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111.发明申请Device for axially holding a ring spacer sector of a high-pressure turbine of a turbomachine 有权用于轴向保持涡轮机的高压涡轮机的环形间隔件的装置公开(公告)号：US20050196270A1
公开(公告)日：2005-09-08
申请号：US11070093
申请日：2005-03-03
申请人： Denis Amiot , Pascal Lefebvre
发明人： Denis Amiot , Pascal Lefebvre
CPC分类号： F01D25/246 , F01D9/04 , F01D11/20 , F02C7/24
摘要： A device for axially holding a ring spacer sector of a high-pressure turbine of a turbomachine, said spacer sector comprising an upstream radial wall provided with an outer upstream tongue for being engaged in a corresponding upstream groove of a casing of the turbine, and with an inner upstream tongue for being engaged in a corresponding upstream groove of a ring sector, said device comprising a piece of longitudinally-extending sheet metal that constitutes a heat shield disposed upstream from the upstream radial wall of the spacer sector against an inner surface of the casing, the piece of longitudinally-extending sheet metal bearing axially against the upstream radial wall of the spacer sector and being secured to the casing so as to hold the spacer sector axially.
摘要翻译： 一种用于轴向保持涡轮机的高压涡轮机的环形间隔件的装置，所述间隔件部分包括设置有外部上游舌片的上游径向壁，用于接合在所述涡轮机壳体的相应的上游槽中，并且与 内部上游舌片，用于接合在环形扇形部分的相应的上游沟槽中，所述装置包括一块纵向延伸的金属板，该片材构成隔热片的上游侧壁的上游侧的热屏障， 壳体，纵向延伸的片状金属轴承轴向地抵靠间隔件扇区的上游径向壁并且被固定到壳体以便沿轴向保持间隔件部分。
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公开(公告)号：US5165844A
公开(公告)日：1992-11-24
申请号：US789556
申请日：1991-11-08
申请人： Syed J. Khalid
发明人： Syed J. Khalid
CPC分类号： F02C9/18 , F01D11/20 , F04D27/0246
摘要： The deflection angle of a gas turbine stator is adjusted in proportion to the difference between two parameters computed from N.sub.2 and TT2 using the same function generator. One parameter is a reference adjustment under standard conditions for measured N.sub.2 adjusted to sea level and standard temperature. The second parameter is an adjustment for actual altitude conditions. The parameters manifest the clearance between the engine case and the turbine blade tips.
摘要翻译： 燃气轮机定子的偏转角度与使用相同函数发生器从N2和TT2计算的两个参数之间的差异成比例地调整。 一个参数是在标准条件下对被调节到海平面和标准温度的N2进行参考调整。 第二个参数是对实际高度条件的调整。 这些参数表明发动机外壳和涡轮叶片尖端之间的间隙。
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公开(公告)号：US20240352866A1
公开(公告)日：2024-10-24
申请号：US18354021
申请日：2023-07-18
发明人： Randy M. Vondrell , Kevin William Caldwell , John Carl Glessner , Javier Barba Fuentes , Dorota Kopkowicz
CPC分类号： F01D11/20 , F05D2260/213
摘要： A gas turbine engine includes a fan section, an engine inlet, and a fan duct splitter in serial flow order. The fan duct splitter splits an airflow entering the engine inlet from the fan section into a fan duct and a core duct. The core duct includes a compressor section, a combustion section, and a turbine section in serial flow order. A duct assembly is coupled to the fan duct to extract a portion of a fan duct airflow passing through the fan duct and deliver the portion of the fan duct airflow to an active clearance control mechanism of the turbine section.
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114.发明公开公开(公告)号：US20240337198A1
公开(公告)日：2024-10-10
申请号：US18393389
申请日：2023-12-21
发明人： Taehong Kim , Tyler F. Hooper
CPC分类号： F01D11/20 , F03G7/06145 , F03G7/0665 , H10N30/206 , H10N30/50 , H10N30/802
摘要： Certain examples disclose and describe apparatus and methods to provide fast response active clearance system with piezoelectric actuator in axial, axial/radial combined, and circumferential directions. In some examples, an apparatus includes an actuator to control clearance between a blade and at least one of a shroud or a hanger, the actuator including a multilayer stack of material, and wherein the actuator is outside a case. The apparatus further includes a rod coupled to the actuator and the at least one of the shroud or the hanger through an opening in the case, the rod to move the at least one of the shroud or the hanger in a radial direction based on axial movement of the multilayer stack of material.
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公开(公告)号：US12049828B2
公开(公告)日：2024-07-30
申请号：US17900513
申请日：2022-08-31
发明人： Anusrita Raychaudhuri , Ravindra Shankar Ganiger , Bhanu Battu , Richa Awasthi , Nilesh Varote , Vidyashankar Buravalla
IPC分类号： F01D11/20 , F01D11/02 , F01D11/08 , F01D11/14 , F01D11/22 , F01D11/24 , F02C7/042 , F02C7/057 , F04D29/52
CPC分类号： F01D11/20 , F01D11/025 , F01D11/22 , F01D11/24 , F02C7/042 , F04D29/526 , F01D11/08 , F01D11/14 , F02C7/057 , F05D2220/32 , F05D2240/11 , F05D2300/505
摘要： Variable sleeve clearance control systems for gas turbine engines are disclosed. An example variable sleeve clearance control system for a gas turbine engine includes a sleeve comprising a first end and a second end, the first end of the sleeve coupled to a first spring that biases the sleeve inward, and the second end of the sleeve coupled to a second spring that biases the sleeve outward, a proximity sensor to measure a clearance width, and a controller for each of the first and second springs, the controller to obtain the measured clearance width from the proximity sensor and determine a response of the first and second springs.
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公开(公告)号：US11867068B2
公开(公告)日：2024-01-09
申请号：US17739766
申请日：2022-05-09
发明人： Taehong Kim , Tyler F. Hooper
CPC分类号： F01D11/20 , F03G7/0665 , F03G7/06145 , H10N30/206 , H10N30/50 , H10N30/802
摘要： Certain examples disclose and describe apparatus and methods to provide fast response active clearance system with piezoelectric actuator in axial, axial/radial combined, and circumferential directions. In some examples, an apparatus includes an actuator to control clearance between a blade and at least one of a shroud or a hanger, the actuator including a multilayer stack of material, and wherein the actuator is outside a case. The apparatus further includes a rod coupled to the actuator and the at least one of the shroud or the hanger through an opening in the case, the rod to move the at least one of the shroud or the hanger in a radial direction based on axial movement of the multilayer stack of material.
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公开(公告)号：US11773742B2
公开(公告)日：2023-10-03
申请号：US16806168
申请日：2020-03-02
CPC分类号： F01D11/20 , F01D5/02 , F01D9/065 , F01D11/24 , F02C3/04 , F02C9/18 , F04D29/542 , F05D2220/32 , F05D2240/35 , F05D2260/213 , F05D2300/50212 , Y02T50/60
摘要： A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
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公开(公告)号：US11732599B2
公开(公告)日：2023-08-22
申请号：US17952905
申请日：2022-09-26
发明人： Taehong Kim , Aaron J. Sentis
IPC分类号： F01D11/20
CPC分类号： F01D11/20 , F05D2220/32 , F05D2240/55 , F05D2270/44
摘要： Methods and apparatus for real-time clearance assessment using a pressure measurement are disclosed. An example method includes determining a first and a second static pressure measurement at a first measurement location and a second measurement location, respectively, relative to the blade tip clearance, determining a normalized pressure measurement using the first and second static pressure measurements, generating a conversion curve to correlate the normalized pressure measurement with a clearance measurement, wherein the conversion curve is developed for the turbine engine during testing at a plurality of operating conditions, and adjusting active clearance control of the blade tip clearance based on the conversion curve.
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公开(公告)号：US20230235680A1
公开(公告)日：2023-07-27
申请号：US17649030
申请日：2022-01-26
CPC分类号： F01D11/20 , F01D7/00 , F01D25/005
摘要： A rotor blade system includes a rotor, a casing radially spaced apart from the rotor, and a plurality of blades coupled to the rotor and positioned between the rotor and the casing. The one or more of the plurality of blades have a radial length different from a remaining one or more of the plurality of blades so as to vary a tip gap between a tip of the one or more of the plurality of blades and the casing to break up a frequency content of a leakage vortex at the tip to modify natural frequencies of the plurality of blades and mode shapes to reduce or substantially eliminate flutter.
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公开(公告)号：US11473510B2
公开(公告)日：2022-10-18
申请号：US16388227
申请日：2019-04-18
发明人： Joseph Kehoe , Richard P. Meisner , Manuj Dhingra , Patrick D. Couture , Matthew R. Feulner , Brenda J. Lisitano , Christopher L. Ho
摘要： A method of operating a gas turbine engine includes commanding an acceleration of the gas turbine engine and moving a variable pitch high pressure compressor vane toward an open position thereby reducing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal. An active clearance control system of a gas turbine engine includes an engine control system configured to command an acceleration of the gas turbine engine and move a variable pitch high pressure compressor vane toward an open position thereby slowing an acceleration rate of a high pressure turbine rotor thereby reducing a change in a clearance gap between the high pressure turbine rotor and a blade outer airseal located radially outboard of the high pressure turbine rotor.
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