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1. 发明授权

US07165937B2 Methods and apparatus for maintaining rotor assembly tip clearances 有权
标题翻译：保持转子总成尖端间隙的方法和装置
公开(公告)号：US07165937B2
公开(公告)日：2007-01-23
申请号：US11005870
申请日：2004-12-06
申请人： Zhifeng Dong , Michael J. Epstein , Glen William Royal , Robert J. Albers
发明人： Zhifeng Dong , Michael J. Epstein , Glen William Royal , Robert J. Albers
IPC分类号： F01D11/08 , F03B11/02
CPC分类号： F01D11/14 , F05D2250/18 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , Y10T29/49323
摘要： A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferentially around the rotor assembly such that a clearance is defined between an inner shroud surface of the casing assembly and the rotor blade tips, and coupling a clearance control system to the casing assembly to facilitate maintaining the clearance between the casing assembly and the rotor blade tips, wherein at least a portion of an external surface of the clearance control system is formed with a textured pattern that facilitates increasing the clearance control closure capability during engine operation.
摘要翻译：一种方法使得能够组装燃气涡轮发动机。该方法包括将包括多个周向间隔开的转子叶片的转子组件联接在一起，并且与压缩机流体连通，将壳体组件周向地围绕转子组件联接，使得间隙限定在转子组件的内护罩表面之间壳体组件和转子叶片尖端，并且将间隙控制系统耦合到壳体组件以便于保持壳体组件和转子叶片尖端之间的间隙，其中间隙控制系统的外表面的至少一部分形成有有助于增加发动机运行期间的间隙控制关闭能力的纹理图案。

2. 发明授权

US07249463B2 Aerodynamic fastener shield for turbomachine 有权
标题翻译：用于涡轮机的气动紧固件护罩
公开(公告)号：US07249463B2
公开(公告)日：2007-07-31
申请号：US10941213
申请日：2004-09-15
申请人： William C. Anderson , Jesse Senyo , Michael J. Epstein , Zhifeng Dong
发明人： William C. Anderson , Jesse Senyo , Michael J. Epstein , Zhifeng Dong
IPC分类号： F02C7/20 , F01D25/12
CPC分类号： F01D25/243 , F05D2250/27 , F05D2250/71 , F05D2260/231 , F05D2260/607 , F05D2260/97 , Y02T50/675
摘要： A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced fasteners. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts.
摘要翻译：一种用于燃气涡轮发动机内的流体流动路径中的紧固件屏蔽件，用于减少在多个周向间隔开的紧固件上的流体流动产生的流体阻力和加热。紧固件屏蔽件具有径向延伸的，面向下游的安装凸缘，多个周向间隔开的螺栓孔定位成接收相应的发动机安装螺栓，并将安装凸缘连接到涡轮发动机的元件。弯曲的面向上游的紧固件屏蔽盖与安装凸缘间隔开地定位，用于至少部分地覆盖和分离出与流体流动的螺栓的暴露的面向上游的部分，从而减少了阻力并随之而来的加热螺栓

3. 发明授权

US07094020B2 Swirl-enhanced aerodynamic fastener shield for turbomachine 有权
公开(公告)号：US07094020B2
公开(公告)日：2006-08-22
申请号：US10941214
申请日：2004-09-15
申请人： Zhifeng Dong , Michael J. Epstein , William C. Anderson , Jesse Senyo
发明人： Zhifeng Dong , Michael J. Epstein , William C. Anderson , Jesse Senyo
IPC分类号： F04D29/08
CPC分类号： F01D25/243 , F01D11/001 , F05B2260/301 , F05D2260/97
摘要： A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced bolts. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts. A plurality of closely spaced-apart, spirally-oriented channels are formed in the fastener shield cover for deflecting the fluid flow impinging on the fastener shield cover, thereby increasing the tangential velocity and lowering the relative temperature of the fluid flow.

4. 发明授权

US06185925B1 External cooling system for turbine frame 有权
标题翻译：涡轮机架外部冷却系统
公开(公告)号：US06185925B1
公开(公告)日：2001-02-13
申请号：US09249206
申请日：1999-02-12
申请人： Robert Proctor , Michael J. Epstein , Gordon G. Fraser , Scott E. Farley , Richard F. Koch , Robert W. Siebert
发明人： Robert Proctor , Michael J. Epstein , Gordon G. Fraser , Scott E. Farley , Richard F. Koch , Robert W. Siebert
IPC分类号： F02C300
CPC分类号： F01D11/24 , Y02T50/671
摘要： An apparatus for cooling a gas turbine engine annular rear turbine frame includes a first plenum box having an inlet for receiving cooling air and an annular first manifold tube in fluid communication with a first outlet of and extending in a first circumferential direction away from the plenum box. The first manifold tube is circumscribed radially outward of and around a centerline and has axially spaced apart first arcuate sections circumscribed about and perpendicular to the centerline. Each of the first arcuate sections of the first manifold tube has a corresponding portion of a first plurality of impingement cooling holes disposed through the first manifold tube and aimed generally radially inward. In one embodiment the impingement cooling holes are aimed towards a first circumference on the frame and A cooling air bleed is preferably connected to the plenum box with a selectable on and off control valve therebetween.
摘要翻译：用于冷却燃气涡轮发动机环形后涡轮机框架的装置包括具有用于接收冷却空气的入口的第一增压箱和与远离增压箱的第一周向方向的第一出口流通连通的环形第一歧管管。第一歧管管径向外围并且围绕中心线并且具有围绕中心线并且垂直于中心线的轴向间隔开的第一弧形部分。第一歧管管的每个第一弓形部分具有穿过第一歧管管设置并大致径向向内定向的第一多个冲击冷却孔的对应部分。在一个实施例中，冲击冷却孔朝向框架上的第一圆周瞄准，并且冷却空气渗出优选地连接到通风箱，其间具有可选择的开和关控制阀。

5. 发明授权

US5251447A Air fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的空气燃料混合器
公开(公告)号：US5251447A
公开(公告)日：1993-10-12
申请号：US955379
申请日：1992-10-01
申请人： Narendra D. Joshi , Edward E. Ekstedt , Michael J. Epstein
发明人： Narendra D. Joshi , Edward E. Ekstedt , Michael J. Epstein
IPC分类号： F23R3/14 , F23R3/32
CPC分类号： F23R3/14 , F05B2250/411
摘要： An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct having contained therein a fuel manifold in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct, hollow vanes in at least the outer swirler having passages therethrough in fluid communication with the fuel manifold to inject fuel into the mixing duct, and a hub separating the inner and outer swirlers to allow independent rotation thereof, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the swirler vanes so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited. Further, the air fuel mixer of the present invention may include passages in the wall of the mixing duct in fluid communication with the fuel manifold, a centerbody in the mixing duct having a passage therethrough to admit air into the downstream end of the mixing duct, and tubes extending from the passages in the swirler vanes and/or mixing duct wall to inject liquid fuel downstream of the swirlers.
摘要翻译：公开了一种具有混合管道的空气燃料混合器，围绕混合管道的上游端的护罩，其中容纳有与燃料供应和控制装置流体连通的燃料歧管，与燃料供应和控制装置相邻的一组内部和外部反向旋转旋流器至少外旋流器的中空叶片具有与燃料歧管流体连通的通道，以将燃料喷射到混合管道中;以及毂，分离内旋流器和外旋流器以允许其独立旋转，其中高来自压缩机的压力空气通过旋流器注入混合管道中以形成强烈的剪切区域，并且燃料从旋流器叶片注入到混合管道中，使得高压空气和燃料均匀地混合在其中，从而产生最小的当燃料/空气混合物从混合管道的下游端排出到燃烧器中并点燃时，形成污染物。此外，本发明的空气燃料混合器可以包括在与燃料歧管流体连通的混合管道的壁中的通道，混合管道中的中心体具有穿过其中的通道，以将空气吸入混合管道的下游端，以及从旋流器叶片和/或混合管道壁中的通道延伸的管以在旋流器下游注入液体燃料。

6. 发明授权

US5638682A Air fuel mixer for gas turbine combustor having slots at downstream end of mixing duct 失效
标题翻译：用于燃气轮机燃烧器的空气燃料混合器，其在混合管道的下游端具有槽
公开(公告)号：US5638682A
公开(公告)日：1997-06-17
申请号：US311639
申请日：1994-09-23
申请人： Narendra D. Joshi , Michael J. Epstein
发明人： Narendra D. Joshi , Michael J. Epstein
IPC分类号： F23D14/02 , F23M99/00 , F23R3/12 , F23R3/32
CPC分类号： F23D14/02 , F23M20/005 , F23R3/12 , F23C2900/07001 , F23D2209/10 , F23D2900/14021
摘要： An air fuel mixer is disclosed having a mixing duct, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct, and a hub separating the inner and outer swirlers to allow independent rotation thereof, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of the mixing duct into the combustor and ignited. In addition, the mixing duct of the mixer includes slots, preferably with flares associated therewith, at its downstream end which modify the shape and direction of mixing eddies emanating therefrom.
摘要翻译：公开了一种空气燃料混合器，其具有混合管道，邻近混合管道的上游端的一组内部和外部反向旋转旋流器，以及分离内部和外部旋流器以允许其独立旋转的毂，其中来自通过旋流器将压缩机注入到混合管道中以形成强烈的剪切区域，并且将燃料注入到混合管道中，使得高压空气和燃料均匀地混合在一起，以便当燃料/ 空气混合物从混合管道的下游端排出到燃烧器中并点燃。此外，混合器的混合管道在其下游端包括槽，优选地具有与其相关的耀斑，其改变了从其发出的混合涡流的形状和方向。

7. 发明授权

US5280705A Fuel injection system for scramjet engines 失效
标题翻译：喷气发动机燃油喷射系统
公开(公告)号：US5280705A
公开(公告)日：1994-01-25
申请号：US902260
申请日：1992-06-22
申请人： Michael J. Epstein , Paul H. Kutschenreuter, Jr.
发明人： Michael J. Epstein , Paul H. Kutschenreuter, Jr.
IPC分类号： F02K7/10 , F23R3/28 , F02K5/02
CPC分类号： F02K7/10 , F23R3/28
摘要： To promote fuel and air mixing combustor of a scramjet engine, fuel is injected as a succession of pulses into the airstream flowing through the combustor. By controlling the duty cycle and flow rate of the fuel pulses, increased fuel penetration and mixing efficiency are obtained with an overall fuel flow schedule comparable to steady state fuel injection. With sequential pulsed operation of plural, variously located fuel injectors in phased relation, the combustor remains in a transient state to enhance mixing and to spread out the combustor heat load.
摘要翻译：为了促进冲击式发动机的燃料和空气混合燃烧器，将燃料作为一连串的脉冲喷射到流过燃烧器的气流中。通过控制燃料脉冲的占空比和流量，可以获得与稳态燃料喷射相当的总体燃料流程图，从而提高燃料渗透和混合效率。通过多个相继的脉冲操作，各种定位的燃料喷射器处于相位关系，燃烧器保持在过渡状态，以增强混合并扩展燃烧器的热负荷。

8. 发明授权

US5613363A Air fuel mixer for gas turbine combustor 失效
标题翻译：用于燃气轮机燃烧器的空气燃料混合器
公开(公告)号：US5613363A
公开(公告)日：1997-03-25
申请号：US312374
申请日：1994-09-26
申请人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
发明人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
IPC分类号： F23C7/00 , F23D11/10 , F23R3/14 , F23R3/28 , F02C3/20
CPC分类号： F23C7/004 , F23D11/107 , F23R3/14 , F23R3/286 , Y02T50/675
摘要： An air fuel mixer having a mixing duct, a set of inner and outer counter-rotating swirlers at the upstream end of the mixing duct, and means for injecting fuel into the mixing duct is provided, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the fuel nozzle by means of a plurality of fuel spokes so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.
摘要翻译：一种空气燃料混合器，其具有混合管道，一组在混合管道的上游端的内部和外部反向旋转旋流器，以及用于将燃料喷射到混合管道中的装置，其中将来自压缩机的高压空气注入通过旋流器形成强烈剪切区域的混合管道和燃料通过多个燃料辐条从燃料喷嘴喷射到混合管道中，使得高压空气和燃料均匀地混合在一起，从而产生最小的当燃料/空气混合物从所述混合管道的下游端排出到燃烧器中并点燃时，形成污染物。

9. 发明授权

US5590529A Air fuel mixer for gas turbine combustor 失效
标题翻译：燃气轮机燃烧器用空气燃料混合器
公开(公告)号：US5590529A
公开(公告)日：1997-01-07
申请号：US312373
申请日：1994-09-26
申请人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
发明人： Narendra D. Joshi , Michael J. Epstein , Michael E. Ewbank
IPC分类号： F23D14/02 , F23R3/14 , F23R3/38 , F02C1/00
CPC分类号： F23R3/14 , F23D14/02 , F23R3/38 , Y02T50/675
摘要： An air fuel mixer having a mixing duct, a set of inner and outer counter-rotating swirlers at the upstream end of the mixing duct, and means for injecting fuel into the mixing duct is provided, wherein high pressure air from a compressor is injected into the mixing duct through the swirlers to form an intense shear region and fuel is injected into the mixing duct from the fuel nozzle by means of a plurality of non-linear fuel spokes so that the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of said mixing duct into the combustor and ignited.
摘要翻译：一种空气燃料混合器，其具有混合管道，一组在混合管道的上游端的内部和外部反向旋转旋流器，以及用于将燃料喷射到混合管道中的装置，其中将来自压缩机的高压空气注入通过旋流器形成强烈剪切区域的混合管道和燃料通过多个非线性燃料辐条从燃料喷嘴喷射到混合管道中，使得高压空气和燃料均匀地混合在一起，以便当燃料/空气混合物从所述混合管道的下游端排出到燃烧器中并点燃时，产生最小的污染物形成。

10. 发明授权

US5275000A Reducing thermal deposits in endothermic fuel reactors of propulsion systems 失效
标题翻译：减少推进系统吸热燃料反应堆中的热沉积物
公开(公告)号：US5275000A
公开(公告)日：1994-01-04
申请号：US931232
申请日：1992-08-17
申请人： George A. Coffinberry , Michael J. Epstein
发明人： George A. Coffinberry , Michael J. Epstein
IPC分类号： F02C7/22 , F02C3/28 , F02C7/16 , F02K9/64 , F02K9/68 , F23R3/40 , F02K9/44
CPC分类号： F23R3/40 , F02C3/28 , F02K9/64 , F02K9/68
摘要： An endothermic hydrocarbon fuel system to avoid thermally induced coking on the catalytic surfaces of an heat exchanger used as a reactor to dehydrogenate the fuel so that it provides a heat sink for the heat exchanger for cooling parts of high speed aircraft. The invention provides a means to feed an acceptable concentration of hydrogen to the reactor feed stock, wherein the feed stock is a portion of the endothermic hydrocarbon fuel that is catalytically dehydrogenated to provide a heat sink. The preferred embodiment uses Methylcyclohexane as a fuel and provides a return loop to recycle a fraction of the reaction products to provide the hydrogen to the reactor feedstock.
摘要翻译：一种吸热烃燃料系统，以避免在用作反应器的热交换器的催化剂表面上引起热致焦化，使燃料脱氢，从而为热交换器提供用于冷却高速飞机部件的散热器。本发明提供了将可接受浓度的氢气供应到反应器原料的方法，其中原料是催化脱氢以提供散热器的吸热烃燃料的一部分。优选的实施方案使用甲基环己烷作为燃料，并提供回流循环以循环一部分反应产物以向反应器原料提供氢气。

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