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1. 发明授权

US07104066B2 Combuster swirler assembly 有权
标题翻译：燃烧器旋流器总成
公开(公告)号：US07104066B2
公开(公告)日：2006-09-12
申请号：US10604809
申请日：2003-08-19
申请人： Thomas Anthony Leen , Marwan Al-Roub , John Robert Staker
发明人： Thomas Anthony Leen , Marwan Al-Roub , John Robert Staker
IPC分类号： F01C1/00
CPC分类号： F23C7/004 , F23R3/14 , Y02T50/675
摘要： A unitary swirler assembly that provides improved service life, having a ferrule body and a unitary swirler body. The unitary swirler body has oppositely-directed primary swirler passages and secondary swirler passages. A pair of rails formed on the unitary swirler body engage the ferrule body to limit relative movement, and prevent relative rotation, of the ferrule body and the unitary swirler body.
摘要翻译：一个整体的旋流器组件，提供更好的使用寿命，具有套圈体和整体旋流器体。单一旋流器主体具有相反方向的初级旋流器通道和次级旋流器通道。形成在整体式旋流器主体上的一对轨道与套圈本体接合以限制套圈主体和整体旋流器主体的相对运动，并防止相对旋转。

2. 发明授权

US06655146B2 Hybrid film cooled combustor liner 有权
标题翻译：混合薄膜冷却燃烧器衬管
公开(公告)号：US06655146B2
公开(公告)日：2003-12-02
申请号：US09919028
申请日：2001-07-31
申请人： Ella Christine Kutter , Marwan Al-Roub , Thomas Anthony Leen , Daniel Dale Brown , Craig Douglas Young , Gilbert Farmer , Mohammad Ehteshami
发明人： Ella Christine Kutter , Marwan Al-Roub , Thomas Anthony Leen , Daniel Dale Brown , Craig Douglas Young , Gilbert Farmer , Mohammad Ehteshami
IPC分类号： F23R306
CPC分类号： F23M5/085 , F23R3/06 , F23R2900/03042 , Y02T50/675
摘要： A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.
摘要翻译：燃烧器衬套具有包括第一部分和第二部分的环形壳体。第一部分设置有槽膜冷却，第二部分设置有多孔膜冷却。根据待使用的衬套的燃烧器的性质，多孔冷却部分可以位于狭缝膜冷却部分的前部或后部。在一个可能的实施例中，衬套包括第一环形板，第二环形面板部分在其前端处连接到第一面板部分的后端，并且第三环形面板部分在其前端处连接到第二面板部分的后端。所述面板部分中的至少一个具有多孔膜冷却，并且所述面板部分中的至少一个具有狭缝膜冷却。

3. 发明授权

US06557350B2 Method and apparatus for cooling gas turbine engine igniter tubes 有权
标题翻译：用于冷却燃气涡轮发动机点火器管的方法和装置
公开(公告)号：US06557350B2
公开(公告)日：2003-05-06
申请号：US09859611
申请日：2001-05-17
申请人： Gilbert Farmer , Ella Christine Kutter , Steven Clayton Vise , John Robert Staker , Marwan Al-Roub , Tariq Kay Harris
发明人： Gilbert Farmer , Ella Christine Kutter , Steven Clayton Vise , John Robert Staker , Marwan Al-Roub , Tariq Kay Harris
IPC分类号： F02C722
CPC分类号： F23R3/50 , F23R3/283 , F23R2900/00012 , F23R2900/03044
摘要： A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.
摘要翻译：用于燃气涡轮发动机的燃烧器包括多个点火器管，其以成本有效和可靠的方式有助于降低燃烧器内的温度梯度。燃烧器包括环形外衬套，其包括多个开口，其尺寸设置成接收点火器管。每个点火器管保持接收在其中的每个点火器的对准，并且包括从点火器管径向向外延伸的空气冲击装置。在操作期间，接触空气冲击装置的气流径向向内引导，用于点火器管和燃烧器外衬套的冲击冷却。

4. 发明授权

US06834505B2 Hybrid swirler 有权
标题翻译：混合旋流器
公开(公告)号：US06834505B2
公开(公告)日：2004-12-28
申请号：US10265824
申请日：2002-10-07
申请人： Marwan Al-Roub , Stanford P. Seto , John Robert Staker , Ting-Yu Tu
发明人： Marwan Al-Roub , Stanford P. Seto , John Robert Staker , Ting-Yu Tu
IPC分类号： F23R304
CPC分类号： F23R3/14 , Y02T50/675
摘要： A swirler includes a tubular body having a row of secondary radial swirl vanes. A tubular ferrule adjoins the body at the secondary vanes, and includes a row of primary swirl vanes. The primary vanes are disposed axially obliquely to the secondary vanes, with a common annular inlet facing radially outwardly for swirling air radially inwardly therefrom with axial momentum into the tubular body.
摘要翻译：旋流器包括具有一排次级径向涡流叶片的管状体。管状套管在次级叶片处邻接身体，并且包括一排初级旋流叶片。主叶片轴向倾斜地设置到次级叶片，其中共同的环形入口面向径向向外，用于从其中径向向内旋转，从而具有轴向动量进入管状体。

5. 发明授权

US07654091B2 Method and apparatus for cooling gas turbine engine combustors 有权
标题翻译：用于冷却燃气涡轮发动机燃烧器的方法和装置
公开(公告)号：US07654091B2
公开(公告)日：2010-02-02
申请号：US11468486
申请日：2006-08-30
申请人： Marwan Al-Roub , Steven Vise
发明人： Marwan Al-Roub , Steven Vise
IPC分类号： F02C7/22
CPC分类号： F23R3/283 , F23R2900/03044
摘要： A method for operating a gas turbine engine includes channeling fluid from a cooling fluid source to a combustor that includes at least one deflector and flare cone. The deflector and flare cone are coupled together and are configured to define a cooling fluid channel therebetween. The flare cone has a plurality of cooling injectors extending therethrough. The plurality of injectors are spaced circumferentially about a centerline axis of the flare cone and are coupled in flow communication with the fluid source. The plurality of injectors has a plurality of first injectors and a plurality of second injectors. The method also includes directing a portion of the fluid through the plurality of first injectors. The method further includes directing a portion of the fluid through the plurality of second injectors, wherein the first plurality of injectors facilitates cooling a portion of the deflector more than the second plurality of injectors.
摘要翻译：一种用于操作燃气涡轮发动机的方法包括将流体从冷却流体源引导到包括至少一个偏转器和火炬锥的燃烧器。偏转器和喇叭形锥体联接在一起并且构造成在其间限定冷却流体通道。喇叭形锥体具有从其延伸穿过的多个冷却喷射器。多个喷射器围绕喇叭形锥体的中心线轴线周向间隔开并且与流体源流动连通地联接。多个喷射器具有多个第一喷射器和多个第二喷射器。该方法还包括将一部分流体引导通过多个第一喷射器。该方法还包括将流体的一部分引导通过多个第二喷射器，其中第一多个喷射器有助于冷却多于第二喷射器的偏转器的一部分。

6. 发明授权

US06651439B2 Methods and apparatus for supplying air to turbine engine combustors 有权
公开(公告)号：US06651439B2
公开(公告)日：2003-11-25
申请号：US09760167
申请日：2001-01-12
申请人： Marwan Al-Roub , Clifford Stephen Creevy , Hubert Smith Roberts, Jr. , Anthony Paul Greenwood
发明人： Marwan Al-Roub , Clifford Stephen Creevy , Hubert Smith Roberts, Jr. , Anthony Paul Greenwood
IPC分类号： F01C100
CPC分类号： F23R3/04 , Y02T50/675
摘要： A combustor for a gas turbine engine that facilitates reducing combustor chamber dump pressure losses to improve combustor and engine performance is described. The combustor includes a diffuser that diffuses airflow directed into the combustor. The diffuser includes an outer wall, an inner wall, and a plurality of splitter vanes between the outer wall and the inner wall. The splitter vanes are spaced radially apart, and each is spaced radially from a respective diffuser wall such that an outer passage, an inner passage, and a central passage are defined by the splitter vanes.

7. 发明申请

US20080053102A1 METHOD AND APPARATUS FOR COOLING GAS TURBINE ENGINE COMBUSTORS 有权
标题翻译：用于冷却燃气轮机发动机的方法和装置
公开(公告)号：US20080053102A1
公开(公告)日：2008-03-06
申请号：US11468486
申请日：2006-08-30
申请人： Marwan Al-Roub , Steven Vise
发明人： Marwan Al-Roub , Steven Vise
IPC分类号： F02C6/08
CPC分类号： F23R3/283 , F23R2900/03044
摘要： A method for operating a gas turbine engine includes channeling fluid from a cooling fluid source to a combustor that includes at least one deflector and flare cone. The deflector and flare cone are coupled together and are configured to define a cooling fluid channel therebetween. The flare cone has a plurality of cooling injectors extending therethrough. The plurality of injectors are spaced circumferentially about a centerline axis of the flare cone and are coupled in flow communication with the fluid source. The plurality of injectors has a plurality of first injectors and a plurality of second injectors. The method also includes directing a portion of the fluid through the plurality of first injectors. The method further includes directing a portion of the fluid through the plurality of second injectors, wherein the first plurality of injectors facilitates cooling a portion of the deflector more than the second plurality of injectors.
摘要翻译：一种用于操作燃气涡轮发动机的方法包括将流体从冷却流体源引导到包括至少一个偏转器和火炬锥的燃烧器。偏转器和喇叭形锥体联接在一起并且构造成在其间限定冷却流体通道。喇叭形锥体具有从其延伸穿过的多个冷却喷射器。多个喷射器围绕喇叭形锥体的中心线轴线周向间隔开并且与流体源流动连通地联接。多个喷射器具有多个第一喷射器和多个第二喷射器。该方法还包括将一部分流体引导通过多个第一喷射器。该方法还包括将流体的一部分引导通过多个第二喷射器，其中第一多个喷射器有助于冷却多个喷射器中的一部分偏转器。

8. 发明申请

US20050039458A1 COMBUSTER SWIRLER ASSEMBLY 有权
标题翻译：燃烧器SWIRLER总成
公开(公告)号：US20050039458A1
公开(公告)日：2005-02-24
申请号：US10604809
申请日：2003-08-19
申请人： Thomas Leen , Marwan Al-Roub , John Staker
发明人： Thomas Leen , Marwan Al-Roub , John Staker
IPC分类号： F23C7/00 , F23R3/14
CPC分类号： F23C7/004 , F23R3/14 , Y02T50/675
摘要： Aunitary swirler assembly that provides improved service life, having a ferrule body and a unitary swirler body. The unitary swirler body has oppositely-directed primary swirler passages and secondary swirler passages. A pair of rails formed on the unitary swirler body engage the ferrule body to limit relative movement, and prevent relative rotation, of the ferrule body and the unitary swirler body.
摘要翻译：独特的旋流器组件，提供更好的使用寿命，具有套圈主体和整体旋流器主体。单一旋流器主体具有相反方向的初级旋流器通道和次级旋流器通道。形成在整体式旋流器主体上的一对轨道与套圈本体接合以限制套圈主体和整体旋流器主体的相对运动，并防止相对旋转。

9. 发明授权

US06205763B1 Method of forming a swirler with as-cast holes 失效
标题翻译：用铸造孔形成旋流器的方法
公开(公告)号：US06205763B1
公开(公告)日：2001-03-27
申请号：US09317243
申请日：1999-05-24
申请人： Gilbert Farmer , James A. Groeschen , Jason P. Hoppa , Stanford P. Seto , Marwan Al-Roub
发明人： Gilbert Farmer , James A. Groeschen , Jason P. Hoppa , Stanford P. Seto , Marwan Al-Roub
IPC分类号： F02C1310
CPC分类号： F23C7/002 , F23R3/14 , Y02T50/675 , Y10T29/49229
摘要： A method for determining the appropriate hole parameters to achieve the desired airflow in a swirler with as-cast air jet holes includes the steps of determining the desired airflow through the holes and selecting a hole angle for the holes. Next, the ratio of the hole exit area to the hole inlet area is calculated based on the desired airflow and the selected hole angle using a regression equation. Then a value is determined for either of the hole exit area or the hole inlet area, and the other area is calculated from the known ratio. Once the hole angle, hole exit area and hole inlet area have been determined, then a swirler can be cast with as-cast holes using these hole parameters.
摘要翻译：用于确定适当的孔参数以在具有铸态空气喷射孔的旋流器中实现所需气流的方法包括以下步骤：确定通过孔的所需气流并选择孔的孔角。接下来，使用回归方程，基于期望的气流和所选择的孔角计算出孔面积与孔入口面积的比率。然后为孔出口区域或孔入口区域中的任一个确定值，并且从已知比例计算另一区域。一旦确定了孔角度，孔出口面积和孔入口面积，则可以使用这些孔参数用旋转器铸造旋流器。

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