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1.发明公开公开(公告)号：US20240352896A1
公开(公告)日：2024-10-24
申请号：US18303111
申请日：2023-04-19
CPC分类号： F02C9/18 , F02C3/08 , F02C9/20 , F02C9/22 , F04D27/0223 , F04D27/0246 , F05D2270/101 , F05D2270/304
摘要： Systems and methods for stable operation of a compressor of a gas turbine engine include axial stages, each including a series of rotor blades. A centrifugal stage has a centrifugal impeller disposed downstream from the axial stages. Air flows through the compressor first through the axial stages and then through the centrifugal stage. Each respective axial stage includes mechanisms for the avoidance of certain operating conditions of the compressor such as surge. The mechanisms include variable vane sets disposed upstream from a series of the rotor blades or a bleed port or ports around the respective axial stage downstream from the series of rotor blades to selectively extract air from the respective axial stage.
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公开(公告)号：US12017790B2
公开(公告)日：2024-06-25
申请号：US17061079
申请日：2020-10-01
发明人： Daniel Swain , Rory D. Stieger , Mark D. Taylor
CPC分类号： B64D41/00 , B64D27/10 , F02C3/08 , F02C6/00 , H02K11/33 , F05D2220/32 , F05D2220/50
摘要： An auxiliary power unit (10) for an aircraft (1) comprises a gas turbine engine comprising an engine core (12). The engine core comprises a core compressor (14) and core turbine (18) coupled by a core shaft (24). The auxiliary power unit further comprises a load spool comprising a load compressor (30), a load turbine (20) and a permanent magnet electric machine (28), each being coupled by a load shaft (26). The load shaft (26) and core shaft (24) are configured to rotate independently of one another.
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公开(公告)号：US11767792B1
公开(公告)日：2023-09-26
申请号：US17808317
申请日：2022-06-23
发明人： Guy Lefebvre , Christopher Gover
CPC分类号： F02C7/06 , F01D25/162 , F01D25/24 , F02C3/08 , F02C7/20 , F05D2220/32 , F05D2230/60 , F05D2240/14 , F05D2240/50
摘要： There is provided a load transfer interface in an aircraft engine for transferring a load from a bearing housing to an engine casing. The load transfer interface comprises a first component operatively coupled to and receiving the load from the bearing housing. The first component has a first annular body with a spigot extending axially from the first annular body. The interface comprises a second component operatively coupled to the first component and to the engine casing. The second component has a second annular body with a spigot-receiving cavity disposed therein. The spigot-receiving cavity is shaped and positioned to receive the spigot of the first component. The second component receives the load from the first component and transfers the load to the engine casing.
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公开(公告)号：US20180023576A1
公开(公告)日：2018-01-25
申请号：US15218915
申请日：2016-07-25
发明人： Daniel Bernard Kupratis , Arthur W. Utay , Tania Bhatia Kashyap , Thomas N. Slavens , Kevin L. Rugg , Mark F. Zelesky , Brian D. Merry , Gabriel L. Suciu
CPC分类号： B64D41/00 , F02C3/08 , F02C3/145 , F04D17/105
摘要： An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.
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公开(公告)号：US09752584B2
公开(公告)日：2017-09-05
申请号：US14495501
申请日：2014-09-24
CPC分类号： F04D17/025 , F01D5/143 , F02C3/08 , F02C3/14 , F04D29/666
摘要： A compressor arrangement has a common shaft, an axial compressor having at least a single-stage, and a radial compressor having at least single-stage. Assemblies of the, or each, axial compressor stage on the rotor side and assemblies of the, or each, radial compressor stage on the rotor side are attached to a common shaft (4). A ratio between a maximum diameter of the shaft (4) in the region of the axial compressor (2) and a minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.5 and 3.0.
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6.发明申请公开(公告)号：US20170211586A1
公开(公告)日：2017-07-27
申请号：US15006551
申请日：2016-01-26
发明人： Raymond Gage , Bruce David Reynolds , Jeffrey D. Harrison , Michael Todd Barton , Mahmoud Mansour , Kent L. Kime
CPC分类号： F04D29/4206 , F02C3/08 , F02C6/08 , F04D29/284 , F04D29/444 , F04D29/582 , F05D2220/32 , F05D2240/128 , F05D2240/30 , F05D2260/20 , Y02T50/671
摘要： Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.
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公开(公告)号：US09631556B2
公开(公告)日：2017-04-25
申请号：US15158894
申请日：2016-05-19
申请人： Masato Yoshino , Hiroki Fujiwara
发明人： Masato Yoshino , Hiroki Fujiwara
CPC分类号： F16C17/024 , F01D25/16 , F01D25/166 , F02C3/08 , F02C7/06 , F02C7/08 , F05D2220/32 , F05D2220/40 , F16C27/02 , F16C32/0607 , F16C33/101 , F16C43/02 , F16C2360/23 , F16C2360/24
摘要： A foil bearing includes an outer member (11), and a plurality of foils (13) that are mounted to an inner circumferential surface (11a) of the outer member (11) and directly face the inner circumferential surface (11a) of the outer member (11) in a radial direction without interposition of another member (such as back foils). The foils (13) each include: holding portions (13a, 13b) that are formed at both circumferential ends and held while in contact with the outer member (11); and a body portion (13c) that is formed circumferentially between the holding portions (13a, 13b) and has a bearing surface (A). At least an end portion on one side in a circumferential direction of the body portion (13c) is raised radially inward with respect to the inner circumferential surface (11a) of the outer member (11).
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8.发明授权Method for attaching the cover of a centrifugal compressor of a turbine engine, compressor cover implementing same and compressor assembly provided with such a cover 有权一种用于安装涡轮发动机的离心式压缩机，实现其的压缩机盖和设置有这种盖的压缩机组件的盖的方法公开(公告)号：US09409228B2
公开(公告)日：2016-08-09
申请号：US13880245
申请日：2011-10-20
CPC分类号： B21K3/00 , F01D11/08 , F01D11/18 , F01D25/246 , F02C3/08 , F04D29/162 , F04D29/4206 , Y10T29/49236
摘要： An attachment arrangement at a middle of a cover having an elastically deformable portion. The cover includes a concave shell including an inner surface spaced apart from the compressor including an impeller including blades by an attachment. The attachment includes one connection end at the middle of the shell, another end attached to a casing of the turbine engine, and an axisymmetric diaphragm having a generally frusto-conical configuration having an arm profile coupled to the end for attachment to the casing by a double-elbow joint having right and obtuse angles when in a rest position. The distance between the inner surface of the shell and upper edges of the blades can be held constant during operation with minimum clearance adjustment. The cover can be moved such that clearance between the cover and blades of the compressor impeller remains substantially constant and as low as possible.
摘要翻译： 在具有可弹性变形部分的盖的中间的连接装置。 所述盖包括凹形壳体，所述凹形壳体包括与所述压缩机间隔开的内表面，所述内表面包括通过附件的包括叶片的叶轮。 附件包括在壳的中间的一个连接端，连接到涡轮发动机的壳体的另一端和具有大致截头圆锥形构造的轴对称隔膜，该轴对称隔膜具有联接到端部的臂形状，用于通过一个 双肘关节在静止位置时具有正角和钝角。 壳体的内表面与叶片的上边缘之间的距离可以在操作期间保持恒定，同时最小间隙调整。 可以移动盖，使得压缩机叶轮的盖和叶片之间的间隙保持基本上恒定并尽可能低。
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9.发明申请公开(公告)号：US20150300248A1
公开(公告)日：2015-10-22
申请号：US14689313
申请日：2015-04-17
发明人： Martin SCHNEIDER
IPC分类号： F02C3/04 , F04D29/42 , F04D29/28 , F04D17/12 , F04D29/053
CPC分类号： F02C3/04 , F01D1/22 , F02C3/08 , F02C3/107 , F02C7/08 , F02K3/06 , F04D17/12 , F04D17/122 , F04D25/02 , F04D25/16 , F04D25/163 , F04D29/053 , F04D29/284 , F04D29/4206 , F05D2240/40 , F05D2260/4031 , F05D2260/532
摘要： A compressor arrangement with centrifugal compressors arranged in sequence and each centrifugal compressor includes a rotor and a drive shaft, such that air flows through an inlet and out an outlet to a subsequent one of the centrifugal compressors, wherein drive shafts at two or more of the centrifugal compressors are arranged at an angle of between 0 degrees and 90 degrees with respect to one another.
摘要翻译： 一种具有离心式压缩机的压缩机装置，每个离心式压缩机包括一个转子和一个驱动轴，使得空气流过入口和出口到随后的一个离心式压缩机，其中两个或更多个 离心压缩机相对于彼此以0度和90度之间的角度布置。
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公开(公告)号：US20150139788A1
公开(公告)日：2015-05-21
申请号：US14495501
申请日：2014-09-24
IPC分类号： F04D17/02
CPC分类号： F04D17/025 , F01D5/143 , F02C3/08 , F02C3/14 , F04D29/666
摘要： A compressor arrangement has a common shaft, an axial compressor having at least a single-stage, and a radial compressor having at least single-stage. Assemblies of the, or each, axial compressor stage on the rotor side and assemblies of the, or each, radial compressor stage on the rotor side are attached to a common shaft (4). A ratio between a maximum diameter of the shaft (4) in the region of the axial compressor (2) and a minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.5 and 3.0.
摘要翻译： 压缩机装置具有公共轴，具有至少单级的轴向压缩机和至少具有单级的径向压缩机。 转子侧的或每个轴向压缩机级的组件或转子侧上的每个或径向压缩机级的组件都附接到公共轴（4）。 轴向压缩机（2）区域中的轴（4）的最大直径与径向压缩机（3）区域中的轴（4）的最小径向叶轮座直径之间的比率在1.5和3.0之间 。
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