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1. 发明授权

US5755093A Forced air cooled gas turbine exhaust liner 失效
标题翻译：强制风冷式燃气轮机排气衬板
公开(公告)号：US5755093A
公开(公告)日：1998-05-26
申请号：US431542
申请日：1995-05-01
申请人： Mark E. Palusis , Carlos G. Figueroa , Daniel C. Friedberg , Debora F. Kehret
发明人： Mark E. Palusis , Carlos G. Figueroa , Daniel C. Friedberg , Debora F. Kehret
IPC分类号： F02K1/00 , F02K1/82 , F23R3/60
CPC分类号： F02K1/82 , F02K1/002 , F02K1/822 , F23R3/60 , Y02T50/67 , Y02T50/672 , Y02T50/675
摘要： The exhaust in a gas turbine engine is lined with stacks of hollow cooling blocks made of a composite material. Air is pumped into each stack and escapes into the exhaust flow from a slot between the blocks in each stack. In addition, the blocks contain passages so that some of the airflow escapes to a space between the stacks. The blocks are attached using special fasteners that does not create mechanical stresses on the composite material.
摘要翻译：燃气涡轮发动机中的排气衬有由复合材料制成的中空冷却块的堆叠。空气被泵送到每个堆叠中并从每个堆叠中的块之间的槽中逸出到排气流中。此外，这些块包含通道，使得一些气流逸出到堆叠之间的空间。使用不会在复合材料上产生机械应力的特殊紧固件来连接块体。

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

US07854124B2 Combined control for supplying cooling air and support air in a turbine engine nozzle 有权
标题翻译：用于在涡轮发动机喷嘴中供应冷却空气和支撑空气的组合控制
公开(公告)号：US07854124B2
公开(公告)日：2010-12-21
申请号：US11588884
申请日：2006-10-27
申请人： Andreas Sadil , Timothy A. Swandon , Roger O. Coffey , Debora F. Kehret
发明人： Andreas Sadil , Timothy A. Swandon , Roger O. Coffey , Debora F. Kehret
IPC分类号： F02K1/00 , B64C15/00
CPC分类号： F02K1/82 , F02K1/12
摘要： A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.
摘要翻译：对于在燃气涡轮发动机喷嘴的后部枢转以改变喷嘴的横截面积的翼片，设置有平衡压力控制。致动器驱动同步环以通过连杆移动襟翼。还向同步环提供加压空气供应，以帮助致动器抵抗来自喷嘴内的高压气体的力。当这些力低于正常值时，同步环后部的空气流减少或阻止。环与另一个环一起旋转以控制这种空气流，以及向喷嘴内部供应冷却空气。

5. 发明授权

US4993641A Gas turbine spherical exhaust nozzle 失效
标题翻译：燃气轮机球形排气喷嘴
公开(公告)号：US4993641A
公开(公告)日：1991-02-19
申请号：US427054
申请日：1989-10-26
申请人： Debora F. Kehret , Edward B. Thayer
发明人： Debora F. Kehret , Edward B. Thayer
IPC分类号： F02K1/00
CPC分类号： F02K1/008 , F05D2250/241
摘要： A spherical exhaust nozzle for a gas turbine engine having gimbal mounted convergent-divergent flaps in which cooling air for the flaps is ducted through the convergent flap pivots and the convergent flaps are actuated by actuators connected to the gimbal structure.
摘要翻译：一种用于燃气涡轮发动机的球形排气喷嘴，其具有万向节安装的会聚 - 发散翼片，其中用于翼片的冷却空气通过会聚翼片枢转并且会聚翼片由连接到万向节结构的致动器致动。

6. 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。

7. 发明申请

US20080098742A1 Combined control for supplying cooling air and support air in a turbine engine nozzle 有权
标题翻译：用于在涡轮发动机喷嘴中供应冷却空气和支撑空气的组合控制
公开(公告)号：US20080098742A1
公开(公告)日：2008-05-01
申请号：US11588884
申请日：2006-10-27
申请人： Andreas Sadil , Timothy A. Swanson , Roger O. Coffey , Debora F. Kehret
发明人： Andreas Sadil , Timothy A. Swanson , Roger O. Coffey , Debora F. Kehret
IPC分类号： F02K1/00
CPC分类号： F02K1/82 , F02K1/12
摘要： A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.
摘要翻译：对于在燃气涡轮发动机喷嘴的后部枢转以改变喷嘴的横截面积的翼片，设置有平衡压力控制。致动器驱动同步环以通过连杆移动襟翼。还向同步环提供加压空气供应，以帮助致动器抵抗来自喷嘴内的高压气体的力。当这些力低于正常值时，同步环后部的空气流减少或阻止。环与另一个环一起旋转以控制这种空气流，以及向喷嘴内部供应冷却空气。

8. 发明申请

US20080072604A1 Pressure balance control for gas turbine engine nozzle 审中-公开
标题翻译：燃气轮机发动机喷嘴压力平衡控制
公开(公告)号：US20080072604A1
公开(公告)日：2008-03-27
申请号：US11527188
申请日：2006-09-26
申请人： Timothy A. Swanson , Debora F. Kehret , Stefan M. Poth , Donald E. Grove
发明人： Timothy A. Swanson , Debora F. Kehret , Stefan M. Poth , Donald E. Grove
IPC分类号： F02K1/00
CPC分类号： F02K1/15 , F02K1/06 , F02K1/1223 , F05D2270/3015
摘要： A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked.
摘要翻译：对于在燃气涡轮发动机喷嘴的后部枢转以改变喷嘴的横截面积的翼片，设置有平衡压力控制。致动器驱动同步环以通过连杆移动襟翼。还向同步环提供加压空气供应，以帮助致动器抵抗来自喷嘴内的高压气体的力。当这些力低于正常值时，同步环后部的空气流减少或阻止。

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