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1. 发明授权

US06269647B1 Rotor system 有权
标题翻译：转子系统
公开(公告)号：US06269647B1
公开(公告)日：2001-08-07
申请号：US09522873
申请日：2000-03-10
申请人： Robert S. Thompson, Jr. , Gregg G. Williams
发明人： Robert S. Thompson, Jr. , Gregg G. Williams
IPC分类号： F02C100
CPC分类号： F02K9/52 , F02K9/48 , F02K9/62 , F02K9/64 , F02K9/66 , F02K9/72 , F05D2240/40
摘要： A rotor system for a rocket engine comprises a first hollow shaft portion and a surrounding annular duct. The interior of the first hollow shaft portion is adapted to receive a first propellant component, and is in fluid communication with a first rotary orifice. The annular duct is adapted to receive a second propellant component, and is in fluid communication with a second rotary orifice located proximate to the first rotary orifice. The rotor system further comprises a third rotary orifice operatively connected to second hollow shaft portion and in fluid communication with the interior of the first hollow shaft portion for discharging a second portion of the first propellant component at second location. The rotary orifices are operatively connected to respective rotary pressure traps that isolate the pressure at the respective rotary orifices from the respective inlet pressures of the respective propellant components.
摘要翻译：用于火箭发动机的转子系统包括第一空心轴部分和周围的环形管道。第一空心轴部分的内部适于接收第一推进剂部件，并且与第一旋转孔流体连通。环形管道适于接收第二推进剂部件，并且与位于第一旋转孔口附近的第二旋转孔流体连通。转子系统还包括可操作地连接到第二空心轴部分并与第一空心轴部分的内部流体连通的第三旋转孔口，用于在第二位置排放第一推进剂部件的第二部分。旋转孔可操作地连接到相应的旋转压力阱，其将相应旋转孔处的压力与相应的推进剂组分的相应入口压力隔离。

2. 发明授权

US06205770B1 Rocket engine 有权
标题翻译：火箭发动机
公开(公告)号：US06205770B1
公开(公告)日：2001-03-27
申请号：US09522871
申请日：2000-03-10
申请人： Gregg G. Williams , Robert S. Thompson, Jr. , Richard D. Stephens , Dean S. Musgrave , John F. Jones , Guido D. Defever
发明人： Gregg G. Williams , Robert S. Thompson, Jr. , Richard D. Stephens , Dean S. Musgrave , John F. Jones , Guido D. Defever
IPC分类号： F02K948
CPC分类号： F02K9/52 , F02K9/48 , F02K9/62 , F02K9/64 , F02K9/66 , F02K9/72 , F05D2240/40
摘要： A rocket engine comprises first and second rotary injectors for injecting respective fuel and oxidizer propellant components into a first combustion chamber, and the effluent therefrom drives a turbine that rotates the rotary injectors. The mixture within the first combustion chamber is preferably fuel-rich so as to reduce the associated combustion temperature, and the fuel-rich effluent mixes in a second combustion chamber with additional oxidizer injected by a third rotary injector so as to generate a high temperature effluent suitable for propulsion. The rotary injectors are adapted so as to isolate the low pressure propellant supply from the relatively high pressures in the respective combustion chambers.
摘要翻译：火箭发动机包括用于将相应的燃料和氧化剂推进剂组分喷射到第一燃烧室中的第一和第二旋转喷射器，并且其流出物驱动旋转旋转喷射器的涡轮机。第一燃烧室内的混合物优选为富燃料，以便降低相关的燃烧温度，并且富含燃料的流出物在第二燃烧室中与另外的由第三旋转喷射器注入的氧化剂混合，从而产生高温流出物适合推进。旋转喷射器适于将低压推进剂供应与相应燃烧室中的较高压力隔离。

3. 发明授权

US5485717A Multi-spool by-pass turbofan engine 失效
标题翻译：多阀芯旁通涡扇发动机
公开(公告)号：US5485717A
公开(公告)日：1996-01-23
申请号：US267616
申请日：1994-06-29
申请人： Gregg G. Williams
发明人： Gregg G. Williams
IPC分类号： F02K3/06 , F02C9/18 , F02K3/075 , F02K3/02
CPC分类号： F02C9/18 , F05D2270/044 , F05D2270/051
摘要： A multi-spool turbofan engine has a high pressure spool that operates at high idle RPM so as to power accessories and minimize acceleration time from idle to full rated RPM without producing high idle thrust which compromises the landing maneuver and ground operation.
摘要翻译：多阀芯涡轮风扇发动机具有高压阀芯，其在高空转RPM下运行，以便为附件提供动力，并将加速时间从空转到全额定RPM最小化，而不会产生高空转推力，从而损害着陆操作和地面操作。

4. 发明授权

US5568984A Fuel lubricated bearing 失效
标题翻译：燃油润滑轴承
公开(公告)号：US5568984A
公开(公告)日：1996-10-29
申请号：US523258
申请日：1995-09-05
申请人： Gregg G. Williams
发明人： Gregg G. Williams
IPC分类号： F01M9/04 , F16C33/66 , F16N15/00 , F02C7/06
CPC分类号： F16N15/00 , F01M9/04 , F16C33/6659 , F16C33/6692 , F05B2220/302 , F16C19/26 , F16N2210/02
摘要： A fuel lubricated anti-friction bearing comprises an inner race for an anti-friction bearing having a plurality of radially opening apertures communicating with a fuel supply, a rotatable outer race, and a plurality of anti-friction rollers between the inner and outer races, rotation of the outer race effecting rotation of the rollers and pumping of fuel radially outwardly through the apertures in the inner race of the rollers.
摘要翻译：燃料润滑的抗摩擦轴承包括用于抗摩擦轴承的内座圈，其具有与燃料供应，可旋转的外圈和多个在内圈和外圈之间的多个抗摩擦辊连通的多个径向开口孔，外圈的旋转影响辊的旋转并且通过辊的内圈中的孔径向向外泵送燃料。

5. 发明授权

US4919439A Balanced ring seal 失效
标题翻译：平衡环密封
公开(公告)号：US4919439A
公开(公告)日：1990-04-24
申请号：US106391
申请日：1987-10-09
申请人： Gregg G. Williams
发明人： Gregg G. Williams
IPC分类号： F01D11/00 , F01D11/02 , F16J15/34
CPC分类号： F01D11/025 , F01D11/00 , F16J15/34 , Y10S277/926
摘要： A ring seal comprises an annular seal segment that is fixed against rotation but is axially movable relative to a fixed seal segment. The axially movable seal segment has substantially equal oppositely facing exposed radial surfaces whereby fluid pressure acting against the rotatable segment is substantially balanced in opposite axial directions.
摘要翻译：环形密封件包括环形密封段，该环形密封段相对于固定的密封段可轴向移动固定。可轴向移动的密封段具有基本相同的相对面的暴露的径向表面，由此作用在可旋转段上的流体压力在相反的轴向方向上基本平衡。

6. 发明授权

US5161369A Aft fan gas turbine engine 失效
标题翻译： AFT风机涡轮发动机
公开(公告)号：US5161369A
公开(公告)日：1992-11-10
申请号：US646253
申请日：1991-01-28
申请人： Gregg G. Williams
发明人： Gregg G. Williams
IPC分类号： F02K3/062
CPC分类号： F02K3/062
摘要： An aft fan gas turbine engine comprises a coaxially related compressor, compressor turbine, fan turbine, and aft fan. An annular fuel tank is disposed about the compressor and an annular combustion chamber is disposed between the compressor and turbine.

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