公开(公告)号：US09140215B2

公开(公告)日：2015-09-22

申请号：US13420021

申请日：2012-03-14

Applicant: Jim A. Clark

Inventor： Jim A. Clark

IPC: F02K9/60 ,  G01M15/00 ,  G01M3/04 ,  G01F1/36 ,  F02K9/56 ,  G01F1/44

CPC classification number: F02K9/60 ,  F02K9/56 ,  F05D2260/80 ,  F05D2270/301 ,  G01F1/36 ,  G01F1/363 ,  G01F1/44 ,  G01M3/04 ,  G01M15/00

Abstract: A rocket engine with a manifold is in communication with a combustion chamber. A sense line extends through the propellant manifold and into the combustion chamber. The sense line includes a venturi arranged downstream from the combustion chamber, and at least one aperture fluidly connecting the propellant manifold to a sense-line passageway downstream from the venturi. A method of sensing conditions in a combustion chamber includes exposing an end of a sense line to the combustion chamber, creating a low static pressure in the sense line at a location upstream from the end, introducing a fluid at the location to purge the sense line, and sensing the conditions downstream from the location.

Abstract translation: 具有歧管的火箭发动机与燃烧室连通。 感测线延伸穿过推进剂歧管并进入燃烧室。 感测线包括布置在燃烧室下游的文丘里管，以及将推进剂歧管流体连接到文丘里管下游的感测线通道的至少一个孔。 感测燃烧室中的条件的方法包括将感测线的端部暴露于燃烧室，在端部上游的位置处在感测线中产生低静压，在该位置处引入流体以清除感测线 ，并感测位置下游的条件。

公开(公告)号：US5373694A

公开(公告)日：1994-12-20

申请号：US103317

申请日：1993-08-09

Applicant: Jim A. Clark

Inventor： Jim A. Clark

IPC: F23R3/12 ,  F23R3/28 ,  F02C3/06

CPC classification number: F23D11/38 ,  F23R3/12 ,  F23R3/28

Abstract: The radial jets of a fuel nozzle for the combustor of a gas turbine engine are non-axisymmetrically disposed around the tip of the fuel nozzle to distribute the fuel into the swirler unevenly around the circumference to reduce pattern factor.

Abstract translation: 用于燃气涡轮发动机的燃烧器的燃料喷嘴的径向射流不是对称地设置在燃料喷嘴的尖端周围，以将燃料分布在旋转器周围不均匀以减小图案因素。

公开(公告)号：US20130239545A1

公开(公告)日：2013-09-19

申请号：US13420021

申请日：2012-03-14

Applicant: Jim A. Clark

Inventor： Jim A. Clark

IPC: F02K9/60 ,  G01M3/04 ,  G01M15/00

CPC classification number: F02K9/60 ,  F02K9/56 ,  F05D2260/80 ,  F05D2270/301 ,  G01F1/36 ,  G01F1/363 ,  G01F1/44 ,  G01M3/04 ,  G01M15/00

Abstract: A rocket engine with a manifold is in communication with a combustion chamber. A sense line extends through the propellant manifold and into the combustion chamber. The sense line includes a venturi arranged downstream from the combustion chamber, and at least one aperture fluidly connecting the propellant manifold to a sense-line passageway downstream from the venturi. A method of sensing conditions in a combustion chamber includes exposing an end of a sense line to the combustion chamber, creating a low static pressure in the sense line at a location upstream from the end, introducing a fluid at the location to purge the sense line, and sensing the conditions downstream from the location.

Abstract translation: 具有歧管的火箭发动机与燃烧室连通。 感测线延伸穿过推进剂歧管并进入燃烧室。 感测线包括布置在燃烧室下游的文丘里管，以及将推进剂歧管流体连接到文丘里管下游的感测线通道的至少一个孔。 感测燃烧室中的条件的方法包括将感测线的端部暴露于燃烧室，在端部上游的位置处在感测线中产生低静态压力，在该位置处引入流体以清除感测线 ，并感测位置下游的条件。

公开(公告)号：US07464537B2

公开(公告)日：2008-12-16

申请号：US11098065

申请日：2005-04-04

Applicant: Jim A. Clark ,  Gregg W. Jones

Inventor： Jim A. Clark ,  Gregg W. Jones

IPC: F02K11/00

CPC classification number: F02K9/64 ,  F05D2260/221 ,  F05D2260/2212

Abstract: A combustion chamber for use in an engine, such as a rocket engine, has an inner wall with a corrugated configuration. The inner wall is formed with a plurality of tubes for carrying a coolant. As a result of the tubular construction, the inner wall has a plurality of spaced apart crowns and a plurality of valleys intermediate with the spaced apart crowns. To enhance the rate of heat flux or transfer in the valleys, a device is installed in each valley to cause local intensification of the turbulence in the hot gas flow in an effective way. The device may take the shape of a chevron or a bump.

Abstract translation: 用于诸如火箭发动机的发动机中的燃烧室具有波纹形状的内壁。 内壁形成有用于承载冷却剂的多个管。 作为管状结构的结果，内壁具有多个间隔开的冠部以及具有间隔开的冠部中间的多个谷部。 为了提高谷中的热通量或转移率，在每个谷中安装一个装置，以有效地引起热气流中的湍流的局部增强。 该装置可以采取人字形或凸块的形状。

公开(公告)号：US5465571A

公开(公告)日：1995-11-14

申请号：US171362

申请日：1993-12-21

Applicant: Jim A. Clark

Inventor： Jim A. Clark

IPC: F23R3/28 ,  F02C7/22

CPC classification number: F23R3/283

Abstract: In a gas turbine, a linear stem extends through a diffuser and a combustor cowl into a sleeve that is attached to the swirler in such a way that the sleeve can move relative to the swirler but is supported on the swirler. The stem slides into the sleeve and contains a fuel nozzle that supplies fuel through a sleeve outlet to a swirler inlet.

Abstract translation: 在燃气轮机中，线性杆通过扩散器和燃烧器整流罩延伸到套筒中，该套管以旋转器相对于旋流器移动但支撑在旋流器上的方式附接到旋流器。 杆滑入套筒并且包含燃料喷嘴，其通过套筒出口将燃料供应到旋流器入口。

公开(公告)号：US4843825A

公开(公告)日：1989-07-04

申请号：US194354

申请日：1988-05-16

Applicant: Jim A. Clark

Inventor： Jim A. Clark

IPC: F23R3/00 ,  F23R3/10

CPC classification number: F23R3/10 ,  F23R3/002 ,  F05B2260/201

Abstract: An annular combustor has a plurality of fuel injectors 14, each supporting a heat shield 30. Each shield has an overlap portion 42 deflecting cooling air passing between the shields, thereby avoiding a curtain of air between the flames of adjacent fuel injectors.

Abstract translation: 环形燃烧器具有多个燃料喷射器14，每个燃料喷射器14各自支撑隔热罩30.每个屏蔽件具有重叠部分42，该重叠部分42使通过屏蔽之间的冷却空气偏转，从而避免相邻燃料喷射器的火焰之间的空气帘幕。

公开(公告)号：US09127622B2

公开(公告)日：2015-09-08

申请号：US13300775

申请日：2011-11-21

Applicant: Jim A. Clark ,  Craig W. Irwin ,  Reed A. Kakuska

Inventor： Jim A. Clark ,  Craig W. Irwin ,  Reed A. Kakuska

IPC: F02K9/56 ,  F16L55/027

CPC classification number: F02K9/566 ,  F02K9/64 ,  F02K9/972 ,  F15D1/025 ,  F16L55/027 ,  G05D7/0186

Abstract: A rocket engine fluid-flow system includes a pump fluidly interconnecting a fluid source to a combustion chamber. A nozzle is in fluid communication with the combustion chamber and includes coolant tubes fluidly arranged between the pump and the combustion chamber. An orifice has a throat and is fluidly arranged between the pump and the coolant tubes. The orifice has entrance and exit ramps arranged on either side of the throat. The exit ramp has an exit ramp surface with a divergent angle that is less than a right angle. The entrance ramp provides a smooth approach to the orifice throat. In one example, the exit ramp includes an exit ramp surface having a divergent angle of 20-60°. The exit ramp radius is less than twice the throat radius in one example.

Abstract translation: 火箭发动机流体流动系统包括将流体源流体地连接到燃烧室的泵。 喷嘴与燃烧室流体连通，并且包括流体地布置在泵和燃烧室之间的冷却剂管。 孔具有喉部并且流体地布置在泵和冷却剂管之间。 孔口具有设置在喉部两侧的入口和出口斜面。 出口斜坡具有出口斜面，其具有小于直角的发散角。 入口斜坡提供了孔口喉咙平滑的方法。 在一个示例中，出口斜坡包括具有20-60°的发散角的出口斜面。 在一个示例中，出口斜坡半径小于喉部半径的两倍。

公开(公告)号：US07373774B2

公开(公告)日：2008-05-20

申请号：US10777435

申请日：2004-02-12

Applicant: Jim A. Clark ,  Mark Ricciardo

Inventor： Jim A. Clark ,  Mark Ricciardo

IPC: F02K11/00 ,  F02C1/04

CPC classification number: F02K9/64

Abstract: A system for cooling a combustion chamber of an engine, such as a rocket engine, is provided. The system has a plurality of coolant tubes or passages surrounding the combustion chamber, a torroidal coolant-collection manifold for receiving coolant from the coolant tubes or passages and for discharging the coolant through a discharge port, and a plurality of turning vanes within the torroidal manifold for reducing pressure loss and improving pressure uniformity associated with the torroidal coolant-collection manifold.

Abstract translation: 提供了一种用于冷却诸如火箭发动机的发动机的燃烧室的系统。 该系统具有围绕燃烧室的多个冷却剂管或通道，用于从冷却剂管或通道接收冷却剂并且用于通过排出口排出冷却剂的环形冷却剂收集歧管以及在环形歧管内的多个转向叶片 用于减少压力损失并改善与环形冷却液收集歧管相关的压力均匀性。

公开(公告)号：US5267442A

公开(公告)日：1993-12-07

申请号：US977476

申请日：1992-11-17

Applicant: Jim A. Clark

Inventor： Jim A. Clark

IPC: F23D11/00 ,  F23D11/10 ,  F23R3/28 ,  F23R3/14

CPC classification number: F23R3/28 ,  F23D11/007 ,  F23D11/107

Abstract: The orifice of the primary circuit on a dual circuit fuel nozzle for a combustor of a gas turbine engine is eccentrically located at the nozzle tip to inject fuel directly toward the prefilming surface of the air swirler and located in proximity to the igniter to enhance ignition. In another embodiment the fuel nozzles circumferentially spaced around the dome of the combustor include the eccentric orifice of the primary circuit to enhance lean blowout characteristics.

Abstract translation: 在用于燃气涡轮发动机的燃烧器的双回路燃料喷嘴上的主回路的孔口偏心地位于喷嘴尖端处，以将燃料直接喷射到空气旋流器的预吹制表面并位于点火器附近以增强点火。 在另一个实施例中，围绕燃烧器的圆顶周向间隔开的燃料喷嘴包括主回路的偏心孔，以增强排气特性。

公开(公告)号：US4979361A

公开(公告)日：1990-12-25

申请号：US379310

申请日：1989-07-13

Applicant: Jim A. Clark ,  James H. Shadowen ,  Barton R. Field

Inventor： Jim A. Clark ,  James H. Shadowen ,  Barton R. Field

IPC: F23R3/04

CPC classification number: F23R3/04

Abstract: The diffuser for delivering compressor discharge air to the combustor of a gas turbine engine includes a prediffuser mounted ahead of a dump diffuser which includes step changes in the flow path at its inlet and adjacent the cowl of the combustor in the passageway of the dump diffuser for providing at least two sudden expansions of the diffuser flow.

Abstract translation: 用于将压缩机排放到燃气涡轮发动机的燃烧器的扩散器包括安装在排放扩散器之前的预扩散器，其包括在其入口处的流动路径中的逐渐变化，并且与排放扩散器的通道中的燃烧器的整流罩相邻， 提供扩散器流的至少两个突然膨胀。