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1. 发明授权

US07980812B2 Low pressure turbine rotor disk 有权
标题翻译：低压汽轮机转子盘
公开(公告)号：US07980812B2
公开(公告)日：2011-07-19
申请号：US11975674
申请日：2007-10-19
申请人： Ryan C. McMahon , Jack W. Wilson, Jr.
发明人： Ryan C. McMahon , Jack W. Wilson, Jr.
IPC分类号： F03B11/06 , F04D29/10
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： A low pressure turbine rotor disk for a small twin spool gas turbine engine in which the rotor disk includes a forward side cavity large enough to allow for the bearing assembly that rotatably supports the rotor disk to fit within the cavity in order to shorten the axial distance between the bearings that support the inner rotor shaft on which the turbine rotor disk is secured. Minimizing the bearings spacing allows for a high critical speed for the inner rotor shaft and therefore allows for the small twin spool gas turbine engine to operate at this small scale. The turbine rotor disk also includes a plurality of axial aligned cooling air holes to allow for cooling air from the bearings to flow out from the aft end of the rotor disk. The inner surface of the cavity is an annular surface that forms a seal with knife edges extending outward from the bearing support plate also located within the cavity. The rotor disk includes an annular groove facing outward and on the rear side of the disk to allow for a tool to be inserted for removing the rotor disk from the shaft. An axial central opening in the rotor disk allows for insertion of the shaft and is formed with a bearing race abutment surface on the forward side and a nut abutment surface of the aft side used to compress the rotor disk assembly on the inner rotor shaft.
摘要翻译：一种用于小双轴卷烟气发动机的低压涡轮转子盘，其中转子盘包括足够大的前侧腔，以允许可转动地支撑转子盘以装配在腔内的轴承组件，以缩短轴向距离在支撑涡轮转子盘固定在其上的内转子轴之间。最小化轴承间距允许内转子轴的高临界转速，从而允许小双轴卷烟机涡轮发动机以小规模运行。涡轮转子盘还包括多个轴向排列的冷却空气孔，以允许冷却来自轴承的空气从转子盘的后端流出。空腔的内表面是形成密封件的环形表面，刀片边缘也从也位于腔体内的轴承支撑板向外延伸。转子盘包括面向盘的外侧和后侧的环形槽，以允许插入工具以从转轴中移除转子盘。转子盘中的轴向中心开口允许轴插入，并且在前侧形成有轴承座抵接表面，并且在后侧形成用于压缩内转子轴上的转子盘组件的螺母邻接表面。

2. 发明申请

US20100284794A1 Low pressure turbine rotor disk 有权
标题翻译：低压涡轮转子盘
公开(公告)号：US20100284794A1
公开(公告)日：2010-11-11
申请号：US11975674
申请日：2007-10-19
申请人： Ryan C. McMahon , Jack W. Wilson, JR.
发明人： Ryan C. McMahon , Jack W. Wilson, JR.
IPC分类号： F01D11/00 , F01D1/24 , F01D5/08 , F01D5/02 , B23P15/04
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： A low pressure turbine rotor disk for a small twin spool gas turbine engine in which the rotor disk includes a forward side cavity large enough to allow for the bearing assembly that rotatably supports the rotor disk to fit within the cavity in order to shorten the axial distance between the bearings that support the inner rotor shaft on which the turbine rotor disk is secured. Minimizing the bearings spacing allows for a high critical speed for the inner rotor shaft and therefore allows for the small twin spool gas turbine engine to operate at this small scale. The turbine rotor disk also includes a plurality of axial aligned cooling air holes to allow for cooling air from the bearings to flow out from the aft end of the rotor disk. The inner surface of the cavity is an annular surface that forms a seal with knife edges extending outward from the bearing support plate also located within the cavity. The rotor disk includes an annular groove facing outward and on the rear side of the disk to allow for a tool to be inserted for removing the rotor disk from the shaft. An axial central opening in the rotor disk allows for insertion of the shaft and is formed with a bearing race abutment surface on the forward side and a nut abutment surface of the aft side used to compress the rotor disk assembly on the inner rotor shaft.
摘要翻译：一种用于小型双卷轴燃气涡轮发动机的低压涡轮转子盘，其中转子盘包括足够大的前侧腔，以允许可旋转地支撑转子盘以装配在腔内的轴承组件，以缩短轴向距离在支撑涡轮转子盘固定在其上的内转子轴之间。最小化轴承间距允许内转子轴的高临界转速，从而允许小双轴卷烟机涡轮发动机以小规模运行。涡轮转子盘还包括多个轴向排列的冷却空气孔，以允许冷却来自轴承的空气从转子盘的后端流出。空腔的内表面是形成密封件的环形表面，刀片边缘也从也位于腔体内的轴承支撑板向外延伸。转子盘包括面向盘的外侧和后侧的环形槽，以允许插入工具以将转子盘从轴上移除。转子盘中的轴向中心开口允许轴插入，并且在前侧形成有轴承座抵接表面，并且在后侧形成用于压缩内转子轴上的转子盘组件的螺母邻接表面。

3. 发明授权

US07665293B2 Low speed rotor shaft for a small twin spool gas turbine engine 有权
标题翻译：低速转子轴用于小型双卷轴燃气轮机
公开(公告)号：US07665293B2
公开(公告)日：2010-02-23
申请号：US11975671
申请日：2007-10-19
申请人： Jack W. Wilson, Jr. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
发明人： Jack W. Wilson, Jr. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
IPC分类号： F02C7/00 , F02K3/04
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： An inner rotor shaft for use in a small twin spool gas turbine engine, the inner rotor shaft having a hollow middle section formed of a smaller diameter hollow section on a compressor end and a larger diameter hollow section on the turbine end of the shaft. Solid shaft end extend from the hollow section to form a forward solid shaft end to secure the fan rotor disk and an aft solid shaft end to secure the turbine rotor disk. A parabolic shaped transition section joins the forward shaft end to the smaller diameter hollow section, and a conical shaped transition section joins the aft shaft end to the larger diameter hollow section. A conical shaped transition piece joins the two hollow sections together to form an inner rotor shaft that can fit within a minimal space between the compressor rotor disk and the annular combustor assembly of the engine. The conical shaped transition section on the turbine end is so shaped in order to fit within a space formed inside the high pressure turbine rotor disk of the engine in order to minimize the axial spacing between the bearings that support the inner rotor shaft and raise the critical speed of the shaft to a safe level above the operating speed of the engine in order to make such a small twin spool gas turbine engine possible.
摘要翻译：一种用于小型双轴卷烟气发动机的内转子轴，内转子轴具有由压缩机端部的较小直径的中空部分形成的空心中部，在轴的涡轮机端部具有较大直径的中空部分。实心轴端从中空部分延伸以形成一个向前的实心轴端，以固定风扇转子盘和一个实心轴端，以固定涡轮转子盘。抛物线形过渡部分将前轴端连接到较小直径的中空部分，并且锥形过渡部分将后轴端连接到较大直径的中空部分。锥形过渡件将两个中空部分连接在一起以形成内转子轴，其可以装配在压缩机转子盘和发动机的环形燃烧器组件之间的最小空间内。涡轮机端部上的锥形过渡部分被成形以便装配在形成在发动机的高压涡轮机转子盘内部的空间内，以便最小化支撑内转子轴的轴承之间的轴向间距并且提高关键轴的转速达到高于发动机运行速度的安全水平，以便使这种小型双阀芯燃气涡轮发动机成为可能。

4. 发明申请

US20090031732A1 Low speed rotor shaft for a small twin spool gas turbine engine 有权
标题翻译：低速转子轴用于小型双卷轴燃气轮机
公开(公告)号：US20090031732A1
公开(公告)日：2009-02-05
申请号：US11975671
申请日：2007-10-19
申请人： Jack W. Wilson, JR. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
发明人： Jack W. Wilson, JR. , Robert E. deLaneuville , Paul E. Orndoff , Ryan C. McMahon
IPC分类号： F02C3/10 , F16C3/02
CPC分类号： F01D5/026 , F16C3/023 , F16C2360/23 , Y02T50/671 , Y10S29/013 , Y10T29/4932
摘要： An inner rotor shaft for use in a small twin spool gas turbine engine, the inner rotor shaft having a hollow middle section formed of a smaller diameter hollow section on a compressor end and a larger diameter hollow section on the turbine end of the shaft. Solid shaft end extend from the hollow section to form a forward solid shaft end to secure the fan rotor disk and an aft solid shaft end to secure the turbine rotor disk. A parabolic shaped transition section joins the forward shaft end to the smaller diameter hollow section, and a conical shaped transition section joins the aft shaft end to the larger diameter hollow section. A conical shaped transition piece joins the two hollow sections together to form an inner rotor shaft that can fit within a minimal space between the compressor rotor disk and the annular combustor assembly of the engine. The conical shaped transition section on the turbine end is so shaped in order to fit within a space formed inside the high pressure turbine rotor disk of the engine in order to minimize the axial spacing between the bearings that support the inner rotor shaft and raise the critical speed of the shaft to a safe level above the operating speed of the engine in order to make such a small twin spool gas turbine engine possible.
摘要翻译：一种用于小型双轴卷烟气发动机的内转子轴，内转子轴具有由压缩机端部的较小直径的中空部分形成的空心中部，在轴的涡轮机端部具有较大直径的中空部分。实心轴端从中空部分延伸以形成一个向前的实心轴端，以固定风扇转子盘和一个实心轴端，以固定涡轮转子盘。抛物线形过渡部分将前轴端连接到较小直径的中空部分，并且锥形过渡部分将后轴端连接到较大直径的中空部分。锥形过渡件将两个中空部分连接在一起以形成内转子轴，其可以装配在压缩机转子盘和发动机的环形燃烧器组件之间的最小空间内。涡轮机端部上的锥形过渡部分被成形以便装配在形成在发动机的高压涡轮机转子盘内部的空间内，以便最小化支撑内转子轴的轴承之间的轴向间距并且提高关键轴的转速达到高于发动机运行速度的安全水平，以便使这种小型双阀芯燃气涡轮发动机成为可能。

5. 发明申请

US20140096537A1 Thin Metal Duct Damper 审中-公开
标题翻译：薄金属管道阻尼器
公开(公告)号：US20140096537A1
公开(公告)日：2014-04-10
申请号：US13544103
申请日：2012-07-09
申请人： Ryan C. McMahon
发明人： Ryan C. McMahon
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F16F7/08 , F16F15/022
摘要： A damper for damping vibration of a structural member of a gas turbine engine is disclosed. The damper may include a first metal mesh pad which abuts an outer circumferential surface of the structural member, and a garter spring which abuts the first metal mesh pad. Both the metal mesh pad and the garter spring may completely or partially encircle the structural member. Alternatively, the damper may include a damper cover which encloses the first metal mesh pad and the garter spring and which abuts the outer surface of the structural member. A second metal mesh pad may be inserted between the damper cover and the garter spring. A gas turbine engine which comprises such a damper is also disclosed.
摘要翻译：公开了一种用于阻尼燃气涡轮发动机结构件振动的阻尼器。阻尼器可以包括邻接结构构件的外圆周表面的第一金属网垫和与第一金属网垫邻接的纽扣弹簧。金属网垫和卡箍弹簧都可以完全或部分地环绕结构件。或者，阻尼器可以包括阻挡器盖，其封闭第一金属网垫和卡箍弹簧并且邻接结构构件的外表面。第二金属网垫可以插入在阻尼器盖和绞合弹簧之间。还公开了一种包括这种阻尼器的燃气涡轮发动机。

6. 发明授权

US09194251B2 Duct damper 有权
标题翻译：管道阻尼器
公开(公告)号：US09194251B2
公开(公告)日：2015-11-24
申请号：US13571625
申请日：2012-08-10
申请人： Ryan C. McMahon , Robert J. Sayers , Steven W. Burd
发明人： Ryan C. McMahon , Robert J. Sayers , Steven W. Burd
IPC分类号： F01D25/00 , F01D25/04
CPC分类号： F01D25/04
摘要： An example damper includes a damping member configured to damp a duct wall at an interface between a duct band and the duct wall.
摘要翻译：示例性阻尼器包括阻尼构件，其构造成在管道带和管道壁之间的界面处阻尼管道壁。

7. 发明授权

US08061209B1 Process and apparatus for sizing a damper ring 有权
标题翻译：调节环的尺寸的方法和装置
公开(公告)号：US08061209B1
公开(公告)日：2011-11-22
申请号：US12212011
申请日：2008-09-17
申请人： Ryan C. McMahon , Kenneth I. Nelson
发明人： Ryan C. McMahon , Kenneth I. Nelson
IPC分类号： G01M7/06
CPC分类号： G01M7/027
摘要： An apparatus and a process for determining the mass required for a wire damper ring to produce the maximum amount of damping in a certain rotary machine. The testing apparatus includes a test piece with an inward facing annular groove and a plurality of expander segments each with the top or outer half of a wire damper ring segment secured to and extending outward to fit within the annular groove. A mandrel with an outer surface having a slight slope is passed through a central opening of the expander segments and displaces the ring segments radially outward and into the annular groove at varying loads. The apparatus is set to vibrating and a piece of the test piece is observed for vibrations. The load applied to the damper ring segments is varied until the vibration is at a minimum. The applied load can now be correlated with the mass required for the damper ring to produce similar damping capability.
摘要翻译：一种用于确定线阻尼器环所需的质量以在特定旋转机器中产生最大阻尼量的装置和方法。测试装置包括具有向内的环形槽的测试件和多个膨胀器段，每个膨胀器段具有固定到外部并向外延伸以配合在环形槽内的钢丝阻尼环环段的顶部或外部半部。具有轻微斜率的外表面的心轴通过膨胀器段的中心开口，并以可变的载荷将环段径向向外移动并进入环形槽。该设备被设置为振动，并且观察到一片测试件用于振动。施加到阻尼器环段的载荷是变化的，直到振动最小。施加的载荷现在可以与阻尼环所需的质量相关联，以产生类似的阻尼能力。

8. 发明申请

US20140099182A1 DUCT DAMPER 有权
标题翻译： DUCT阻尼器
公开(公告)号：US20140099182A1
公开(公告)日：2014-04-10
申请号：US13571625
申请日：2012-08-10
申请人： Ryan C. McMahon , Robert J. Sayers , Steven W. Burd
发明人： Ryan C. McMahon , Robert J. Sayers , Steven W. Burd
IPC分类号： F01D25/04
CPC分类号： F01D25/04
摘要： An example damper includes a damping member configured to damp a duct wall at an interface between a duct band and the duct wall
摘要翻译：示例性阻尼器包括阻尼构件，其构造成在管道带和管道壁之间的界面处阻尼管道壁

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