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1. 发明授权

US08899924B2 Non-mechanically fastened TOBI heat shield 有权
标题翻译：非机械固定TOBI隔热罩
公开(公告)号：US08899924B2
公开(公告)日：2014-12-02
申请号：US13164234
申请日：2011-06-20
申请人： Ioannis Alvanos
发明人： Ioannis Alvanos
IPC分类号： F04D31/00 , F01D5/08 , F02C7/18
CPC分类号： F01D5/081 , F02C7/18 , F05D2260/30 , Y02T50/676 , Y10T29/49327
摘要： A high pressure turbine includes a stator, a rotor, a tangential on-board injector, and a heat shield. The rotor is located downstream of the stator and the tangential on-board injector directs cooling air to the rotor. The heat shield is retained by abutment with the stator and the tangential on-board injector.
摘要翻译：高压涡轮机包括定子，转子，切向的车载喷射器和隔热罩。转子位于定子的下游，切向的车载喷射器将冷却空气引导到转子。隔热板通过与定子和切向机载喷射器的邻接保持。

2. 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。

3. 发明申请

US20120301303A1 HYBRID CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的混合陶瓷基体复合材料结构
公开(公告)号：US20120301303A1
公开(公告)日：2012-11-29
申请号：US13116144
申请日：2011-05-26
申请人： Ioannis Alvanos , Gabriel L. Suciu
发明人： Ioannis Alvanos , Gabriel L. Suciu
IPC分类号： F01D5/22 , B21K25/00
CPC分类号： F01D5/284 , C04B37/001 , C04B2237/38 , C04B2237/86 , F01D5/282 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2300/6033 , Y10T29/49321 , Y10T29/49323
摘要： A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner ring.
摘要翻译：用于燃气涡轮发动机的叶片结构包括集成在CMC外环和金属合金内圈之间的多个CMC翼型部分。

4. 发明申请

US20120301285A1 CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE TURBINE 有权
标题翻译：用于气体涡轮发动机涡轮机的陶瓷基体复合材料结构
公开(公告)号：US20120301285A1
公开(公告)日：2012-11-29
申请号：US13116053
申请日：2011-05-26
申请人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry , Christopher M. Dye
发明人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry , Christopher M. Dye
IPC分类号： F01D9/04
CPC分类号： F01D5/284 , F01D5/147 , F01D5/282 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2240/12 , F05D2300/6033
摘要： A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.
摘要翻译：一种用于燃气涡轮发动机的叶片结构，其包括集成在CMC外环和CMC内环之间的多个CMC翼型部分。

5. 发明申请

US20120301275A1 INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR MODULE FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的集成陶瓷基体复合转子模块
公开(公告)号：US20120301275A1
公开(公告)日：2012-11-29
申请号：US13116129
申请日：2011-05-26
申请人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
发明人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
IPC分类号： F01D5/02 , B23P15/04
CPC分类号： F01D5/34 , C04B37/001 , C04B2237/38 , C04B2237/76 , C04B2237/84 , F01D5/282 , F01D5/284 , F01D11/001 , F05D2300/6033 , Y10T29/4932
摘要： A rotor module for a gas turbine engine includes a multiple of CMC airfoil rows which extend from a common CMC drum.
摘要翻译：用于燃气涡轮发动机的转子模块包括从公共CMC鼓延伸的多个CMC翼型排。

6. 发明授权

US08162605B2 Gas turbine engine case 有权
标题翻译：燃气涡轮发动机外壳
公开(公告)号：US08162605B2
公开(公告)日：2012-04-24
申请号：US12013617
申请日：2008-01-14
申请人： Ioannis Alvanos , Gabriel L. Suciu , Brian D. Merry
发明人： Ioannis Alvanos , Gabriel L. Suciu , Brian D. Merry
IPC分类号： F01D25/28
CPC分类号： F01D25/24 , F01D25/243 , F01D25/246 , F05D2230/60 , Y02T50/671 , Y10T29/49826
摘要： A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.
摘要翻译：燃气涡轮发动机的壳体包括单件壳体，其包括燃烧器壳体部分和与燃烧器壳体部分一体形成为一体的涡轮壳体部分。在一个示例中，单件式壳体包括过渡管道/中涡轮机壳体部分，其与燃烧器和涡轮机壳体部分整体形成。

7. 发明授权

US07708520B2 Gas turbine engine with concave pocket with knife edge seal 有权
标题翻译：带凹口的燃气轮机，带刀口密封
公开(公告)号：US07708520B2
公开(公告)日：2010-05-04
申请号：US11605678
申请日：2006-11-29
申请人： Roger E. Paolillo , Ioannis Alvanos , Cheng-Zhang Wang
发明人： Roger E. Paolillo , Ioannis Alvanos , Cheng-Zhang Wang
IPC分类号： F01D11/02
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.
摘要翻译：燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。

8. 发明申请

US20090257877A1 ASYMMETRICAL ROTOR BLADE FIR-TREE ATTACHMENT 有权
标题翻译：不对称转子叶片FIR-TREE附件
公开(公告)号：US20090257877A1
公开(公告)日：2009-10-15
申请号：US12103673
申请日：2008-04-15
申请人： Ioannis Alvanos , John J. OConnor
发明人： Ioannis Alvanos , John J. OConnor
IPC分类号： F01D5/02 , F01D5/30
CPC分类号： F01D5/3007
摘要： A rotor blade for a gas turbine engine includes an asymmetric attachment section received within a rotor disk rim with an asymmetric slot.
摘要翻译：用于燃气涡轮发动机的转子叶片包括容纳在具有不对称槽的转子盘形边缘内的非对称附接部分。

9. 发明申请

US20080044284A1 Segmented fluid seal assembly 审中-公开
标题翻译：分段流体密封组件
公开(公告)号：US20080044284A1
公开(公告)日：2008-02-21
申请号：US11505165
申请日：2006-08-16
申请人： Ioannis Alvanos
发明人： Ioannis Alvanos
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D11/02 , F05D2230/60 , F05D2260/30
摘要： A rotor assembly for a turbine engine includes a rotor disk having rotor blades mounted about the circumference and rotatable about a central longitudinal axis. A fluid seal extends about the circumference of the rotor disk in close proximity to a stationary component to separate the space between the rotor blades and a stationary component into separate cavities. The fluid seal includes a plurality of disk seal segments and a plurality of blade seal segments. The disk seal segments each attach to the rotor disk between the rotor blades. The blade seal segments attach to the blades. After the blades are assembled the blade seal segments and the disk seal segments align to form a segmented, ring-like fluid seal around the circumference of the rotor disk.
摘要翻译：用于涡轮发动机的转子组件包括转子盘，转子盘具有围绕圆周安装的转子叶片，并可围绕中心纵向轴线旋转。流体密封件围绕转子盘的圆周延伸，靠近固定部件，以将转子叶片和固定部件之间的空间分离成单独的空腔。流体密封件包括多个盘密封段和多个叶片密封段。盘密封片段各自连接到转子叶片之间的转子盘上。叶片密封段附接到叶片。在叶片组装之后，叶片密封段和盘密封段对齐以在转子盘的圆周周围形成分段的环状流体密封。

10. 发明申请

US20070059158A1 Turbine cooling air sealing 有权
标题翻译：涡轮冷却空气密封
公开(公告)号：US20070059158A1
公开(公告)日：2007-03-15
申请号：US11224613
申请日：2005-09-12
申请人： Ioannis Alvanos , Rajendra Agrawal , Hector Pinero
发明人： Ioannis Alvanos , Rajendra Agrawal , Hector Pinero
IPC分类号： F03B11/00
CPC分类号： F01D5/081 , F01D11/001 , F01D25/12 , F02C7/18 , F02C7/28
摘要： A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing means restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing means restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing means and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.
摘要翻译：涡轮发动机部分具有静止叶片台和旋转叶片台。叶片台与叶片台间隔开以在它们之间形成环形室。歧管将加压流体输送到腔室。外径（OD）密封装置限制加压流体从腔室泄漏。内径（ID）密封装置限制加压流体从腔室泄漏。流动引导件在内径密封装置和歧管之间径向延伸。流动导向装置将室平分成一个固定室部分和旋转室部分，旋转室部分至少部分地沿着第一叶片台的圆盘。

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