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1. 发明授权

US09394799B1 Air riding seal for a turbine 有权
标题翻译：涡轮机用空气密封
公开(公告)号：US09394799B1
公开(公告)日：2016-07-19
申请号：US14795095
申请日：2015-07-09
申请人： Jacob A Mills , Wesley D Brown , Thomas D Sexton , Russell B Jones
发明人： Jacob A Mills , Wesley D Brown , Thomas D Sexton , Russell B Jones
IPC分类号： F16J15/34 , F01D11/02
CPC分类号： F01D11/025 , F01D11/003 , F16J15/34 , F16J15/3448
摘要： An air riding seal between a rotor and a stator in a turbine of a gas turbine engine, where an annular piston is movable in an axial direction within a housing that extends from the stator, and a bellows is secured to the annular piston to form a flexible air passageway from a compressed air inlet through the annular piston and into a cushion cavity that forms an air riding seal between the annular piston and the rotor sealing surface. In another embodiment, a flexible seal secured to and extending from the annular piston forms a sealing surface between the annular piston chamber and the annular piston to provide a seal and allow for axial movement.
摘要翻译：在燃气涡轮发动机的涡轮机中的转子和定子之间的空气骑行密封件，其中环形活塞在从定子延伸的壳体内的轴向方向上可移动，并且波纹管固定到环形活塞以形成柔性空气通道从压缩空气入口通过环形活塞并进入缓冲腔，其在环形活塞和转子密封表面之间形成空气密封。在另一个实施例中，固定到环形活塞并从环形活塞延伸的柔性密封件在环形活塞室和环形活塞之间形成密封表面，以提供密封并允许轴向移动。

2. 发明授权

US09771821B1 Turbine interstage seal with self-balancing capability 有权
公开(公告)号：US09771821B1
公开(公告)日：2017-09-26
申请号：US14739536
申请日：2015-06-15
申请人： Jacob A Mills , Russell B Jones , Thomas D Sexton
发明人： Jacob A Mills , Russell B Jones , Thomas D Sexton
IPC分类号： F01D11/02 , F01D1/02
CPC分类号： F01D11/025 , F01D11/04 , F05D2240/511 , F05D2300/507 , F16J15/441 , F16J15/445 , F16J15/453
摘要： An interstage seal for a turbine of a gas turbine engine, the interstage seal having a seal carrier with an axial extending seal tooth movable with a stator of the engine, and a rotor with a seal surface that forms the interstage seal with the seal tooth, where a magnetic force produced by two magnets and a gas force produced by a gas pressure acting on the seal carrier forms a balancing force to maintain a close clearance of the seal without the seal tooth contacting the rotor seal surfaces during engine operation. In other embodiments, two pairs of magnets produce first and second magnetic forces that balance the seal in the engine.

3. 发明授权

US09732621B1 Air riding seal with purge cavity 有权
公开(公告)号：US09732621B1
公开(公告)日：2017-08-15
申请号：US14548492
申请日：2014-11-20
申请人： Thomas D Sexton , Jacob A Mills
发明人： Thomas D Sexton , Jacob A Mills
IPC分类号： F01D11/00 , F01D11/02 , F01D11/10
CPC分类号： F01D11/025 , F01D11/003 , F01D11/02 , F01D11/04
摘要： An air riding seal for a turbine in a gas turbine engine, where an annular piston is axial moveable within an annular piston chamber formed in a stator of the turbine and forms a seal with a surface on the rotor using pressurized air that forms a cushion in a pocket of the annular piston. A purge cavity is formed on the annular piston and is connected to a purge hole that extends through the annular piston to a lower pressure region around the annular piston or through the rotor to an opposite side. The annular piston is sealed also with inner and outer seals that can be a labyrinth seal to form an additional seal than the cushion of air in the pocket to prevent the face of the air riding seal from overheating.

4. 发明授权

US08407981B1 Johnson Sexton cycle rocket engine 有权
标题翻译：约翰逊·塞克斯循环火箭发动机
公开(公告)号：US08407981B1
公开(公告)日：2013-04-02
申请号：US12700937
申请日：2010-02-05
申请人： Gabriel L Johnson , Thomas D Sexton
发明人： Gabriel L Johnson , Thomas D Sexton
IPC分类号： F02K9/46
CPC分类号： F02K9/46
摘要： An expander cycle rocket engine includes secondary turbopump to further pressurize a gaseous fuel discharged from a primary turbine prior to entering the combustion chamber. The secondary turbopump is driven by fuel bled off from the primary fuel pump. A gaseous fuel that is heated from passing around the nozzle that is passed through the primary turbine to drive the primary fuel and oxidizer pumps is then passed through the secondary turbine to drive the secondary fuel compressor. With the secondary turbopump used in the Johnson-Sexton cycle engine, a thrust produced by the expander cycle rocket engine is greater than those obtained by prior art expander cycle rocket engines due to the square-cube rule.
摘要翻译：膨胀循环火箭发动机包括二次涡轮泵，以在进入燃烧室之前进一步加压从主涡轮排出的气体燃料。二次涡轮泵由从主燃料泵排出的燃料驱动。然后，通过喷嘴周围的通过主涡轮以驱动主燃料和氧化剂泵的气态燃料通过次级涡轮以驱动次级燃料压缩机。在Johnson-Sexton循环发动机中使用的次级涡轮泵，由于平方立方体规则，由膨胀机循环火箭发动机产生的推力大于现有技术的膨胀机循环火箭发动机获得的推力。

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