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1. 发明申请

US20190032490A1 MISTUNED CONCENTRIC AIRFOIL ASSEMBLY AND METHOD OF MISTUNING SAME 审中-公开
公开(公告)号：US20190032490A1
公开(公告)日：2019-01-31
申请号：US16106221
申请日：2018-08-21
申请人： United Technologies Corporation
发明人： Richard K. Hayford , Steven J. Ford
IPC分类号： F01D5/14 , F01D5/02 , F01D25/06 , F01D5/22
CPC分类号： F01D5/146 , F01D5/022 , F01D5/225 , F01D25/06 , F05D2260/961 , Y02T50/673
摘要： An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an annular shroud having a radially inner face and a radially outer face opposing the radially inner face, a radially inner array of airfoils extending from the radially inner face, and a radially outer array of airfoils extending from the radially outer face. The radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section. At least one, but fewer than each, airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils. A method of reducing a vibratory response of airfoils is also disclosed.

2. 发明申请

US20190017516A1 COMPRESSOR ROTOR STACK ASSEMBLY FOR GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20190017516A1
公开(公告)日：2019-01-17
申请号：US15650066
申请日：2017-07-14
申请人： United Technologies Corporation
发明人： John C. DiTomasso
IPC分类号： F04D29/32 , F04D29/18 , F02C3/06
CPC分类号： F01D5/30 , F01D5/022 , F01D5/025 , F01D5/06 , F01D5/066 , F05B2220/302 , F05B2240/24 , F05B2240/80 , F05D2220/32 , F05D2230/60
摘要： A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.

3. 发明申请

US20170241348A1 CONNECTION OF ROTATABLE PARTS 审中-公开
公开(公告)号：US20170241348A1
公开(公告)日：2017-08-24
申请号：US15417584
申请日：2017-01-27
申请人： ROLLS-ROYCE plc
发明人： Johnathan H. WILSHAW
IPC分类号： F02C7/36 , F04D29/64 , F04D29/32 , F02K3/06 , F01D5/02 , F04D29/054 , F02C3/04
CPC分类号： F02C7/36 , F01D5/02 , F01D5/022 , F01D5/023 , F01D5/06 , F01D5/066 , F02C3/04 , F02K3/06 , F04D29/054 , F04D29/321 , F04D29/644 , F05D2220/32 , F05D2230/60 , F05D2230/64 , F05D2240/60 , F05D2260/30
摘要： A gas turbine engine has two connected parts that rotate together during use. The two parts have a tensile loading that acts to separate the two parts in use. The two parts may be neighbouring rotating stages of a gas turbine engine. The two parts are connected together using both a mechanical fastener and an interlocking feature. The interlocking feature may be, for example, interlocking conical surfaces and/or interlocking protrusions.

4. 发明申请

US20170226861A1 ROTARY ASSEMBLY FOR A TURBINE ENGINE COMPRISING A SELF-SUPPORTED ROTOR COLLAR 审中-公开
公开(公告)号：US20170226861A1
公开(公告)日：2017-08-10
申请号：US15519351
申请日：2015-10-15
申请人： SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
发明人： Gael Frederic Claude Cyrille EVAIN , Pierre-Louis Alexandre CARLOS , Claire Charlotte GROLEAU , Mathieu Louis Jean LEDUC , David MARSAL
IPC分类号： F01D5/02 , F01D25/24 , F01D25/00 , F04D29/52 , F04D29/54 , F04D29/02 , F01D9/04 , F04D19/02
CPC分类号： F01D5/022 , F01D9/041 , F01D11/001 , F01D25/005 , F01D25/24 , F04D19/022 , F04D29/023 , F04D29/522 , F04D29/542 , F05D2230/642 , F05D2250/232 , F05D2300/6033 , Y02T50/672
摘要： A rotary assembly for a turbine engine is provided. The assembly includes a rotor with two consecutive rotor stages equipped with a plurality of movable vanes, and an annular rotor shroud connecting the two consecutive rotor stages; and a stator including a stator stage, provided with a plurality of fixed vanes and disposed between the two rotor stages, and an annular stator ring mounted on the fixed vanes. Either the rotor shroud or the stator ring bears at least one wiper designed to cooperate with an abradable track on the other of the rotor shroud and stator ring, such that the rotor shroud includes at at least one of its upstream or downstream ends an inclined contact portion resting on an inclined bearing surface of the corresponding rotor stage, the bearing surface being the outer surface of a projection extending from a base portion of the corresponding rotor stage.

5. 发明申请

US20170022816A1 MIM-FORMED TiA1 TURBINE WHEEL SURROUNDING A CAST/MACHINED CORE 审中-公开
标题翻译： MIM形成的TiA1涡轮轮环绕铸造/加工核心
公开(公告)号：US20170022816A1
公开(公告)日：2017-01-26
申请号：US14808305
申请日：2015-07-24
申请人： BorgWarner Inc.
发明人： Brock Fraser
IPC分类号： F01D5/02 , B22F7/04 , B22F3/02 , B22D19/00
CPC分类号： F01D5/02 , B22D19/0054 , B22F3/02 , B22F3/17 , B22F3/225 , B22F5/009 , B22F7/04 , B22F2207/11 , B22F2998/10 , B23P15/006 , B29C45/00 , C22C14/00 , C22C21/00 , F01D5/022 , F01D5/06 , F05D2220/30 , F05D2230/21 , F05D2230/22 , F05D2230/24 , F05D2230/30 , F05D2250/232 , B22F5/04 , B22F7/062 , B22F7/08
摘要： A number of variations may include a method that may include casting or providing a central core comprising titanium aluminide; and metal injection molding a shell comprising titanium aluminide around the central core to produce a rotor assembly.
摘要翻译：许多变型可以包括可以包括铸造或提供包含钛铝化物的中心芯的方法; 以及金属注射成型壳体，其包含围绕中心芯的铝酸铝以产生转子组件。

6. 发明授权

US08784062B2 Asymmetrically slotted rotor for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的不对称开槽的转子
公开(公告)号：US08784062B2
公开(公告)日：2014-07-22
申请号：US13283710
申请日：2011-10-28
申请人： Gabriel L. Suciu , Stephen P. Muron , Christopher M. Dye , Ioannis Alvanos , Brian D. Merry
发明人： Gabriel L. Suciu , Stephen P. Muron , Christopher M. Dye , Ioannis Alvanos , Brian D. Merry
IPC分类号： F01D11/00 , F01D5/02
CPC分类号： F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
摘要： A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
摘要翻译：用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度。多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。

7. 发明申请

US20130343892A1 PROPFAN ENGINE 有权
标题翻译： PROPFAN发动机
公开(公告)号：US20130343892A1
公开(公告)日：2013-12-26
申请号：US13359194
申请日：2012-01-26
申请人： Richard G. STRETTON , Nicholas HOWARTH
发明人： Richard G. STRETTON , Nicholas HOWARTH
IPC分类号： F01D5/02
CPC分类号： F01D5/022 , B64C11/48 , B64D29/00 , B64D2027/005 , F01D5/143 , F01D5/145 , F02C3/067 , F02K3/072 , F05D2220/324 , F05D2220/325 , F05D2240/14 , F05D2250/70 , Y02T50/66 , Y02T50/671
摘要： The present disclosure relates to a propfan engine comprising: one or more rotor stages comprising a plurality of rotors; and an outer wall comprising an outer profile, at least a portion of the outer profile defining a substantially circular cross-section, wherein the diameter of the substantially circular cross-section increases in the direction of flow over the outer wall and downstream of a leading edge of the rotors, and the diameter increases at substantially all points defining the circumference of the substantially circular cross-section.
摘要翻译：本公开涉及一种普通发动机，其包括：一个或多个转子级，包括多个转子; 以及外壁，其包括外轮廓，所述外轮廓的至少一部分限定基本上圆形的横截面，其中所述基本圆形横截面的直径在所述外壁上的流动方向上增加，并且在前缘转子的边缘，并且在限定基本圆形横截面的圆周的基本上所有点处的直径增加。

8. 发明授权

US08104257B2 Tip turbine engine with multiple fan and turbine stages 有权
标题翻译：具有多个风扇和涡轮级的涡轮发动机
公开(公告)号：US08104257B2
公开(公告)日：2012-01-31
申请号：US11719589
申请日：2004-12-01
申请人： James W. Norris , Craig A. Nordeen , Gary Roberge
发明人： James W. Norris , Craig A. Nordeen , Gary Roberge
IPC分类号： F02C3/045
CPC分类号： F02C3/14 , F01D5/022 , F02C3/067 , F02C3/073 , F02K3/068 , F02K3/072 , F05D2260/40311 , Y02T50/673
摘要： A tip turbine engine (10) provides first and second turbines (32) rotatably driven by a combustor (30) generating a high-energy gas stream. The first turbine (32) is mounted at an outer periphery of a first fan (24a), such that the first fan is rotatably driven by the first turbine (32a). The second turbine (32b) is mounted at an outer periphery of a second fan (24b), and is rotatably driven by the high-energy gas stream. In one embodiment, the first turbine (32a) rotatably drives a plurality of stages of first compressor blades (54) in an axial compressor (22) in a first rotational direction, while the second turbine (32b) rotatably drives a plurality of stages of second compressor blades (52) in the axial compressor (22) in a second rotational direction opposite the first. By rotatably driving alternating stages of compressor blades in opposite directions, the efficiency of the axial compressor (22) is increased and/or the number of stages of compressor blades can be reduced. Other variations are described in additional embodiments.
摘要翻译：顶端涡轮发动机（10）提供由可产生高能气流的燃烧器（30）可旋转地驱动的第一和第二涡轮机（32）。第一涡轮（32）安装在第一风扇（24a）的外周，使得第一风扇由第一涡轮机（32a）旋转驱动。第二涡轮（32b）安装在第二风扇（24b）的外周，由高能气流旋转驱动。在一个实施例中，第一涡轮机（32a）以第一旋转方向可旋转地驱动轴向压缩机（22）中的多级第一压缩机叶片（54），而第二涡轮（32b）可旋转地驱动多个级第二压缩机叶片（52）在轴向压缩机（22）中沿与第一压缩机相反的第二旋转方向。通过以相反的方向旋转地驱动压缩机叶片的交替级，轴流式压缩机（22）的效率提高和/或压缩机叶片的级数可以减少。在另外的实施例中描述了其它变型。

9. 发明授权

US08083030B2 Gearbox lubrication supply system for a tip engine 有权
标题翻译：齿轮箱润滑供油系统
公开(公告)号：US08083030B2
公开(公告)日：2011-12-27
申请号：US11718521
申请日：2004-12-01
申请人： Lawrence E. Portlock
发明人： Lawrence E. Portlock
IPC分类号： F16H57/04 , F01D25/18 , F02C7/06
CPC分类号： F16H57/0421 , F01D5/022 , F01D25/18 , F01D25/20 , F02C3/073 , F02C7/32 , F02C7/36 , F02K3/068 , F05D2260/20 , F05D2260/40311 , F16H57/0482 , Y02T50/675
摘要： An oil system (118) for a tip turbine engine (10) includes an annular lubricating fluid plenum (136) which sprays lubricating fluid through a multitude of lubricating fluid passages (144, 146, 148) and into the multitude of passages (152, 154, 156) located within a gearbox assembly (90) as they revolve thereby. Lubricating fluid is thereby communicated directly into the gearbox assembly (90) and returned to a sump tank (140) through a multitude of drain passages.
摘要翻译：一种用于顶端涡轮发动机（10）的油系统（118）包括环形润滑流体通风室（136），其通过多个润滑流体通道（144,146,148）喷射润滑流体并进入多个通道位于齿轮箱组件（90）内的，当它们旋转时。因此，润滑流体直接连接到齿轮箱组件（90）中并且通过多个排放通道返回到贮槽（140）。

10. 发明授权

US08033092B2 Tip turbine engine integral fan, combustor, and turbine case 有权
标题翻译：涡轮发动机一体式风机，燃烧器和涡轮机壳
公开(公告)号：US08033092B2
公开(公告)日：2011-10-11
申请号：US11720539
申请日：2004-12-01
申请人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
发明人： Gabriel L. Suciu , James W. Norris , Craig A. Nordeen , Brian Merry
IPC分类号： F02K3/02
CPC分类号： F01D5/187 , F01D1/023 , F01D5/022 , F01D21/045 , F02C3/045 , F02C3/08 , F02C3/107 , F05D2300/433 , Y02T50/676
摘要： A tip turbine engine assembly includes an integral engine outer case located radially outward from a fan assembly. The integral outer case includes a rear portion and a forward portion with an arcuate portion that curves radially inwardly to form a compartment. An annular combustor is housed and mounted in the compartment. Fan inlet guide vanes are integrally formed with the arcuate portion to form the integral case portion. The rear portion, forward portion, and fan inlet guide vanes are integrally formed in a casting process.
摘要翻译：顶端涡轮发动机组件包括从风扇组件径向向外定位的一体式发动机外壳。一体的外壳包括后部和具有弓形部分的向前部分，其径向向内弯曲以形成隔间。环形燃烧器容纳并安装在隔室中。风扇入口导向叶片与弓形部分一体地形成，以形成一体的壳体部分。后部，前部和风扇入口导向叶片在铸造过程中一体地形成。

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