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1. 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。

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

US06286302B1 Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein 失效
标题翻译：文丘里管用于其中注入有水的燃气轮机燃烧器的涡流杯组件
公开(公告)号：US06286302B1
公开(公告)日：2001-09-11
申请号：US09283428
申请日：1999-04-01
申请人： Gilbert Farmer , James A. Groeschen , Mark G. Rettig
发明人： Gilbert Farmer , James A. Groeschen , Mark G. Rettig
IPC分类号： F02C700
CPC分类号： F23L7/002 , F23D2211/00 , F23R3/14
摘要： A combustion apparatus for a gas turbine engine including a combustor structure having at least one combustion chamber, a dual cone fuel nozzle for injecting both fuel and water to the combustion chamber, and a swirl cup package upstream of and adjacent to the combustion chamber. The swirl cup package further includes a swirler and a venturi extending between the nozzle and the combustion chamber for mixing the fuel and water with air. The venturi is configured to have a non-uniform thickness from an upstream end to a downstream end resulting in a cross-sectional area which provides a heat transfer conduction path that reduces axial stresses imposed on the venturi when water impinges on an upstream portion of the venturi.
摘要翻译：一种用于燃气涡轮发动机的燃烧装置，其包括具有至少一个燃烧室的燃烧器结构，用于将燃料和水喷射到燃烧室的双锥形燃料喷嘴，以及在燃烧室上游和邻近燃烧室的涡流杯组件。涡流杯包装还包括在喷嘴和燃烧室之间延伸的旋流器和文氏管，用于将燃料和水与空气混合。文丘里管构造成具有从上游端到下游端的不均匀的厚度，从而产生横截面积，该横截面面积提供传热传导路径，当水冲击在文丘里管的上游部分时，该导热路径减小施加在文氏管上的轴向应力文丘里

5. 发明授权

US07022940B2 Combustor linear and method for making thereof 失效
标题翻译：燃烧器线性及其制造方法
公开(公告)号：US07022940B2
公开(公告)日：2006-04-04
申请号：US10722101
申请日：2003-11-24
申请人： Gilbert Farmer , James A. Groeschen , Ronald D. Redden , Shaun M. DeVane
发明人： Gilbert Farmer , James A. Groeschen , Ronald D. Redden , Shaun M. DeVane
IPC分类号： B23K26/00
CPC分类号： F23R3/002 , B23K26/244 , B23K2101/001
摘要： A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such a combustor liner is also provided.
摘要翻译：燃烧器衬套设置有第一和第二环形带，其限定重叠的圆周接合区域，其中在包围接头区域的基本上所有轴向长度的接头区域中设置焊缝。还提供了一种用于制造这种燃烧器衬套的方法。

6. 发明授权

US06672067B2 Corrugated cowl for combustor of a gas turbine engine and method for configuring same 失效
标题翻译：用于燃气涡轮发动机的燃烧器的波纹罩及其配置方法
公开(公告)号：US06672067B2
公开(公告)日：2004-01-06
申请号：US10085767
申请日：2002-02-27
申请人： Gilbert Farmer , Ronald D. Redden , Balena B. Shorter , James A. Groeschen , Mehmet M. Dede , Daniel L. Durstock
发明人： Gilbert Farmer , Ronald D. Redden , Balena B. Shorter , James A. Groeschen , Mehmet M. Dede , Daniel L. Durstock
IPC分类号： F02C100
CPC分类号： F23R3/04
摘要： A cowl for use with a combustor of a gas turbine engine, the cowl includes a main body with an annular corrugation. A combustor of a gas turbine engine, the combustor includes: a hollow body defining a combustion chamber, the hollow body having a liner; an outer cowl having an annular corrugation, the cowl connecting to the liner; and an inner cowl connecting to the liner. A method of configuring a cowl for a gas turbine engine combustor, the method includes forming an annular corrugation in a main body of the cowl.
摘要翻译：一种与燃气涡轮发动机的燃烧器一起使用的整流罩，整流罩包括具有环形波纹的主体。燃气涡轮发动机的燃烧器，所述燃烧器包括：限定燃烧室的空心体，所述中空体具有衬套; 具有环形波纹的外整流罩，连接到衬套的整流罩; 以及连接到衬管的内罩。一种配置燃气涡轮发动机燃烧室的整流罩的方法，包括在整流罩的主体中形成环形波纹。

7. 发明授权

US06651437B2 Combustor liner and method for making thereof 失效
标题翻译：燃烧器衬管及其制造方法
公开(公告)号：US06651437B2
公开(公告)日：2003-11-25
申请号：US10028028
申请日：2001-12-21
申请人： Gilbert Farmer , James A. Groeschen , Ronald D. Redden , Shaun M. DeVane
发明人： Gilbert Farmer , James A. Groeschen , Ronald D. Redden , Shaun M. DeVane
IPC分类号： F23R306
CPC分类号： F23R3/002 , B23K26/244 , B23K2101/001
摘要： A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such a combustor liner is also provided.
摘要翻译：燃烧器衬套设置有第一和第二环形带，其限定重叠的圆周接合区域，其中在包围接头区域的基本上所有轴向长度的接头区域中设置焊缝。还提供了一种用于制造这种燃烧器衬套的方法。

8. 发明授权

US06908657B2 Coated component with through-hole having improved surface finish 失效
标题翻译：具有通孔的涂层部件具有改进的表面光洁度
公开(公告)号：US06908657B2
公开(公告)日：2005-06-21
申请号：US10605241
申请日：2003-09-17
申请人： Gilbert Farmer , Jeffrey Arnold Fehrenbach
发明人： Gilbert Farmer , Jeffrey Arnold Fehrenbach
IPC分类号： B24C1/00 , B23P6/00 , B24C11/00 , C23C4/00 , F01D5/18 , F01D5/28 , B32B3/10 , F02G1/00
CPC分类号： B23P6/002 , B23P2700/06 , C23C4/00 , F01D5/186 , F01D5/288 , F05D2230/13 , F05D2260/607 , Y10T29/49318 , Y10T29/49339 , Y10T428/12361 , Y10T428/24273 , Y10T428/249953
摘要： A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of a component as a result of depositing a coating of the TBC material on a surface of the component, in which the deposit is removed from the cooling hole without damaging the cooling hole or the TBC coating surrounding the cooling hole on the coated surface of the component. A preferred feature is that the cooling hole, including the entrance to the hole at a surface of the component opposite the coated surface and the coating surrounding the exit of the hole at the coated surface, exhibits improved surface characteristics that increase the discharge coefficient of the cooling hole, as evidenced by an increase in the effective area of the cooling hole.
摘要翻译：从空气冷却燃气涡轮发动机的冷却孔中除去金属结合层和陶瓷材料等成分的通孔的沉积物的工序。该方法特别有效地除去沉积在部件的冷却孔中的TBC材料，这是因为在组件的表面上沉积TBC材料的涂层，其中沉积物从冷却孔移除而不损坏冷却孔或TBC涂层，围绕组件的涂覆表面上的冷却孔。一个优选的特征是，包括在与涂覆表面相对的部件的表面处的孔的入口和围绕涂覆表面的孔的出口的涂层的冷却孔表现出改进的表面特性，其增加了如冷却孔的有效面积的增加所证明的。

9. 发明授权

US06655149B2 Preferential multihole combustor liner 有权
公开(公告)号：US06655149B2
公开(公告)日：2003-12-02
申请号：US10321088
申请日：2002-12-17
申请人： Gilbert Farmer , Daniel Dale Brown , Myron Edward Rutherford
发明人： Gilbert Farmer , Daniel Dale Brown , Myron Edward Rutherford
IPC分类号： F01D2512
CPC分类号： F23R3/06 , Y02T50/675
摘要： A multi-hole cooled combustor liner is provided which reduces hot streaks and associated material distress in the liner. Areas of increased cooling hole density are disposed upstream of the primary dilution holes and in circumferential alignment with fuel cup centers. Additional cooling holes are provided in between primary dilution holes are arranged in alternating pairs of circumferentially angled holes so as to provide a converging cooling air flow in the downstream direction.

10. 发明授权

US06561872B2 Method and apparatus for stripping coating 有权
公开(公告)号：US06561872B2
公开(公告)日：2003-05-13
申请号：US09878847
申请日：2001-06-11
申请人： Gilbert Farmer , Jeffrey Arnold Fehrenbach , William Lee Imhoff , David Allen Kastrup
发明人： Gilbert Farmer , Jeffrey Arnold Fehrenbach , William Lee Imhoff , David Allen Kastrup
IPC分类号： B24B100
CPC分类号： B44D3/16 , B08B3/02
摘要： A method of stripping coating from a portion of a coated surface of a component. The method includes fastening a mask sheet to the component over a region adjacent the portion of the coated surface. The mask sheet has a contour generally corresponding to a contour of the surface of the component. A high pressure fluid jet is sprayed from a spray head toward the portion of the coated surface after the mask sheet is fastened to the component to strip the coating from the portion of the surface. After the coating is stripped from the portion of the surface, the mask sheet is removed from the component.

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