公开(公告)号：WO2010008641A2

公开(公告)日：2010-01-21

申请号：PCT/US2009040129

申请日：2009-04-09

Applicant: WILLIAMS INT CO LLC ,  SORDYL JOHN ,  CONDEVAUX JAMEY J

Inventor： SORDYL JOHN ,  CONDEVAUX JAMEY J

IPC: F02C9/32

CPC classification number: F02C7/224 ,  F01D5/185 ,  F02C3/16 ,  F02C9/32 ,  F05D2260/205 ,  Y02T50/673 ,  Y02T50/676

Abstract: A rotary injector (95, 222) comprising one or more radially-extending arms (93) provides for injecting fuel (12, 12.1, 12.4) into a combustion chamber (16). The combustion chamber (16) receives air (14) from locations upstream and downstream of the rotary injector (95, 222), and the arms (93) of the rotary injector (95, 222) are adapted so that a pressure (P2) in the combustion chamber (16) upstream of the rotary injector (95, 222) is less than a pressure (Po") in a plenum (212) supplying air (14) to the combustion chamber (16) upstream of the rotary injector (95, 222).

Abstract translation: 包括一个或多个径向延伸的臂（93）的旋转喷射器（95,222）提供将燃料（12,12.1,12.4）喷射到燃烧室（16）中。 燃烧室（16）从旋转喷射器（95,222）的上游和下游的位置接收空气（14），旋转喷射器（95,222）的臂（93）适于使压力（P2） 在旋转喷射器（95,222）上游的燃烧室（16）中的压力小于在旋转喷射器上游向燃烧室（16）供应空气（14）的增压室（212）中的压力（Po“） 95,222）。

公开(公告)号：WO2010096817A3

公开(公告)日：2013-02-28

申请号：PCT/US2010025073

申请日：2010-02-23

Applicant: WILLIAMS INT CO LLC ,  CONDEVAUX JAMEY J ,  SIMPKINS LISA M ,  SORDYL JOHN

Inventor： CONDEVAUX JAMEY J ,  SIMPKINS LISA M ,  SORDYL JOHN

IPC: F23R3/06 ,  F23R3/16 ,  F23R3/34 ,  F23R3/38 ,  F23R3/50 ,  F23R3/52

CPC classification number: F23R3/16 ,  F23R3/06 ,  F23R3/343 ,  F23R3/38 ,  F23R3/50 ,  F23R3/52 ,  F23R2900/00015 ,  F23R2900/03041 ,  F23R2900/03282

Abstract: Fuel (110) and air (100) are injected in a first poloidal flow (130) in a first poloidal direction (132) within a first annular zone (54) of an annular combustor (52). A first combustion gas (140) from the at least partial combustion of the fuel (110) and air (100) is discharged into an annular transition zone (58) of the annular combustor (52) and transformed to a second combustion gas (150) therein within an at least partial second poloidal flow (142) followed by an at least partial third poloidal flow (152) in the annular transition zone (58), wherein the direction of the second poloidal flow (144) is opposite to that (132) of the first (130) and third (152) poloidal flows. The second combustion gas (150) is discharged into a second annular zone (56) of the annular combustor (52), and then transformed to a third combustion gas (160) therein before being discharged therefrom, responsive to which a back pressure (207) is generated in the annular combustor (52).

Abstract translation: 燃料（110）和空气（100）在环形燃烧器（52）的第一环形区域（54）内沿第一极向方向（132）注入第一极向流（130）。 来自燃料（110）和空气（100）的至少部分燃烧的第一燃烧气体（140）被排放到环形燃烧器（52）的环形过渡区域（58）中并转变成第二燃烧气体 ）在至少部分第二极向流（142）中，随后是环形过渡区（58）中的至少部分第三极向流（152），其中第二极向流（144）的方向与（ （130）和第三（152）极向流。 第二燃烧气体（150）被排放到环形燃烧器（52）的第二环形区域（56）中，然后在其中被排出之前转化为第三燃烧气体（160），响应于此，背压（207 ）在环形燃烧器（52）中产生。

公开(公告)号：WO2005028843A3

公开(公告)日：2005-05-12

申请号：PCT/US2004016020

申请日：2004-05-21

Applicant: WILLIAMS INT CO LLC ,  CONDEVEAUX JAMEY J ,  DEFEVER GUIDO J

Inventor： CONDEVEAUX JAMEY J ,  DEFEVER GUIDO J

IPC: F02C7/22 ,  F02K20060101 ,  F23D11/04

CPC classification number: F02C7/22 ,  F02K3/10 ,  F05D2240/36 ,  F23R3/38

Abstract: A radially-extending arm (48) rotates within a stream of first fluid (30) flowing thereacross. The arm (48) comprises a plurality of lands (52) located at different radial distances from the axis of rotation (50). A port (58) located on each land (52) is operatively coupled to a source of a second fluid (22), which is sprayed (74) from the rotating arm (48) into the stream of first fluid (30) flowing across the lands (52), and is thereby atomized. In other embodiments: 1) the arm (30) comprises a land (52) stepped into the trailing edge (56) thereof, and a port (58) for injecting the second fluid (22) is located on the land (52); 2) the land (52) comprises a groove (96) located between the port (58) and an associated riser surface (88) stepped into the trailing edge (56); and 3) the arm (48) comprises a port (58) in the trailing edge (56) thereof from which the second fluid (22) is injected, and a groove (96) is located on the trailing edge (56, 98) in a radially increasing direction from the port (58).

Abstract translation: 径向延伸臂（48）在流过其中的第一流体（30）的流内旋转。 臂（48）包括位于离旋转轴线（50）不同径向距离处的多个平台（52）。 位于每个台面（52）上的端口（58）可操作地联接到第二流体（22）的源，该第二流体从旋转臂（48）喷射（74）进入流过的第一流体 （52），并由此雾化。 在其他实施例中：1）所述臂（30）包括台阶（52），所述台阶（52）步进其后缘（56），并且用于注入所述第二流体（22）的端口（58）位于所述台面（52）上; 2）所述台肩52包括位于所述端口58和相关联的提升器表面88之间的凹槽96，所述提升器表面88步进所述后缘56中; 和3）所述臂（48）包括在其后缘（56）中的第二流体（22）从其注入的端口（58），并且在所述后缘（56,98）上设置有凹槽（96） 在从端口（58）沿径向增加的方向上。

公开(公告)号：WO0057048A3

公开(公告)日：2001-01-18

申请号：PCT/US0006393

申请日：2000-03-10

Applicant: WILLIAMS INT CO LLC

Inventor： STEPHENS RICHARD D ,  THOMPSON ROBERT S JR ,  DEFEVER GUIDO J ,  JONES JOHN F ,  MUSGRAVE DEAN S ,  WILLIAMS GREGG G

IPC: F02K9/50 ,  F02K9/48 ,  F02K9/52 ,  F02K9/56 ,  F02K9/60 ,  F02K9/62 ,  F02K9/64 ,  F02K9/66 ,  F02K9/72 ,  F02K9/97 ,  F02K11/00 ,  F23R3/00

CPC classification number: F02K9/52 ,  F02K9/48 ,  F02K9/62 ,  F02K9/64 ,  F02K9/66 ,  F02K9/72 ,  F05D2240/40

Abstract: A rocket engine (10) comprises first (76) and second (142) rotary injectors for injecting respective fuel (20) and oxidizer (18) propellant components into a first combustion chamber (34), and the effluent (38) therefrom drives a turbine (40) that rotates the rotary injectors (76, 142). The mixture within the first combustion chamber (34) is preferably fuel-rich so as to reduce the associated combustion temperature, and the fuel-rich effluent mixes in a second combustion chamber (36) with additional oxidizer injected by a third rotary injector (182) so as to generate a high temperature effluent (214) suitable for propulsion. The rotary injectors (76, 142, 182) are adapted with associated rotary pressure traps (86, 146, 174) so as to isolate the low pressure propellant supply (22', 24') from the relatively high pressures in the respective combustion chambers (34, 36). A portion of the fuel-rich effluent from the first combustion chamber (34) is directed through an annular passage (198, 204) surrounding the combustion chambers (34, 36) to provide effusion cooling of a surface (218) of the second combustion chamber (36).

Abstract translation: 火箭发动机（10）包括用于将相应燃料（20）和氧化剂（18）推进剂组分喷射到第一燃烧室（34）中的第一（76）和第二（142）旋转喷射器，并且其中的流出物（38）驱动 使旋转喷射器（76,142）旋转的涡轮机（40）。 第一燃烧室（34）内的混合物优选为富燃料，以便降低相关联的燃烧温度，并且富含燃料的流出物在第二燃烧室（36）中与另外的由第三旋转喷射器（182）注入的氧化剂混合 ），以产生适于推进的高温流出物（214）。 旋转喷射器（76,142,182）适配于相关联的旋转压力捕集器（86,146,174），以将低压推进剂供应源（22'，24'）与相应燃烧室中相对较高的压力隔离 （34,36）。 来自第一燃烧室（34）的富含燃料的流出物的一部分被引导通过围绕燃烧室（34,36）的环形通道（198,204），以提供第二燃烧表面（218）的渗出冷却 室（36）。