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1. 发明授权

US07631481B2 Cooled duct for gas turbine engine 有权
标题翻译：燃气轮机发动机冷却管道
公开(公告)号：US07631481B2
公开(公告)日：2009-12-15
申请号：US11000829
申请日：2004-12-01
申请人： Curtis C Cowan , Jorge I. Farah , Debora F. Kehret , Stanley Keysa , Jeffrey R. Lavin , Michael Murphy , Stephen A. Paul , Richard Scott
发明人： Curtis C Cowan , Jorge I. Farah , Debora F. Kehret , Stanley Keysa , Jeffrey R. Lavin , Michael Murphy , Stephen A. Paul , Richard Scott
IPC分类号： F02C7/08
CPC分类号： F02K1/827 , F02K1/004 , F02K1/82 , F02K1/822 , Y02T50/675
摘要： A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.
摘要翻译：提供了一种用于燃气涡轮发动机的冷却排气管。冷却的排气管道包括轴向中心线，圆周，环形空间和多个可径向扩张的带。环形空间设置在第一壁和第二壁之间，并且沿轴向中心线延伸。第一壁径向设置在第二壁的内侧。多个可径向扩张的带中的每一个在圆环内周向延伸。带彼此轴向间隔开。每个带包括附接到第一壁的第一部分，附接到第二壁的第二部分和连接到第一和第二部分的中间部分。带形成周向延伸的隔室，其阻止环形空间内的冷却空气的轴向移动。

2. 发明申请

US20090072044A1 Convergent Divergent Nozzle With Slot Cooled Nozzle Liner 有权
标题翻译：收敛发散喷嘴与槽冷却喷嘴衬里
公开(公告)号：US20090072044A1
公开(公告)日：2009-03-19
申请号：US11676595
申请日：2007-02-20
申请人： Debora F. Kehret , Jorge I. Farah
发明人： Debora F. Kehret , Jorge I. Farah
IPC分类号： B05B17/04 , B64D33/04 , F02K99/00
CPC分类号： F02K1/1223 , F02K1/822 , Y02T50/675
摘要： A nozzle system includes a multitude of circumferentially distributed convergent flaps and seals that circumscribe an engine centerline. A cooling liner body cooperates with a cooling liner panel attached to respective convergent flaps and convergent seals to define an annular cooling airflow passageway which is movable therewith. Each cooling liner panels includes an arcuate cooling liner leading edge with a multiple of openings to distribute cooling airflow over both the inner “cold-side” and outer “hot-side” surfaces thereof. Through this backside cooling, thermal gradients are controlled at the attachment interface between the arcuate cooling liner leading edge and the main cooling liner body.
摘要翻译：喷嘴系统包括大量周向分布的会聚翼片和密封件，其围绕发动机中心线。冷却衬套主体与连接到相应的会聚翼片和会聚密封件的冷却衬套板配合，以限定可随之移动的环形冷却气流通道。每个冷却衬板包括具有多个开口的弧形冷却衬套前缘，以在其“冷侧”和“外侧”表面之间分配冷却气流。通过这种背面冷却，在弧形冷却衬套前缘和主冷却衬套主体之间的附接界面处控制热梯度。

3. 发明授权

US07757477B2 Convergent divergent nozzle with slot cooled nozzle liner 有权
标题翻译：具有狭缝冷却喷嘴衬管的收敛发散喷嘴
公开(公告)号：US07757477B2
公开(公告)日：2010-07-20
申请号：US11676595
申请日：2007-02-20
申请人： Debora F. Kehret , Jorge I. Farah
发明人： Debora F. Kehret , Jorge I. Farah
IPC分类号： F02K99/00 , F02K1/00 , B05B1/24 , B63H11/10
CPC分类号： F02K1/1223 , F02K1/822 , Y02T50/675
摘要： A nozzle system includes a multitude of circumferentially distributed convergent flaps and seals that circumscribe an engine centerline. A cooling liner body cooperates with a cooling liner panel attached to respective convergent flaps and convergent seals to define an annular cooling airflow passageway which is movable therewith. Each cooling liner panels includes an arcuate cooling liner leading edge with a multiple of openings to distribute cooling airflow over both the inner “cold-side” and outer “hot-side” surfaces thereof. Through this backside cooling, thermal gradients are controlled at the attachment interface between the arcuate cooling liner leading edge and the main cooling liner body.
摘要翻译：喷嘴系统包括大量周向分布的会聚翼片和密封件，其围绕发动机中心线。冷却衬套主体与连接到相应的会聚翼片和会聚密封件的冷却衬套板配合，以限定可随之移动的环形冷却气流通道。每个冷却衬板包括具有多个开口的弧形冷却衬套前缘，以在其“冷侧”和“外侧”表面之间分配冷却气流。通过这种背面冷却，在弧形冷却衬套前缘和主冷却衬套主体之间的附接界面处控制热梯度。

4. 发明授权

US09932845B2 Impingement cooled nozzle liner 有权
公开(公告)号：US09932845B2
公开(公告)日：2018-04-03
申请号：US13173903
申请日：2011-06-30
申请人： Curtis C. Cowan , Jorge I. Farah
发明人： Curtis C. Cowan , Jorge I. Farah
IPC分类号： F02K1/82 , F01D11/00 , F02K1/12 , F02C7/28 , F16J15/08 , F02K1/00 , F16J15/02 , F01D5/18
CPC分类号： F01D11/005 , F01D5/18 , F02C7/28 , F02K1/006 , F02K1/12 , F02K1/1223 , F02K1/822 , F16J15/025 , F16J15/027 , F16J15/0893 , Y02T50/675
摘要： A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.

5. 发明申请

US20130001319A1 IMPINGEMENT COOLED NOZZLE LINER 有权
标题翻译： IMPINGEMENT冷却喷嘴线
公开(公告)号：US20130001319A1
公开(公告)日：2013-01-03
申请号：US13173903
申请日：2011-06-30
申请人： Curtis C. Cowan , Jorge I. Farah
发明人： Curtis C. Cowan , Jorge I. Farah
IPC分类号： B64D33/04
CPC分类号： F01D11/005 , F01D5/18 , F02C7/28 , F02K1/006 , F02K1/12 , F02K1/1223 , F02K1/822 , F16J15/025 , F16J15/027 , F16J15/0893 , Y02T50/675
摘要： A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.
摘要翻译：用于可旋转喷嘴的喷嘴衬套包括密封台面和用于与喷嘴一起移动的可旋转密封件。如果可旋转密封件处于第一位置，密封件具有用于分配冷却空气的第一扩散孔和用于在可旋转密封件处于第一位置并且如果处于第二位置时分配冷却空气的第二扩散孔。

6. 发明申请

US20140102110A1 MID-TURBINE FRAME WITH TENSIONED SPOKES 有权
标题翻译：中等涡轮机框架与张力调查
公开(公告)号：US20140102110A1
公开(公告)日：2014-04-17
申请号：US13548613
申请日：2012-07-13
申请人： Jorge I. Farah , Paul K. Sanchez , Andrew D. Burdick
发明人： Jorge I. Farah , Paul K. Sanchez , Andrew D. Burdick
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F01D25/162 , F01D25/28 , F02C7/06 , F05D2260/31 , F05D2260/941
摘要： A mid-turbine frame located in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine includes an outer frame case, an inner frame case, and at least a first spoke connecting the outer frame case to the inner frame case. The first spoke is tightened so as to be in tension during substantially all operating conditions of the gas turbine engine.
摘要翻译：位于高压涡轮机轴向后方的燃气涡轮发动机的中涡轮机框架和低压涡轮机的前部包括外框架壳体，内框架壳体和至少第一轮辐，其将外框架壳体连接到内框框。在燃气轮机的基本上所有的操作条件下，第一轮辐被拧紧以致处于紧张状态。

7. 发明申请

US20140056704A1 TURBINE ENGINE SUPPORT ASSEMBLY INCLUDING SELF ANTI-ROTATING BUSHING 有权
标题翻译：涡轮发动机支撑组件，其中包括自动旋转轴
公开(公告)号：US20140056704A1
公开(公告)日：2014-02-27
申请号：US13592391
申请日：2012-08-23
申请人： Meggan Harris , Jorge I. Farah , Christopher Treat , Timothy Dale
发明人： Meggan Harris , Jorge I. Farah , Christopher Treat , Timothy Dale
IPC分类号： F04D29/52 , B23P11/00 , F16B39/28
CPC分类号： F01D25/28 , F01D25/162 , F16B9/023 , Y10T29/49323
摘要： A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.
摘要翻译：涡轮发动机包括多个层架支架。每个层架支撑件通过多个紧固件和至少一个自反向旋转衬套部件连接到涡轮发动机的内框架壳体。

8. 发明申请

US20140013770A1 VANE INSERTABLE TIE RODS WITH KEYED CONNECTIONS 有权
公开(公告)号：US20140013770A1
公开(公告)日：2014-01-16
申请号：US13548581
申请日：2012-07-13
申请人： Jorge I. Farah , Paul K. Sanchez
发明人： Jorge I. Farah , Paul K. Sanchez
IPC分类号： F02C7/20 , B21K3/00
CPC分类号： F01D25/16 , F01D9/065 , F02C7/20 , F05D2260/31 , Y10T29/49231
摘要： A gas turbine engine includes a combustor, a first turbine section in fluid communication with the combustor, a second turbine section in fluid communication with the first turbine section, and a mid-turbine frame located axially between the first turbine section and the second turbine section. The mid-turbine frame includes a first frame case, a second frame case, a vane positioned between the first frame case and the second frame case, and a spoke extending through the vane and connecting the first frame case to the second frame case. The spoke includes a tie rod having a first end connected to the first frame case at a keyed connection.
摘要翻译：燃气涡轮发动机包括燃烧器，与燃烧器流体连通的第一涡轮机部分，与第一涡轮机部分流体连通的第二涡轮机部分和轴向位于第一涡轮机部分和第二涡轮部分之间的中间涡轮机机架。中间涡轮机框架包括第一框架壳体，第二框架壳体，位于第一框架壳体和第二框架壳体之间的叶片以及延伸穿过叶片并且将第一框架框架连接到第二框架壳体的轮辐。辐条包括一个拉杆，该连杆具有一个连接在第一框架壳体上的第一端。

9. 发明申请

US20130224010A1 TURBINE FRAME FAIRING FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的涡轮机框架
公开(公告)号：US20130224010A1
公开(公告)日：2013-08-29
申请号：US13403407
申请日：2012-02-23
申请人： Jorge I. Farah , Theodore W. Kapustka , Jonathan P. Burt , Jonathan J. Jakiel , Dana P. Stewart
发明人： Jorge I. Farah , Theodore W. Kapustka , Jonathan P. Burt , Jonathan J. Jakiel , Dana P. Stewart
IPC分类号： F01D25/24 , B23K31/02 , F01D1/04
CPC分类号： F01D25/162 , B23K1/0018 , B23K2101/001 , F01D9/04 , F01D9/044 , F01D9/065 , F01D25/246 , F05D2230/237
摘要： A static structure of a gas turbine engine includes a multiple of airfoil segments and at least one structural reinforcement ring mounted to the multiple of airfoil segments.
摘要翻译：燃气涡轮发动机的静态结构包括多个翼型段和安装到多个翼型段的至少一个结构加强环。

10. 发明授权

US09482115B2 Turbine engine support assembly including self anti-rotating bushing 有权
标题翻译：涡轮发动机支撑组件包括自我防旋转轴套
公开(公告)号：US09482115B2
公开(公告)日：2016-11-01
申请号：US13592391
申请日：2012-08-23
申请人： Meggan Harris , Jorge I. Farah , Christopher Treat , Timothy Dale
发明人： Meggan Harris , Jorge I. Farah , Christopher Treat , Timothy Dale
IPC分类号： F01D25/28 , F01D25/16 , F16B9/02
CPC分类号： F01D25/28 , F01D25/162 , F16B9/023 , Y10T29/49323
摘要： A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.
摘要翻译：涡轮发动机包括多个层架支架。每个层架支撑件通过多个紧固件和至少一个自反向旋转衬套部件连接到涡轮发动机的内框架壳体。

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