafford , Juan Yin , Steven D. Gray
摘要： Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.
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公开(公告)号：US11352904B2
公开(公告)日：2022-06-07
申请号：US16745600
申请日：2020-01-17
IPC分类号： F04D17/08 , F04D29/058 , F01D25/16 , F04D29/059
摘要： A magnetic bearing assembly for a rotary machine may lose power and fail to support the rotating assembly resulting in damage to magnetic bearing assembly and/or other components. An auxiliary bearing assembly may be used to support the rotating assembly during such a failure. The auxiliary bearing assembly is located radially inwards of the magnetic bearing assembly and may reduce resonance and/or whirl of the rotating assembly during failure of the magnetic bearing assembly.
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5.发明授权公开(公告)号：US11236615B1
公开(公告)日：2022-02-01
申请号：US17009469
申请日：2020-09-01
发明人： David A. Burton , Kwok-Kwong Ben Tse , David Lau
摘要： A stator assembly, at a compressor mid-plane in a gas turbine engine, to be mounted around a rotor disc, enables access to the rotor disc (e.g., for trim balancing), without requiring disassembly of the stator assembly and/or a compressor case in which the stator assembly is housed, via a removable stator vane. The stator assembly may comprise vane apertures, aligned along a radial axis, that hold the removable stator vane when inserted into the stator assembly, and provide a radial pathway to the rotor disc, when the removable stator vane is removed from the stator assembly. In addition, a case access assembly may seal the removable stator vane in place within a compressor case when engaged, and provide access to the removable stator vane and radial pathway through the compressor case when disengaged. This enables trim balancing of a mid-plane compressor rotor assembly through the stator assembly and compressor case.
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公开(公告)号：US11174739B2
公开(公告)日：2021-11-16
申请号：US16552853
申请日：2019-08-27
摘要： A damped turbine blade assembly for a gas turbine engine is disclosed. The damped turbine blade assembly includes a damper positioned within a first small slot of a first turbine blade and a second large slot of the second turbine blade. A portion of the damper can slidably mate with the second large slot providing a radial and angular connection between the first turbine blade and second turbine blade while allowing movement in a direction tangent to a radial of a center axis of the gas turbine engine. The tangential movement is resisted by friction between the damper contacting the second large slot and provides friction damping against vibrations felt by the turbine blades during operation of the gas turbine engine. The damper can be shaped and/or pre-stressed to control the normal force component of the friction between the damper and the second large slot.
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公开(公告)号：US11162682B2
公开(公告)日：2021-11-02
申请号：US16600124
申请日：2019-10-11
发明人： Richard A. Rogers , Drew Allen Dominique , Timothy Ray Evans, Jr. , Jonathan Gerrard Duckers , Stephen Burke , Robert Archer , Stefan Helmuth Humer , Hanjie Lee
摘要： A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel stem assembly for receiving and distributing fuel and an injector head receiving fuel from the fuel stem assembly. The injector head can include an injector body, swirler vanes, a pilot assembly, passages, and fuel galleries. The pilot assembly can include pilot struts and a pilot tube. The swirler vanes and pilot struts can include passages to transport the pilot fuel from the fuel stem assembly to the pilot tube.
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公开(公告)号：US11111859B2
公开(公告)日：2021-09-07
申请号：US16596453
申请日：2019-10-08
发明人： Peter Davis
摘要： A method and control system for controlling compressor output for a gas turbine engine is disclosed. The power output of a gas turbine engine can vary and be below desired output levels due to operating conditions such as ambient temperature and elevation. These operating conditions can lead to lower output of the gas compressor of the turbine engine and lower operating temperatures within or proximate to a turbine of the gas turbine engine and lead to less power output. Additional fuel can be added to increase power to the gas producer shaft and increase turbine temperature of the gas turbine engine. A power transfer device can be used to remove or add power to the gas producer shaft to balance the gas producer mechanical limits and turbine thermal limits at maximum levels and lead to higher power output.
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公开(公告)号：US20210062659A1
公开(公告)日：2021-03-04
申请号：US16552853
申请日：2019-08-27
IPC分类号： F01D5/22
摘要： A damped turbine blade assembly for a gas turbine engine is disclosed. The damped turbine blade assembly includes a damper positioned within a first small slot of a first turbine blade and a second large slot of the second turbine blade. A portion of the damper can slidably mate with the second large slot providing a radial and angular connection between the first turbine blade and second turbine blade while allowing movement in a direction tangent to a radial of a center axis of the gas turbine engine. The tangential movement is resisted by friction between the damper contacting the second large slot and provides friction damping against vibrations felt by the turbine blades during operation of the gas turbine engine. The damper can be shaped and/or pre-stressed to control the normal force component of the friction between the damper and the second large slot.
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公开(公告)号：US20200340673A1
公开(公告)日：2020-10-29
申请号：US16397999
申请日：2019-04-29
发明人： German Verduzco , Michael Telfer , Drew Dominique , James Peffley , Taher Basrai , Rasoul Paydar
摘要： This disclosure provides an air tube for a combustor of a gas turbine engine. The air tube includes an inner tube and an outer tube to deliver discharged compressor air into a combustion chamber of the combustor. The air tube can include struts and fins that can improve the cooling performance of the air tube during operation of the gas turbine engine.
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