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公开(公告)号：US20240271575A1
公开(公告)日：2024-08-15
申请号：US18645585
申请日：2024-04-25
CPC分类号： F02C9/22 , F04D27/001 , F05D2220/323 , F05D2260/81 , F05D2270/301 , F05D2270/304 , F05D2270/306 , F05D2270/71
摘要： A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.
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公开(公告)号：US12044134B2
公开(公告)日：2024-07-23
申请号：US18112900
申请日：2023-02-22
申请人： BorgWarner Inc.
发明人： Nico Kanoffsky , Thomas Ramb
CPC分类号： F01D17/165 , F01D9/04 , F02B37/24 , F02C9/22 , F05D2220/40
摘要： An adjustment ring (200) for a variable turbine geometry (100). The adjustment ring (200) comprises a disk-shaped body (210) and a plurality of coupling regions (220) which are configured in the disk-shape body (210). The coupling regions (220) are spaced apart in the circumferential direction (26), and each coupling region (220) is adapted for at least partially receiving a vane lever (140) for adjusting a guide vane (120) of a variable turbine geometry (100). Each coupling region (220) circumferentially is fully surrounded by the disk-shaped body (210). The disk-shaped body (210) on one or more of the coupling regions (220) has at least one reinforcement means (230) which extends in the axial direction (22) from the disk-shaped body (210) and circumferentially at least partially surrounds the coupling region (220).
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公开(公告)号：US20230415914A1
公开(公告)日：2023-12-28
申请号：US18466930
申请日：2023-09-14
IPC分类号： B64D45/00 , B32B7/022 , B64C1/12 , B64C1/38 , B64D27/12 , F01D5/14 , F01D5/18 , F01D5/30 , F01D7/00 , F01D9/04 , F01D15/10 , F01D15/12 , F01D17/16 , F01D25/12 , F02C6/20 , F02C7/264 , F02C7/32 , F02C7/36 , F02C9/00 , F02C9/22 , F02K1/66 , F02K1/76
CPC分类号： B64D45/00 , B32B7/022 , B64C1/12 , B64C1/38 , B64D27/12 , F01D5/146 , F01D5/187 , F01D5/30 , F01D5/3007 , F01D7/00 , F01D9/041 , F01D15/10 , F01D15/12 , F01D17/162 , F01D25/12 , F02C6/206 , F02C7/264 , F02C7/32 , F02C7/36 , F02C9/00 , F02C9/22 , F02K1/66 , F02K1/76 , B32B2307/558 , B32B2307/72 , B32B2307/732 , B32B2571/02 , B32B2605/18 , B64C2001/0072
摘要： A method is provided of operating a single unducted rotor engine, the single unducted rotor engine comprising a single stage of unducted rotor blades. The method includes operating the single unducted rotor engine to define a flight speed, V0, in a length unit per second and an angular speed, n, in revolutions per second, the single stage of unducted rotor blades defining a diameter, D, in the length unit; wherein operating the single unducted rotor engine comprises operating the single unducted rotor engine to define an advance ratio greater than 3.8 while operating the single unducted rotor engine at a net efficiency of at least 0.8, the advance ratio defined by the equation V0/(n×D).
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公开(公告)号：US11828237B2
公开(公告)日：2023-11-28
申请号：US16860848
申请日：2020-04-28
IPC分类号： F02C9/22 , F02C7/057 , F02C7/04 , F02C9/18 , F02C6/08 , F01D17/10 , F04D27/00 , F04D29/54 , F04D27/02 , B64D33/02
CPC分类号： F02C9/22 , F01D17/105 , F02C6/08 , F02C7/04 , F02C7/057 , F02C9/18 , F04D27/009 , F04D27/0215 , F04D29/545 , B64D2033/0226 , F05D2220/323 , F05D2240/12 , F05D2270/301
摘要： Methods, apparatus, systems, and articles of manufacture are to control air flow separation of an engine. An example turbofan includes a nacelle having an outer lip surface, an inner lip surface, a first opening and a second opening, the first opening coupled to a first region forward of a fan of the turbofan, the second opening coupled to a second region aft of the fan, the nacelle including a first pressure sensor coupled to the outer lip surface, a second pressure sensor coupled to the inner lip surface, and an actuator, and a conduit coupled to the actuator, the conduit configured to have a first end and a second end, the first end coupled to the first opening, the second end coupled to the second opening.
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公开(公告)号：US11781492B2
公开(公告)日：2023-10-10
申请号：US17251098
申请日：2019-08-27
发明人： Bruno Giunta , Marco Palladino
CPC分类号： F02C9/22 , F02C3/10 , F02C9/54 , F05D2260/96 , F05D2270/024 , F05D2270/07 , F05D2270/304
摘要： A two-gas shaft turbine control system (31) is disclosed. The gas turbine control system comprises a fuel controller (35), which receives a speed error signal, indicating whether the low-pressure turbine wheel (11) of the gas turbine (1) is rotating at the desired target speed. The gas turbine control system (31) further comprises an NGV controller (41), which receives a speed error signal, indicating whether the high-pressure turbine wheel (9) of the gas turbine engine (1) is rotating at the desired target speed. Two cross channel controllers are further provided. On the basis of a gas turbine model, a first cross channel controller (43) provides a fuel control modification signal, which is added to a control signal generated by the fuel controller (35). A second cross channel controller (45) provides an NGV control modification signal. The modification signals are aimed at reducing or canceling the effect of mutual interaction between fuel control and NGV control. A two-shaft gas turbine engine system and a method of operation are further disclosed.
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公开(公告)号：US11739699B2
公开(公告)日：2023-08-29
申请号：US17521352
申请日：2021-11-08
发明人： Martin Drolet , Yves Cloutier
CPC分类号： F02C9/22 , F02C9/18 , F02C9/20 , F05D2200/13 , F05D2200/14 , F05D2200/211 , F05D2220/323 , F05D2270/303 , F05D2270/3015 , F05D2270/3061 , F05D2270/335 , F05D2270/71
摘要： The method can include determining a mass flow rate W of working fluid circulating through the compressor stage, determining a control parameter value associated to the geometrical configuration of the variable geometry element based on the determined value of mass flow rate W; and changing the geometrical configuration of the variable geometry element in accordance with the determined control parameter value.
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公开(公告)号：US20230193855A1
公开(公告)日：2023-06-22
申请号：US18113139
申请日：2023-02-23
发明人： Michael M. Joly , Zaffir A. Chaudhry , Andrzej Ernest Kuczek , Om P. Sharma , Georgi Kalitzin , Simon W. Evans
CPC分类号： F02K3/06 , F01D5/28 , F02C9/20 , F02C9/22 , F02C9/54 , F02C9/58 , F05D2220/36 , F05D2240/128
摘要： An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.
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8.发明申请公开(公告)号：US20230086029A1
公开(公告)日：2023-03-23
申请号：US17479200
申请日：2021-09-20
IPC分类号： F02C9/22
摘要： A system includes a gas turbine system including a compressor, a combustor, a turbine, and an exhaust section. The system also includes multiple sensors coupled to components of the gas turbine system. The system further includes a controller communicatively coupled to the gas turbine system and the multiple sensors and configured to control operations of the gas turbine system, wherein the controller is configured to calculate a surrogate value for turbine exit Mach number based on the feedback from the multiple sensors and to utilize the surrogate value to derive a control action for the gas turbine system.
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公开(公告)号：US20230024094A1
公开(公告)日：2023-01-26
申请号：US17381446
申请日：2021-07-21
发明人： Daniel COUTU
摘要： An aircraft engine, has: a low-pressure compressor and a high-pressure compressor located downstream of the low-pressure compressor; a gaspath valve upstream of the high-pressure compressor, the gaspath valve movable between an open configuration and a closed configuration; and a bypass flow path having in flow series a bypass inlet, a bypass valve, and a bypass outlet, the bypass inlet fluidly communicating with the gaspath upstream of at least one stage of the low-pressure compressor, the bypass valve having an open configuration in which the bypass valve allows a bypass flow and a closed configuration in which the bypass valve blocks the bypass flow, the bypass outlet fluidly communicating with the bypass inlet via the bypass valve and with the gaspath at a location in the gaspath fluidly downstream of the gaspath valve, downstream of the low-pressure compressor, and upstream of the high-pressure compressor.
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10.发明授权公开(公告)号：US11371942B2
公开(公告)日：2022-06-28
申请号：US16769699
申请日：2018-12-05
摘要： A Raman scattered light acquisition device includes an emitting optical system configured to guide excitation light into a fluid, a scattered light window configured to define a part of a flow path of the fluid and through which Raman scattered light from the fluid irradiated with the excitation light passes, and a scattered light receiving device having a light receiving surface receiving Raman scattered light passed through the scattered light window. The scattered light window and the light receiving surface of the scattered light receiving device are disposed at a position in which they are separated from an optical axis in the fluid in a radial direction within a range in which an optical path of the excitation light in the fluid is present in an optical axis direction in which the optical axis in the fluid which is an optical axis of the excitation light in the fluid extends.
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