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公开(公告)号：US4082477A
公开(公告)日：1978-04-04
申请号：US636653
申请日：1975-12-01
Applicant: Sven-Olof Kronogard
Inventor： Sven-Olof Kronogard
CPC classification number: F04D29/462 , F01D25/002 , F04D17/02 , F04D17/127 , F04D29/4213 , F05D2250/51
Abstract: In order to raise the degree of compression without unduly increasing the dimensions a compressor having at least two stages includes a first centripetal stage and a last centrifugal stage mounted upon the same shaft. The diameter at the centripetal stage inlet does not exceed the diameter at the outlet of the centrifugal stage and the air flows radially inwards in the first stage, and radially outwards in the last stage.
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公开(公告)号：US4025228A
公开(公告)日：1977-05-24
申请号：US589799
申请日：1975-06-24
Applicant: Jean Lieber
Inventor： Jean Lieber
Abstract: In a hydraulic plant comprising one or more machines of the reaction turbine or rotary pump type, the conventional single spiral casing of each machine is replaced by several partial volutes connecting the periphery of the fixed supporting blade ring by several independent tubular connection elements to a pressure pipeline.
Abstract translation: 在包括反应涡轮机或旋转泵型的一个或多个机器的液压设备中，每台机器的常规单螺旋壳体由几个部分蜗壳替代，该部分蜗壳通过几个独立的管状连接元件将固定的支撑叶片环的周边连接到压力 管道。
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公开(公告)号：US3558084A
公开(公告)日：1971-01-26
申请号：US3558084D
申请日：1968-06-05
Applicant: ROBERT B COTTON
Inventor： COTTON ROBERT B
Abstract: A gas flow turbine for use in conjunction with a jet engine includes a series of radially disposed blades mounted about a periphery of a circular support wheel. The edges of the blades are substantially free of obstruction to minimize impediment to the flow of gas directed against them. This causes the turbine wheel to derive a substantial thrust from the gas flowing against it without materially impeding such flow. A convenient form of such turbine includes slightly curved blades centrally mounted in cantilever manner to a rotatable disc with their ends extending therefrom. Despite the minimal reaction imparted to the wheel by the gases, substantial energy is derived from the gases discharged from a jet engine without materially reducing the engine''s efficiency. The turbine''s energy may be advantageously utilized for a multitude of purposes including general augmentation of jet engine thrust, particularly for improving efficiency of launching thrust and auxiliary uses in conjunction with jet engine exhaust including electric power generation.
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公开(公告)号：US2944786A
公开(公告)日：1960-07-12
申请号：US38635853
申请日：1953-10-15
Applicant: THOMPSON RAMO WOOLDRIDGE INC
Inventor： ANGELL PIERCE T , ANDERSON ROBERT J , HOPPER MALCOLM M
CPC classification number: F01D9/026 , F01D1/08 , F01D17/146
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公开(公告)号：US2280585A
公开(公告)日：1942-04-21
申请号：US23869938
申请日：1938-11-03
Applicant: PETER KAPITZA
Inventor： PETER KAPITZA
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Patent Agency Ranking
公开(公告)号：US12129764B2
公开(公告)日：2024-10-29
申请号：US18285318
申请日：2022-03-28
Inventor： Nao Taniguchi , Fumito Hiratani , Takeshi Tsuji
CPC classification number: F01D25/24 , F01D1/08 , F05D2220/40 , F05D2240/14
Abstract: A turbocharger gas casing includes a scroll part forming a plurality of scroll passages at a same position in an axial direction of the turbine. The plurality of scroll passages include a first scroll passage. The first scroll passage is configured so that an extension line of a line segment connecting a farthest position from a rotational axis of the turbine at an inlet for an exhaust gas of the first scroll passage and a position of a tip of a tongue part formed on an inner peripheral side of the first scroll passage does not intersect a rotor blade of the turbine in a cross section of the turbine orthogonal to the axial direction.
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公开(公告)号：US20240191636A1
公开(公告)日：2024-06-13
申请号：US18285318
申请日：2022-03-28
Inventor： Nao Taniguchi , Fumito Hiratani , Takeshi Tsuji
CPC classification number: F01D25/24 , F01D1/08 , F05D2220/40 , F05D2240/14
Abstract: A turbocharger gas casing includes a scroll part forming a plurality of scroll passages at a same position in an axial direction of the turbine. The plurality of scroll passages include a first scroll passage. The first scroll passage is configured so that an extension line of a line segment connecting a farthest position from a rotational axis of the turbine at an inlet for an exhaust gas of the first scroll passage and a position of a tip of a tongue part formed on an inner peripheral side of the first scroll passage does not intersect a rotor blade of the turbine in a cross section of the turbine orthogonal to the axial direction.
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公开(公告)号：US11834963B2
公开(公告)日：2023-12-05
申请号：US17672107
申请日：2022-02-15
Applicant: Raytheon Technologies Corporation
Inventor： Mark T. Ucasz
IPC: F01D5/28 , C23C30/00 , C23C28/04 , C23C28/00 , C23C28/02 , F01D25/00 , F01D5/02 , F01D9/04 , F01D1/08 , F01D11/08
CPC classification number: F01D5/288 , C23C28/028 , C23C28/048 , C23C28/3215 , C23C28/345 , C23C30/00 , F01D1/08 , F01D5/02 , F01D9/041 , F01D25/007 , F05D2220/32 , F05D2230/90 , F05D2240/35 , F05D2260/95 , F05D2300/171 , F05D2300/177 , F05D2300/611 , Y02T50/60
Abstract: A coated article includes a substrate and an MCrAlY coating supported on the substrate. The M includes at least one of nickel, cobalt, and iron, Cr is chromium, Al is aluminum, and Y is yttrium. The composition of the MCrAlY coating varies in an amount of at least one of Cr, Al, and Y by location on the substrate with respect to localized property requirements. In one example, the coated article is an article of a gas turbine engine.
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公开(公告)号：US20180030834A1
公开(公告)日：2018-02-01
申请号：US15550475
申请日：2016-02-12
Applicant: Hyuk Sun CHOI
Inventor： Hyuk Sun CHOI
CPC classification number: F01D1/026 , F01D1/08 , F01D1/10 , F01D1/22 , F01D5/14 , F01D9/04 , F01D9/045
Abstract: The present invention relates to an axial flow turbine, comprising: a rotor mounting part; a housing having a fluid supply part surrounding the rotor mounting part; a rotor which is installed at a rotation shaft installed in the housing and has a plurality of blades installed in a circumferential direction; and a plurality of injection nozzles, installed in the fluid supply part surrounding the rotor mounting part, for spraying a high-pressure fluid toward the blades, wherein the fluid collision surface of the blades installed at the rotor is formed to be inclined at an angle in the rotational direction of the rotor with respect to the normal axis of the rotation center axis, and the injection nozzles formed in the fluid supply part are installed at an angle parallel to the normal direction of the fluid collision surface of the blades. Due to the aforementioned configuration, the present invention provides the effect of maximizing the rotation rate of a turbine while smoothing fluid flow by optimizing the angle of the fluid collision surface of the blades.
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公开(公告)号：US09534576B2
公开(公告)日：2017-01-03
申请号：US14369522
申请日：2011-12-30
IPC: F03B3/02 , F03B11/02 , F03B3/18 , F01D9/02 , F01D17/16 , F01D25/14 , F01D1/08 , F03B11/00 , F01D5/02
CPC classification number: F03B3/02 , F01D1/08 , F01D5/025 , F01D9/026 , F01D17/165 , F01D25/145 , F03B3/183 , F03B11/006 , F03B11/02 , F05B2210/11 , F05D2210/11 , F05D2250/131 , Y02E10/223 , Y02E10/226
Abstract: A cryogenic liquid turbine is provided, wherein, impeller end of the rotor and nozzle assembly are received into cavity of volute, and main part of the volute is put into perlite cold box; insulation pad is used between the volute and machine housing to insulate heat; impeller outlet is connected to diffuser pipe. A nozzle assembly is connected to the machine housing by a nozzle compression flange; a nozzle compression plate adjusts a compactness of nozzle vanes by a disc spring; a nozzle turntable is connected on a nozzle chassis, and adjusts the nozzle vane stagger angle by adjusting mechanism passing through the volute; impeller shroud side seal is axially fixed on the nozzle compression flange, and a shaft seal is axially fixed to a seal gas part; the seal gas part and an oil seal are axially fixed to the machine housing by a bolt.
Abstract translation: 提供了一种低温液体涡轮机，其中转子和喷嘴组件的叶轮端部被容纳在蜗壳的空腔中，并将蜗壳的主要部分放入珍珠岩冷箱中; 蜗壳和机壳之间使用绝缘垫来隔热; 叶轮出口连接到扩散管。 喷嘴组件通过喷嘴压缩法兰连接到机器壳体; 喷嘴压缩板通过碟形弹簧调节喷嘴叶片的紧凑度; 喷嘴转盘连接在喷嘴底座上，通过调节机构通过蜗壳调节喷嘴叶片交错角度; 叶轮护罩侧密封件轴向固定在喷嘴压缩凸缘上，轴封固定在密封气体部分上; 密封气体部分和油封通过螺栓轴向固定到机器壳体。
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