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1. 发明授权

US08142163B1 Turbine blade with spar and shell 有权
标题翻译：涡轮叶片与翼梁和壳
公开(公告)号：US08142163B1
公开(公告)日：2012-03-27
申请号：US12024667
申请日：2008-02-01
申请人： Daniel O Davies
发明人： Daniel O Davies
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/187 , F01D5/20 , F05D2300/131
摘要： A turbine blade for use in a gas turbine engine, the turbine blade being made from a spar and shell construction in which the spar extends from the root and forms a cavity in which cooling air is supplied to the blade. The shell is held between the tip cap and the platform in grooves. A tension rod extends from the root and through the cavity within the spar to engage with the tip cap and secure the tip cap and the shell in place. A pretension nut is secured to the tension rod on the root end and engages a surface of the root to allow for a tension to be applied to the tension rod. Ceramic rope seals are secured within the grooves between the shell ends and the groove to form a seal. An inner seal is secured within a groove of the spar and engages with a projecting member on the tip cap to form a seal. Heat shields are wrapped around the platforms to provide thermal protection to the platforms.
摘要翻译：一种用于燃气涡轮发动机的涡轮机叶片，涡轮机叶片由翼梁和壳体结构制成，其中翼梁从根部延伸并形成冷却空气供应到叶片的空腔。壳体保持在顶盖和平台之间的凹槽中。张力杆从根部延伸并且穿过翼梁内的空腔，以与尖端盖接合并将尖端盖和壳固定在适当位置。预紧螺母固定在根部的拉杆上，并与根部的表面接合以允许将张力施加到张力杆上。陶瓷绳密封件固定在壳体端部和凹槽之间的凹槽内以形成密封。内密封件固定在翼梁的凹槽内，并与顶盖上的突出构件接合以形成密封。隔热罩围绕平台缠绕，为平台提供热保护。

2. 发明申请

US20110142639A1 MODULAR TURBINE AIRFOIL AND PLATFORM ASSEMBLY WITH INDEPENDENT ROOT TEETH 失效
标题翻译：模块化涡轮机空气和平台组装，具有独立的根部
公开(公告)号：US20110142639A1
公开(公告)日：2011-06-16
申请号：US12793935
申请日：2010-06-04
申请人： Christian X. Campbell , Daniel O. Davies , Darryl Eng
发明人： Christian X. Campbell , Daniel O. Davies , Darryl Eng
IPC分类号： F01D5/18 , F01D5/00
CPC分类号： F01D5/147 , F01D5/081 , F01D5/3007 , F01D11/008
摘要： A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second portion of the shank (29) that extends below the platform (30E-H) to engage other slots (52) in the disk. Thus the platform (30E-H) and the shank (23E-H) independently support their own centrifugal loads via their respective teeth. The platform may be formed in two portions (32E-H, 34E-H), that are bonded to each other at matching end-walls (37) and/or via pins (36G) passing through the shank (23E-H). Coolant channels (41, 43) may pass through the shank beside the pins (36G).
摘要翻译：涡轮机翼（22E-H）从柄（23E-H）延伸。平台（30E-H）支架或围绕柄部（23E-H）的第一部分。相对的齿（33,35）从平台（30E-H）横向地延伸以与盘中的相应的槽（50）接合。相对的齿（25,27）从在所述平台（30E-H）下方延伸的所述柄（29）的第二部分横向延伸，以接合所述盘中的其它狭槽（52）。因此，平台（30E-H）和柄（23E-H）通过其相应的齿独立地支撑它们自己的离心载荷。平台可以形成为两个部分（32E-H，34E-H），它们在通过柄（23E-H）的匹配端壁（37）和/或通孔销（36G）处彼此结合。冷却剂通道（41,43）可以穿过销（36G）旁边的柄。

3. 发明授权

US5048288A Combined turbine stator cooling and turbine tip clearance control 失效
标题翻译：组合涡轮定子冷却和涡轮机顶端间隙控制
公开(公告)号：US5048288A
公开(公告)日：1991-09-17
申请号：US644461
申请日：1990-11-13
申请人： Alan D. Bessette , Daniel O. Davies , John L. Shade
发明人： Alan D. Bessette , Daniel O. Davies , John L. Shade
IPC分类号： F01D11/24
CPC分类号： F01D11/24
摘要： The outer air seal of a gas turbine engine is continuously cooled by compressor discharge air (primary) and a by-pass line (secondary) which can be throttled or shut off, augments cooling during high power conditions and is throttled or shut off at reduced power conditions, allowing the casing scrubbed by fan discharged air to shrink and reduce the clearance of the tips of the turbine blades. The air from the continuous flow (primary) line is routed to the outer air seals in a manner to avoid scrubbing the engine case.
摘要翻译：燃气涡轮发动机的外部空气密封通过压缩机排出空气（初级）和旁通管线（次级）连续冷却，其可以被节流或切断，在高功率条件下增加冷却并且在减少的情况下被节流或切断功率条件，允许通过风扇排出的空气来净化的套管收缩并且减小涡轮叶片的尖端的间隙。来自连续流（主）线的空气以避免擦洗发动机壳体的方式被引导到外部空气密封件。

4. 发明授权

US08162617B1 Turbine blade with spar and shell 有权
标题翻译：涡轮叶片与翼梁和壳
公开(公告)号：US08162617B1
公开(公告)日：2012-04-24
申请号：US12022217
申请日：2008-01-30
申请人： Daniel O. Davies , Ross H. Peterson
发明人： Daniel O. Davies , Ross H. Peterson
IPC分类号： F01D5/14
CPC分类号： F01D5/189 , F01D5/147 , F05D2230/232 , F05D2230/60 , Y02T50/676
摘要： A turbine blade with a spar and shell construction in which the spar and the shell are both secured within two platform halves. The spar and the shell each include outward extending ledges on the bottom ends that fit within grooves formed on the inner sides of the platform halves to secure the spar and the shell against radial movement when the two platform halves are joined. The shell is also secured to the spar by hooks extending from the shell that slide into grooves formed on the outer surface of the spar. The hooks form a serpentine flow cooling passage between the shell and the spar. The spar includes cooling holes on the lower end in the leading edge region to discharge cooling air supplied through the platform root and into the leading edge cooling channel.
摘要翻译：具有翼梁和壳结构的涡轮叶片，其中翼梁和壳体均固定在两个平台的两半内。翼梁和壳体各自包括在底端上的向外延伸的突出部，其配合在形成在平台半部的内侧上的槽内，以在两个平台半部接合时将翼梁和壳体抵抗径向移动。壳体还通过从壳体延伸的钩子固定到翼梁上，所述钩子滑入形成在翼梁的外表面上的凹槽中。钩在壳和翼梁之间形成蛇形流冷却通道。翼梁在前缘区域的下端包括冷却孔，以排出通过平台根部供应并进入前缘冷却通道的冷却空气。

5. 发明授权

US07958777B1 Thermal mechanical fatigue test rig 有权
标题翻译：热机械疲劳试验台
公开(公告)号：US07958777B1
公开(公告)日：2011-06-14
申请号：US12573133
申请日：2009-10-04
申请人： Daniel O. Davies , Ross H Peterson
发明人： Daniel O. Davies , Ross H Peterson
IPC分类号： G01M15/14
CPC分类号： G01M99/002
摘要： A thermal mechanical fatigue test rig for testing a coating, such as a thermal barrier coating, under high temperature and pressure to simulate the actual operating environment of the coating. The test rig includes a combustor to produce a hot gas flow, a hollow test specimen on which the coating is placed, and a sapphire vessel that encloses the hollow test specimen to form a hot gas flow path over the coating. The sapphire vessel is clear so that the coating can be observed by a camera during the testing. An exhaust plenum is formed around the sapphire vessel to collect the exhaust form the hot gas flow in which additional cooling air and water for quenching can be injected to reduce the temperature of the hot gas flow prior to discharge from the test rig.
摘要翻译：一种热机械疲劳试验台，用于在高温和高压下测试涂层，如热障涂层，以模拟涂层的实际操作环境。试验台包括一个产生热气流的燃烧器，一个中空的试样，涂有涂层的中空试样，以及包围中空试样以形成涂层上的热气流路的蓝宝石容器。蓝宝石容器是清洁的，使得在测试期间可以通过照相机观察涂层。在蓝宝石容器周围形成排气室，以收集热气流的排气，其中可以注入额外的冷却空气和用于淬火的水，以在从试验台排出之前降低热气流的温度。

6. 发明授权

US08496443B2 Modular turbine airfoil and platform assembly with independent root teeth 失效
标题翻译：模块化涡轮机翼型和具有独立根齿的平台组件
公开(公告)号：US08496443B2
公开(公告)日：2013-07-30
申请号：US12793935
申请日：2010-06-04
申请人： Christian X. Campbell , Daniel O. Davies , Darryl Eng
发明人： Christian X. Campbell , Daniel O. Davies , Darryl Eng
IPC分类号： F01D5/30
CPC分类号： F01D5/147 , F01D5/081 , F01D5/3007 , F01D11/008
摘要： A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second portion of the shank (29) that extends below the platform (30E-H) to engage other slots (52) in the disk. Thus the platform (30E-H) and the shank (23E-H) independently support their own centrifugal loads via their respective teeth. The platform may be formed in two portions (32E-H, 34E-H), that are bonded to each other at matching end-walls (37) and/or via pins (36G) passing through the shank (23E-H). Coolant channels (41, 43) may pass through the shank beside the pins (36G).
摘要翻译：涡轮机翼（22E-H）从柄（23E-H）延伸。平台（30E-H）支架或围绕柄部（23E-H）的第一部分。相对的齿（33,35）从平台（30E-H）横向地延伸以与盘中的相应的槽（50）接合。相对的齿（25,27）从在所述平台（30E-H）下方延伸的所述柄（29）的第二部分横向延伸，以接合所述盘中的其它狭槽（52）。因此，平台（30E-H）和柄（23E-H）通过其相应的齿独立地支撑它们自己的离心载荷。平台可以形成为两个部分（32E-H，34E-H），它们在通过柄（23E-H）的匹配端壁（37）和/或通孔销（36G）处彼此结合。冷却剂通道（41,43）可以穿过销（36G）旁边的柄。

7. 发明授权

US08281649B1 Advanced hot section materials and coatings test rig 有权
标题翻译：先进的热段材料和涂料试验台
公开(公告)号：US08281649B1
公开(公告)日：2012-10-09
申请号：US12814130
申请日：2010-06-11
申请人： Jeffrey M Crutchfield , Daniel O Davies , Ross H Peterson , Mark M Harris , Natalie L Marshall
发明人： Jeffrey M Crutchfield , Daniel O Davies , Ross H Peterson , Mark M Harris , Natalie L Marshall
IPC分类号： G01M15/14
CPC分类号： G01M15/14
摘要： A test rig that reproduces high temperature and high pressure conditions found in a gas turbine engine for testing materials under these conditions. The test rig includes a combustor surrounded by an upper plenum chamber and an exhaust plenum that receives a hot gas stream from the combustor. A transparent channeling vessel guides the hot gas stream from the combustor over a test specimen on which a material to be tested is mounted. The hot gas stream exits the clear channeling vessel and into the exhaust plenum where the stream is cooled by diluting the stream with cooling air. A viewing portal is located in the exhaust plenum so that the material can be observed through the clear vessel.
摘要翻译：在这种条件下，用于测试燃料涡轮发动机中测试材料的高温和高压条件的试验台。试验台包括由上部增压室和排气室围绕的燃烧室，其接纳来自燃烧器的热气流。透明导流容器将来自燃烧器的热气流引导到其上安装待测试材料的试样上。热气流从清澈的沟渠容器中排出并进入排气室，通过用冷却空气稀释流来冷却气流。观察门口位于排气通风室中，使得可以通过清洁容器观察材料。

8. 发明授权

US07972113B1 Integral turbine blade and platform 有权
标题翻译：整体涡轮叶片和平台
公开(公告)号：US07972113B1
公开(公告)日：2011-07-05
申请号：US11799642
申请日：2007-05-02
申请人： Daniel O. Davies
发明人： Daniel O. Davies
IPC分类号： F01D5/30
CPC分类号： F01D5/025 , F01D5/147 , F01D5/3007 , F05D2300/606 , Y02T50/672
摘要： A turbine blade for a gas turbine engine, in which the turbine blade includes an airfoil portion with a root having a dovetail shape, and two platform halves that include a dovetail shaped opening within the platform halves to secure the blade root within the platform halves when fastened together. The platform halves have an outer fir tree shaped surface so that the blade assembly can be inserted into a slot within a rotor disk. the blade is uncoupled from the platform in the invention so that the airfoil can be made from a single crystal material with low casting defects because the platform is not cast with the airfoil. the two platform halves include the openings with side walls that are curved to follow the contour of the airfoil root so that the airfoil is secured within the platform halves against all directions of movement. An annular groove extends around the platform opening to provide for a seal to produce a seal between the high pressure cooling air supply passage within the platform and the lower pressure hot gas flow passing through the blade.
摘要翻译：一种用于燃气涡轮发动机的涡轮机叶片，其中涡轮机叶片包括具有燕尾形状的根部的翼型部分和两个平台半部，其包括在该平台的半部内的燕尾形开口，以将叶片根部固定在平台半部内，紧固在一起平台一半具有外部杉木树形表面，使得叶片组件可以插入转子盘内的槽中。叶片与本发明的平台脱离联接，使得翼型件可以由具有低铸件缺陷的单晶材料制成，因为该平台不被翼型铸造。两个平台半部包括具有侧壁的开口，该侧壁弯曲以跟随翼型根部的轮廓，使得翼型件抵抗所有运动方向固定在平台半部内。环形槽围绕平台开口延伸以提供密封件以在平台内的高压冷却空气供应通道和通过叶片的低压热气流之间产生密封。

9. 发明申请

US20080053107A1 Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine 有权
标题翻译：可滑动的弹簧加载的过渡到涡轮密封装置和热屏蔽系统，包括在燃气涡轮发动机的过渡/涡轮连接处的密封件
公开(公告)号：US20080053107A1
公开(公告)日：2008-03-06
申请号：US11498478
申请日：2006-08-03
申请人： Adam J. Weaver , Raymond S. Nordlund , David B. Allen , Daniel O. Davies
发明人： Adam J. Weaver , Raymond S. Nordlund , David B. Allen , Daniel O. Davies
IPC分类号： F02C7/20 , F01D25/26
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28
摘要： One embodiment of a transition-to-turbine seal (300) comprises a first, flattened section (302) adapted to be received in a peripheral axial slot (320) of a transition (325), and a second, generally C-shaped section (301). The generally C-shaped section (301) comprises a flattened portion (305) near the first, flattened section (302), and a curved portion (306) extending to a free edge (307). A fiber metal strip component (309) may be attached to the flattened portion (305) to define a first engagement surface adapted to engage an upstream side (336) of an outer vane seal rail (337), and a second engagement surface 308, adjacent the free edge (307), provides an opposed wear surface adapted to engage a downstream side (338) of the outer vane seal rail (337). System embodiments also are described, in which such transition-to-turbine seal (300) is isolated from a hot gas path (350) by provision of a plurality of cooling apertures (327) in the transition (325).
摘要翻译：过渡到涡轮机密封件（300）的一个实施例包括适于容纳在过渡（325）的周向轴向槽（320）中的第一平坦部分（302），以及第二大致C形截面（301）。大致C形截面（301）包括靠近第一平坦部分（302）的平坦部分（305）和延伸到自由边缘（307）的弯曲部分（306）。纤维金属带部件（309）可以附接到平坦部分（305）以限定适于接合外部叶片密封轨道（337）的上游侧（336）的第一接合表面，以及第二接合表面308，邻近自由边缘（307），提供适于接合外部叶片密封轨道（337）的下游侧（338）的相对的磨损表面。还描述了系统实施例，其中通过在过渡（325）中设置多个冷却孔（327），这种过渡到涡轮机密封件（300）与热气体路径（350）隔离。

10. 发明授权

US07784264B2 Slidable spring-loaded transition-to-turbine seal apparatus and heat-shielding system, comprising the seal, at transition/turbine junction of a gas turbine engine 有权
标题翻译：可滑动的弹簧加载的过渡到涡轮密封装置和热屏蔽系统，包括在燃气涡轮发动机的过渡/涡轮连接处的密封件
公开(公告)号：US07784264B2
公开(公告)日：2010-08-31
申请号：US11498478
申请日：2006-08-03
申请人： Adam J. Weaver , Raymond S. Nordlund , David B. Allen , Daniel O. Davies
发明人： Adam J. Weaver , Raymond S. Nordlund , David B. Allen , Daniel O. Davies
IPC分类号： F04D29/04 , F23R3/42
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28
摘要： One embodiment of a transition-to-turbine seal (300) comprises a first, flattened section (302) adapted to be received in a peripheral axial slot (320) of a transition (325), and a second, generally C-shaped section (301). The generally C-shaped section (301) comprises a flattened portion (305) near the first, flattened section (302), and a curved portion (306) extending to a free edge (307). A fiber metal strip component (309) may be attached to the flattened portion (305) to define a first engagement surface adapted to engage an upstream side (336) of an outer vane seal rail (337), and a second engagement surface 308, adjacent the free edge (307), provides an opposed wear surface adapted to engage a downstream side (338) of the outer vane seal rail (337). System embodiments also are described, in which such transition-to-turbine seal (300) is isolated from a hot gas path (350) by provision of a plurality of cooling apertures (327) in the transition (325).
摘要翻译：过渡到涡轮机密封件（300）的一个实施例包括适于容纳在过渡（325）的周向轴向槽（320）中的第一平坦部分（302），以及第二大致C形截面（301）。大致C形截面（301）包括靠近第一平坦部分（302）的平坦部分（305）和延伸到自由边缘（307）的弯曲部分（306）。纤维金属带部件（309）可以附接到平坦部分（305）以限定适于接合外部叶片密封轨道（337）的上游侧（336）的第一接合表面，以及第二接合表面308，邻近自由边缘（307），提供适于接合外部叶片密封轨道（337）的下游侧（338）的相对的磨损表面。还描述了系统实施例，其中通过在过渡（325）中设置多个冷却孔（327），这种过渡到涡轮机密封件（300）与热气体路径（350）隔离。

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