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1. 发明申请

US20120102969A1 CENTRIFUGAL COMPRESSOR WITH BLEED FLOW SPLITTER FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的离心式分流器的离心式压缩机
公开(公告)号：US20120102969A1
公开(公告)日：2012-05-03
申请号：US12914947
申请日：2010-10-28
申请人： Joel H. Wagner , Shankar S. Magge , Keith A. Santeler
发明人： Joel H. Wagner , Shankar S. Magge , Keith A. Santeler
IPC分类号： F02C6/08 , F04D29/28
CPC分类号： F02C6/08 , F02C3/08 , F04D29/284 , F04D29/286 , F04D29/4206 , F04D29/4246
摘要： An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.
摘要翻译：叶轮包括围绕轮毂形成的多个叶片，所述多个叶片中的每一个限定了前缘和后缘之间的偏移。

2. 发明授权

US08935926B2 Centrifugal compressor with bleed flow splitter for a gas turbine engine 有权
标题翻译：具有用于燃气涡轮发动机的排气分流器的离心式压缩机
公开(公告)号：US08935926B2
公开(公告)日：2015-01-20
申请号：US12914947
申请日：2010-10-28
申请人： Joel H. Wagner , Shankar S. Magge , Keith A. Santeler
发明人： Joel H. Wagner , Shankar S. Magge , Keith A. Santeler
IPC分类号： F02C6/04 , F02C6/08 , F04D29/28 , F04D29/42 , F02C3/08
CPC分类号： F02C6/08 , F02C3/08 , F04D29/284 , F04D29/286 , F04D29/4206 , F04D29/4246
摘要： An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.
摘要翻译：叶轮包括围绕轮毂形成的多个叶片，所述多个叶片中的每一个限定了前缘和后缘之间的偏移。

3. 发明申请

US20090148282A1 3D CONTOURED VANE ENDWALL FOR VARIABLE AREA TURBINE VANE ARRANGEMENT 有权
标题翻译：用于可变区域涡轮风扇装置的3D轮廓端板
公开(公告)号：US20090148282A1
公开(公告)日：2009-06-11
申请号：US11953478
申请日：2007-12-10
申请人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
发明人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
IPC分类号： F01D1/02
CPC分类号： F01D17/162 , F02C9/22
摘要： A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.
摘要翻译：燃气涡轮发动机的涡轮机部分包括具有基本上平坦的表面的弧形叶片平台段，旋转涡轮叶片可绕其旋转。

4. 发明授权

US08105019B2 3D contoured vane endwall for variable area turbine vane arrangement 有权
标题翻译：用于可变区域涡轮叶片布置的3D轮廓叶片端壁
公开(公告)号：US08105019B2
公开(公告)日：2012-01-31
申请号：US11953478
申请日：2007-12-10
申请人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
发明人： Michael G. McCaffrey , Eric A. Hudson , James D. Hill , Shankar S. Magge , Joel H. Wagner
IPC分类号： F01D9/02
CPC分类号： F01D17/162 , F02C9/22
摘要： A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.
摘要翻译：燃气涡轮发动机的涡轮机部分包括具有基本上平坦的表面的弧形叶片平台段，旋转涡轮叶片可绕其旋转。

5. 发明申请

US20090142181A1 Gas Turbine Engine Systems Involving Mechanically Alterable Vane Throat Areas 有权
标题翻译：燃气轮机发动机系统涉及机械可变叶片喉区
公开(公告)号：US20090142181A1
公开(公告)日：2009-06-04
申请号：US11947160
申请日：2007-11-29
申请人： Michael G. McCaffrey , Shankar S. Magge , Joel H. Wagner , Daniel R. Sabatino , Joseph Clayton Burge
发明人： Michael G. McCaffrey , Shankar S. Magge , Joel H. Wagner , Daniel R. Sabatino , Joseph Clayton Burge
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D9/02 , F05D2270/17
摘要： Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture.
摘要翻译：提供涉及可机械地改变的叶片喉部区域的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性叶片包括：前缘; 后缘吸引侧表面，其在前缘和后缘之间延伸; 空腔，其具有位于所述吸力侧表面中的孔; 以及位于腔体内且可在其中移动的筒体，使得筒体的移动改变了筒体穿过该孔突出的程度。

6. 发明授权

US09382807B2 Non-axisymmetric rim cavity features to improve sealing efficiencies 有权
标题翻译：非轴对称轮辋腔特征，以提高密封效率
公开(公告)号：US09382807B2
公开(公告)日：2016-07-05
申请号：US13466254
申请日：2012-05-08
申请人： Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
发明人： Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
IPC分类号： F01D11/02 , F01D11/00 , F01D5/08
CPC分类号： F01D11/001 , F01D5/081 , F01D11/02 , F05D2250/73 , F05D2260/97
摘要： Turbomachinery, such as a gas turbine engine, has parts with opposed first and second surfaces and with a cavity between the surfaces and with the first surface moving relative to the second surface. The turbomachinery further has at least one feature for creating pressure variations incorporated into the first and second surfaces.
摘要翻译：涡轮机械，例如燃气涡轮发动机，具有相对的第一和第二表面的部件，并且在表面之间具有空腔，并且第一表面相对于第二表面移动。涡轮机械还具有用于产生并入第一和第二表面的压力变化的至少一个特征。

7. 发明授权

US06932572B2 Film cooled article with improved temperature tolerance 有权
标题翻译：具有改善耐温性的薄膜冷却制品
公开(公告)号：US06932572B2
公开(公告)日：2005-08-23
申请号：US10375337
申请日：2003-02-27
申请人： Atul Kohli , Joel H. Wagner , Andrew S. Aggarwala
发明人： Atul Kohli , Joel H. Wagner , Andrew S. Aggarwala
IPC分类号： F01D5/14 , F01D5/18 , F01D9/02
CPC分类号： F01D5/141 , F01D5/186
摘要： The invention is a film cooled article such as a turbine engine blade or vane, having a wall with a hot surface 26 to be film cooled. The hot surface 26 includes a depression 48 featuring a descending flank 52 and an ascending flank 54. Coolant holes 60, which penetrate through the wall, have discharge openings residing on the ascending flank 54. During operation, the depression locally over-accelerates a primary fluid stream F flowing over the ascending flank while coolant jets 70 concurrently issue from the discharge openings. The local over-acceleration of the primary fluid deflects the jets onto the hot surface and spatially constrains the jets thus encouraging them to spread out laterally and coalesce into a laterally continuous, protective coolant film. In one embodiment, the depression 48 is a trough 50. In another embodiment, the depression is a dimple 72.
摘要翻译：本发明是一种薄膜冷却制品，例如涡轮发动机叶片或叶片，其具有壁，其具有待冷却的热表面26。热表面26包括具有下降侧面52和上升侧面54的凹部48。穿过壁的冷却剂孔60具有位于上升侧面54上的排出口。在操作期间，凹陷局部过度加速初级流体流F在上升侧面上流动，而冷却剂喷嘴70同时从排出口发出。主流体的局部过加速度将射流偏转到热表面上并在空间上限制射流，从而鼓励它们横向扩展并且聚结成横向连续的保护性冷却剂膜。在一个实施例中，凹陷部48是槽50.在另一个实施例中，凹陷部是凹坑72。

8. 发明授权

US08511978B2 Airfoil array with an endwall depression and components of the array 有权
标题翻译：翼型阵列具有端壁凹陷和阵列的部件
公开(公告)号：US08511978B2
公开(公告)日：2013-08-20
申请号：US11415898
申请日：2006-05-02
申请人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
发明人： Eunice Allen-Bradley , Eric A. Grover , Thomas J. Praisner , Joel H. Wagner
IPC分类号： F01D1/04 , F01D9/02
CPC分类号： F01D5/145 , F01D5/143 , F01D9/041 , F05D2240/80 , F05D2250/291 , F05D2250/60
摘要： An airfoil array includes a laterally extending endwall 56 with a series of airfoils such as 28 or 38 projecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages 74. The endwall has a trough 100 toward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.
摘要翻译：翼型阵列包括横向延伸的端壁56，其具有从端壁突出的一系列诸如28或38的翼型件。翼型件与端壁协作以限定一系列流体流动通道74.端壁具有朝向通道的压力侧的槽100和朝向通道的吸入侧的更加升高的型面，用于减少二次流动损失。

9. 发明授权

US08240121B2 Retrofit dirt separator for gas turbine engine 有权
标题翻译：燃气轮机发动机改装污垢分离器
公开(公告)号：US08240121B2
公开(公告)日：2012-08-14
申请号：US11942962
申请日：2007-11-20
申请人： Robert L. Hazzard , Joel H. Wagner , Edward M. Henrahan , Ryan Shepard Levy , Takao Fukuda , Eric A. Grover , Paul Smith
发明人： Robert L. Hazzard , Joel H. Wagner , Edward M. Henrahan , Ryan Shepard Levy , Takao Fukuda , Eric A. Grover , Paul Smith
IPC分类号： F02G3/00
CPC分类号： F04D29/701 , F01D25/00 , F01D25/32 , F02C7/00 , F05D2230/80 , F05D2240/11 , F05D2260/607 , Y02T50/67 , Y02T50/675 , Y10T29/49236
摘要： A dirt separator may be retrofit into existing gas turbine engines since it is formed of circumferentially separate pieces which may be assembled together in the gas turbine engine.
摘要翻译：污垢分离器可以改装成现有的燃气涡轮发动机，因为它由周向分开的片形成，其可以组装在燃气涡轮发动机中。

10. 发明申请

US20110203286A1 3D NON-AXISYMMETRIC COMBUSTOR LINER 有权
标题翻译： 3D非轴对称配线架
公开(公告)号：US20110203286A1
公开(公告)日：2011-08-25
申请号：US12709951
申请日：2010-02-22
申请人： Joel H. Wagner , Paul M. Lutjen
发明人： Joel H. Wagner , Paul M. Lutjen
IPC分类号： F23R3/42
CPC分类号： F23R3/16 , F23C3/00 , F23R3/002 , F23R3/50
摘要： A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.
摘要翻译：具有输入端和输出端的燃烧器衬套包括环形内壁和环形外壁。内壁和外壁中的至少一个是三维轮廓。内壁和外壁形成燃烧室，其轮廓在室内形成交替的膨胀和收缩区域，使得燃烧气体在周向和轴向上流动。

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