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91. 发明申请

WO2004007914A1 ABGASTURBINE 审中-公开
标题翻译：燃气轮机
公开(公告)号：WO2004007914A1
公开(公告)日：2004-01-22
申请号：PCT/EP2003/005620
申请日：2003-05-28
申请人： DAIMLERCHRYSLER AG , DÖRING, Volker , HENSEL, Hans-Dieter , SCHICK, Peter
发明人： DÖRING, Volker , HENSEL, Hans-Dieter , SCHICK, Peter
IPC分类号： F01D17/16
CPC分类号： F01D17/167 , F01D17/20 , F02B37/025 , F02B39/00 , F05D2220/40 , Y02T10/144
摘要： Die Erfindung bezieht sich auf Abgasturbine für einen Turbolader einer Verbrennungskraftmaschine mit einem einen Einlasskanal (13) aufweisenden Laufrad, das in einem Turbinengehäuse (1) aufgenommenen ist, wobei im Bereich des Aussenumfangs des Laufrads ein Gitterring (9) mittels einer Stellvorrichtung (22) in einen das Laufrad umgebenden Ringraum (8) hinein- und herausschiebbar ist, wobei die Stellvorrichtung (22) aus einem Betätigungszylinder (22') besteht, der an eine Halterung (23) angeschlossen ist, die im Bereich des Aussenumfangs eines zylindrischen den Auslasskanal (14) koaxial umgebenden Innenteils (4) angeschlossen und mit dem Gitterring (9) verbunden ist.
摘要翻译：本发明涉及（9）通过在调节装置（22）的装置，以废气涡轮机的用于内燃发动机的具有一个入口通道（13），其具有容纳在涡轮机壳体（1）叶轮，其中，在所述叶轮的网格环的外周的区域中的涡轮增压器围绕所述叶轮的环形空间（8）和被推出，其特征在于，其连接到保持器（23）的致动缸（22“）的所述致动装置（22）（在圆柱形出口通道14的外周的区域中是）同轴地围绕所述内部分（4）插入并连接到电网环（9）。

92. 发明申请

WO2003100221A1 ABGASTURBINE FÜR EINEN TURBOLADER 审中-公开
标题翻译：燃气轮机涡轮增压器
公开(公告)号：WO2003100221A1
公开(公告)日：2003-12-04
申请号：PCT/EP2003/003001
申请日：2003-03-22
申请人： DAIMLERCHRYSLER AG , DÖRING, Volker , HENSEL, Hans-Dieter , SCHICK, Peter
发明人： DÖRING, Volker , HENSEL, Hans-Dieter , SCHICK, Peter
IPC分类号： F01D17/16
CPC分类号： F02C6/12 , F01D17/141 , F01D17/167 , F02B37/025 , F05D2220/40 , Y02T10/144
摘要： Die Erfindung betrifft eine Abgasturbine für einen Turbolader, deren Laufrad drehbar in einem Turbinengehäuse mit einem spiralförmigen Einlasskanal (13) gelagert ist, an den sich ein das Laufrad umgebender Ringraum (8) anschliesst, wobei nahe dem äusseren Umfang des Laufrades in einem axial versetzten Ringspalt (3) zwischen dem Turbinengehäuse und einer Innenführung (4) ein Leitgitter (9) vorgesehen ist, das an seiner dem Ringraum abgewandten Stirnseite mit axial gerichteten Gleitzapfen (6) fest verbunden ist, die durch Bohrungen einer gehäusefesten Kulisse (7) greifen, und das mittels einer Schiebehülse (5), die auf die Enden der Gleitzapfen (6) wirkt, axial in den Ringraum geschoben werden kann, wobei das Leitgitter (9) Leitschaufeln (10) zwischen zwei stirnseitigen Deckscheiben (11, 12) aufweist, von denen in einer Position des Leitgitters (9) im Ringspalt (3) die dem Ringraum zugewandte Deckscheibe (11) den Ringspalt abdeckt, während bei einer Position des Leitgitters im Ringraum der Ringspalt von der anderen Deckscheibe (12) geschlossen ist. Es wird vorgeschlagen, dass die Gleitzapfen (6) nach der Montage des Axialschiebers (2) und der Schiebehülse (5) auf der Innenführung mit der Schiebehülse (5) stoffschlüssig verbunden werden.
摘要翻译：本发明可旋转地涉及一种排气涡轮机的涡轮增压器，所述叶轮与一螺旋入口通道（13）被安装时，一个涡轮机壳体，其叶轮周围环室（8）相连接，其特征在于，靠近叶轮的在轴向偏移环形间隙的外周（3）在涡轮机壳体和内引导（4）之间，引导挡板设置（9），其被牢固地轴向取向的导向销连接在其一侧远离所述环形腔室的端面（6），其通过壳体固定导向件（7）的孔卡合，并且作用在导向销（6）的端部的滑动套筒的装置（5）可沿轴向推到环形空间，引导格栅（9）叶片（10）两者之间的端盖板（11，12），其中在导向挡板（9）的位置面向所述环形空间盖盘（11）覆盖在环形间隙（3）的环形间隙，而在所述导向挡板的在R的位置 ingraum被关闭时，其它的盖盘（12）的环形间隙。本发明提出，在导向销（6）的轴向滑动（2）的组装和在与滑动套筒内引导所述滑动套筒（5）（5）之后一体地连接。

93. 发明申请

WO01053679A1 TURBOCHARGER WITH SLIDING BLADES HAVING COMBINED DYNAMIC SURFACES AND HEAT SCREEN AND UNCOUPLED AXIAL ACTUATING DEVICE 审中-公开
标题翻译：具有组合动力表面的滑动刀片和加热筛和未激励的轴向动作装置的涡轮增压器
公开(公告)号：WO01053679A1
公开(公告)日：2001-07-26
申请号：PCT/FR2000/000066
申请日：2000-01-14
IPC分类号： F02B39/00 , F01D17/14 , F01D17/16 , F02B37/22 , F02B37/24 , F02C6/12
CPC分类号： F02C6/12 , F01D17/167 , F02B37/24 , F05D2220/40
摘要： The invention concerns a turbocharger having a variable geometry turbine intake incorporating a mobile cylindrical piston (70) for varying the area of the induction nozzle in the turbine (18). Blades (90) mounted on the piston for controlling the flow in the nozzle penetrate through a slotted heat shield (92) having a central opening wherein the rear disc of the turbine wheel is embedded to provide a smooth aerodynamic flow in the turbine vanes. A shield (100) engaged between the heat screen and a central housing of the turbocharger prevents the gas from the rear disc cavity from recycling into the cavity housing the blades further enhancing the aerodynamic flow. An axial actuating device (77) is secured for operating the piston by means of a shaft coupled by a cross (72) to the piston and coupled to an actuating hub (118) in the actuating device by quick connect unthreaded connection (122).
摘要翻译：本发明涉及一种具有可变几何涡轮进气口的涡轮增压器，其包括用于改变涡轮机（18）中的感应喷嘴的面积的可移动圆柱形活塞（70）。安装在活塞上用于控制喷嘴中的流动的叶片（90）穿过具有中心开口的开槽式热屏蔽（92），其中涡轮机叶轮的后盘被嵌入以在涡轮机叶片中提供平滑的空气动力学流。接合在热屏和涡轮增压器的中心壳体之间的屏蔽（100）防止来自后盘腔的气体再循环到容纳叶片的空腔中，进一步增强空气动力学流。轴向致动装置（77）被固定以通过由十字架（72）联接到活塞并通过快速连接无螺纹连接（122）联接到致动装置中的致动毂（118）的轴来操作活塞。

94. 发明公开

KR1020130098872A 터보 과급기 审中-实审
标题翻译：涡轮喷油器和涡轮旁通阀的涡轮增压器
公开(公告)号：KR1020130098872A
公开(公告)日：2013-09-05
申请号：KR1020127031024
申请日：2011-04-20
申请人： 허니웰 인터내셔널 인코포레이티드
发明人： 롬바르드,알랑 , 티리옹,미쉘 , 세레스,니콜라스
IPC分类号： F02B37/18 , F02B39/00 , F01D9/02 , F01D9/04
CPC分类号： F01D17/105 , F01D17/148 , F01D17/167 , F02C6/12 , F05D2220/40 , F05D2250/311 , F05D2250/411 , F05D2260/606 , F05D2270/66
摘要： 터보 과급기는 배기가스가 터빈 휠을 바이패스하게 하는 환형 바이패스 통로를 구비한다. 상기 바이패스 통로 내에는 환형 바이패스 밸브가 배치된다. 상기 바이패스 밸브는 고정식 환형 밸브 시트와, 상기 밸브 시트와 동축으로 배치된 회전식 환형 밸브 부재를 포함한다. 상기 밸브 부재는 상기 밸브 시트에 대해 배치되며 밸브 시트와 밸브 부재의 각각의 오리피스들 사이의 정렬 정도를 선택적으로 변경하기 위해 축 둘레에서 회전가능하다. 터빈은 베인 조립체를 갖는 노즐을 구비한다. 일 실시예에서, 베인은 고정형 베인만을 갖는다. 다른 실시예에서, 상기 베인 조립체는 고정형 베인 및 가변형 베인 모두를 구비하고, 상기 가변형 베인은 회전식 밸브 부재와 함께 회전하는 로터의 일부분이다.

95. 发明授权

KR101223968B1 유압 서보 구동 장치 및 이것을 사용한 가변 터보 과급기 失效
标题翻译：液压伺服驱动装置及其可变的涡轮增压器
公开(公告)号：KR101223968B1
公开(公告)日：2013-01-21
申请号：KR1020107016856
申请日：2009-03-02
申请人： 가부시키가이샤 고마쓰 세이사쿠쇼
发明人： 코즈카다이스케 , 타지마마사유키 , 아카시미츠마사 , 호리슈우지
IPC分类号： F15B13/042 , F02B37/22
CPC分类号： F15B9/12 , F01D17/143 , F01D17/167 , F02B37/24 , F05D2220/40 , F05D2260/406 , F15B21/042 , F15B2013/0409 , Y02T10/144
摘要： 파일럿 압에 의해 슬라이딩되어 기름의 공급 및 차단을 스위칭하는 파일럿 스풀(20)과, 파일럿 스풀(20)에 추종해서 슬라이딩하는 서보 피스톤(11)과, 서보 피스톤(11)의 이동량을 검출하는 스트로크 센서(15)와, 서보 피스톤(11)을 이동시키기 위한 기름이 유입되는 제 1 유압실(51)과, 펌프로부터의 기름이 공급되는 펌프 포트와 제 1 유압실(51)을 연통시키는 제 1 피스톤 유로(65)와, 제 1 유압실(51)과 드레인 포트를 연통시키는 배출 순환 유로(66)를 구비하고 있는 구성으로 했다.

96. 发明公开

KR1020040002526A 터빈 无效
标题翻译：涡轮
公开(公告)号：KR1020040002526A
公开(公告)日：2004-01-07
申请号：KR1020030036019
申请日：2003-06-04
申请人： 홀셋 엔지니어링 컴퍼니 리미티드
发明人： 샤프니콜라스 , 가렛트스티븐
IPC分类号： F02B37/22
CPC分类号： F01D17/167 , F01D5/141 , F01D17/165
摘要： PURPOSE: A turbine is provided to disturb the pressure fields generated by vanes by forming a discontinuity in a trailing edge or a turbine blade and to reduce vibrations which cause damage to the turbine blade. CONSTITUTION: A turbine is composed of a turbine wheel formed with radial blades and supported in a housing(1) to rotate about an axis(12); an annular inlet passageway(4) extending radially inward to the turbine wheel; and an annular array of vanes(10) extending across the inlet passageway. The inlet passageway is defined between first and second annular walls. Each vane has a trailing edge(10a) extending adjacently to turbine wheel blades(11) and each trailing edge of the vanes deviates from a straight line over at least a portion of the length formed by the ends. The trailing edge of each vane has a discontinuity positioned in the middle side of the ends.
摘要翻译：目的：提供涡轮以通过在后缘或涡轮叶片中形成不连续性来干扰由叶片产生的压力场，并且减少对涡轮叶片造成损坏的振动。构成：涡轮机由形成有径向叶片的涡轮机叶轮组成，并被支撑在壳体（1）中以围绕轴线（12）旋转; 环形入口通道（4），径向向内延伸到涡轮机轮; 以及横跨入口通道延伸的环形阵列的叶片（10）。入口通道限定在第一和第二环形壁之间。每个叶片具有与涡轮叶片（11）相邻延伸的后缘（10a），并且叶片的每个后缘在由端部形成的长度的至少一部分上偏离直线。每个叶片的后缘具有位于端部中间侧的不连续部分。

97. 发明公开

KR1020030081059A 가변형상 터빈 无效
标题翻译：变形涡轮机
公开(公告)号：KR1020030081059A
公开(公告)日：2003-10-17
申请号：KR1020030021753
申请日：2003-04-07
申请人： 홀셋 엔지니어링 컴퍼니 리미티드
发明人： 멀로이존 , 파커존프레더릭
IPC分类号： F02B37/22
CPC分类号： F02B37/24 , F01D17/143 , F01D17/167 , Y02T10/144
摘要： 본 발명은 터빈 흡기 유동 패스를 따라 슬롯에 신축가능하게 형성되는 노즐 베인을 포함하는 터보차저의 가변형상 터빈에 관한 것이다. 상기 베인은 베인의 코드를 감소시키고 터빈 효율의 피크(peak)를 형상에 따라 다르게 할 수 있다.

98. 发明申请

US20180334921A1 STATOR ARRANGEMENT 审中-公开
公开(公告)号：US20180334921A1
公开(公告)日：2018-11-22
申请号：US15983555
申请日：2018-05-18
申请人： ROLLS-ROYCE plc
发明人： Piera CARUGNO
IPC分类号： F01D17/16
CPC分类号： F01D17/167 , F01D5/146 , F01D9/04 , F05D2220/32
摘要： A stator arrangement for use in a gas turbine engine, the arrangement comprising an inner outlet guide wall having a central axis, the inner outlet guide wall comprising a first aerofoil extending radially relative to the central axis; the an inner outlet guide wall further comprising a second aerofoil extending radially relative to the central axis, the second aerofoil being relatively displaceable between a first position and a second position; the first aerofoil combining with the second aerofoil to form a combined aerofoil when the second aerofoil is in the first position, and separating to form two or more aerofoils when the second aerofoil is relatively displaced, in use, from the first position towards the second position; wherein one or more of a profile, shape or configuration of the second aerofoil, when in the second position, are substantially identical to that of the first aerofoil.

99. 发明申请

US20180209294A1 AIRCRAFT COMPRISING A TURBINE ENGINE INCORPORATED INTO THE REAR FUSELAGE WITH VARIABLE SUPPLY 审中-公开
公开(公告)号：US20180209294A1
公开(公告)日：2018-07-26
申请号：US15745704
申请日：2016-07-21
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Francois GALLET , Nicolas Jerome Jean TANTOT
IPC分类号： F01D17/14 , B64D27/20 , F02K3/072 , F02K3/12 , F01D17/16
CPC分类号： F01D17/141 , B64C11/48 , B64D27/14 , B64D27/20 , F01D1/023 , F01D1/24 , F01D17/105 , F01D17/14 , F01D17/145 , F01D17/148 , F01D17/16 , F01D17/162 , F01D17/167 , F02C3/10 , F02K1/52 , F02K3/072 , F02K3/075 , F02K3/077 , F02K3/12 , F05D2220/323 , F05D2240/128 , F05D2260/606 , F05D2270/093 , F05D2270/102
摘要： The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).

100. 发明申请

US20180038239A1 TURBINE ASSEMBLY AND METHOD FOR FLOW CONTROL 审中-公开
公开(公告)号：US20180038239A1
公开(公告)日：2018-02-08
申请号：US15227194
申请日：2016-08-03
申请人： Solar Turbines Incorporated
发明人： Scott L. Stafford
IPC分类号： F01D17/12 , F01D25/24 , F01D9/04 , F01D5/02 , F01D5/12
CPC分类号： F01D25/246 , F01D9/041 , F01D17/167 , F05D2220/40 , F05D2270/80
摘要： A turbine assembly of an engine is disclosed. The turbine assembly includes a nozzle ring for receiving exhaust gases from a combustion chamber having a plurality of guide vanes for guiding the exhaust gases, a stator ring disposed downstream to the nozzle ring, and a rotor disposed circumferentially within the stator ring. The stator ring includes a plurality of stator vanes adapted to receive the exhaust gases through the guide vanes of the nozzle ring. The stator ring is axially movable between a first position and a second position along at least one cross-key pin disposed between the stator ring and a turbine casing. Each of the plurality of stator vanes moves into a throat plane of each pair of the plurality of guide vanes in the first position of the stator ring, and moves out of the throat plane in the second position of the stator ring.

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