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1. 发明授权

US06254756B1 Preparation of components having a partial platinum coating thereon 失效
标题翻译：制备其上具有部分铂涂层的部件
公开(公告)号：US06254756B1
公开(公告)日：2001-07-03
申请号：US09373269
申请日：1999-08-11
申请人： Antonio F. Maricocchi , Roger D. Wustman , Jonathan P. Clarke , Thomas E. Mantkowski , David G. W. Fargher , Jeffrey A. Conner
发明人： Antonio F. Maricocchi , Roger D. Wustman , Jonathan P. Clarke , Thomas E. Mantkowski , David G. W. Fargher , Jeffrey A. Conner
IPC分类号： C25D502
CPC分类号： C23C28/321 , C23C4/01 , C23C10/58 , C23C28/021 , C23C28/023 , C23C28/028 , C23C28/322 , C23C28/325 , C23C28/3455 , C25D5/02 , C25D7/00 , F01D5/288 , F05D2230/90 , F05D2300/143 , F05D2300/611 , Y02T50/67 , Y10T428/12736 , Y10T428/12875 , Y10T428/24802
摘要： A curved component such as a turbine airfoil, shroud, or combustor centerbody is prepared with a platinum or a platinum-aluminide protective coating over only a portion of the surface thereof. The coating may serve as an environmental coating, or as a bond coat of a thermal barrier coating system. The partial coverage is achieved by depositing platinum only over a portion of the surface of the component, typically including the concave portion in the case of an airfoil, optionally depositing an aluminum layer, and optionally interdiffusing the platinum and aluminum layers.
摘要翻译：在其表面的仅一部分上用铂或铂 - 铝化物保护涂层制备诸如涡轮机翼型，护罩或燃烧器中心体之类的弯曲部件。涂层可以用作环境涂层，或作为热障涂层系统的粘结层。部分覆盖是通过仅在组件表面的一部分上沉积铂来实现的，通常在翼型的情况下包括凹部，可选地沉积铝层，并且可选地相互扩散铂和铝层。

2. 发明授权

US5388962A Turbine rotor disk post cooling system 失效
标题翻译：涡轮转子盘后冷却系统
公开(公告)号：US5388962A
公开(公告)日：1995-02-14
申请号：US136143
申请日：1993-10-15
申请人： Thomas G. Wygle , David G. W. Fargher , Arthur J. Piekarski
发明人： Thomas G. Wygle , David G. W. Fargher , Arthur J. Piekarski
IPC分类号： F01D5/08 , F01D5/30 , F01D11/00
CPC分类号： F01D11/008 , F01D5/082 , F01D5/3015
摘要： The present invention discloses a system for cooling turbine rotor disk posts in a gas turbine engine with a preferred embodiment illustrating an application for a high pressure turbine stage 1 rotor disk. The disk includes a plurality of circumferentially alternating posts and slots disposed about the periphery of the disk with each slot receiving a dovetail of a radially extending blade. The cooling system comprises a plurality of seal bodies with each seal body including a relatively low volume thermal isolation chamber positioned over the top of a corresponding disk post; a plurality of axially extending blade cooling plenums supplied with cooling air with one of the plenums positioned radially inward of each of the blades; a plurality of shallow, radially extending slots formed in a relatively low stressed axially facing surface of each of the blade dovetails for diverting cooling air from the blade cooling plenums to the thermal isolation chambers. Cooling air flows from the blade cooling plenums through the slots into a radially extending plenum which supplies at least one hole in each seal body. The holes are in flow communication with the thermal isolation chambers and are oriented to cause the cooling air to impinge directly on the outer surface of each of the disk posts.
摘要翻译：本发明公开了一种用于冷却燃气涡轮发动机中的涡轮机转子盘柱的系统，其中优选实施例示出了用于高压涡轮级1转子盘的应用。盘包括围绕盘的周边设置的多个周向交替的柱和槽，每个槽容纳径向延伸叶片的燕尾。冷却系统包括多个密封体，每个密封体包括位于相应的圆柱的顶部上的相对低体积的热隔离室; 多个轴向延伸的叶片冷却气室，其供应有冷却空气，其中一个气室位于每个叶片的径向内侧; 多个浅的，径向延伸的狭槽形成在每个叶片燕尾榫的相对低应力的轴向面对的表面中，用于将冷却空气从叶片冷却风室转移到热隔离室。冷却空气从叶片冷却气室通过狭槽流入径向延伸的气室，其在每个密封体中提供至少一个孔。孔与热隔离室流动连通，并且被定向成使得冷却空气直接撞击在每个盘柱的外表面上。

3. 发明授权

US06290463B1 Slotted impingement cooling of airfoil leading edge 失效
标题翻译：机翼前缘的开槽冲击冷却
公开(公告)号：US06290463B1
公开(公告)日：2001-09-18
申请号：US09410241
申请日：1999-09-30
申请人： David G. W. Fargher , Ching-Pang Lee
发明人： David G. W. Fargher , Ching-Pang Lee
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2260/201 , Y02T50/676
摘要： A coolable gas turbine engine airfoil for a gas turbine engine suitable for a blade or vane includes an outer airfoil wall with pressure and suction sides extending chordwise between leading and trailing edges of the airfoil, a leading edge cooling plenum formed between a forward most span rib and the outer wall along the leading edge of the airfoil, and a cooling air channel within the airfoil bounded in part by the forward most rib. A slotted cooling air impingement element is disposed in the span rib for impinging cooling air from the channel on an interior surface of the outer airfoil wall along the leading edge of the airfoil. One embodiment of the slotted cooling air impingement element is a single longitudinally extending slot extending along almost an entire length of the forward most rib and the longitudinally slot preferably includes longitudinally spaced apart rounded ends. In another embodiment of the airfoil, the slotted cooling air impingement element is includes two or more closely spaced apart longitudinally extending slots extending along almost an entire length of the forward most rib and each of the longitudinally extending slots preferably has longitudinally spaced apart rounded ends
摘要翻译：用于适用于叶片或叶片的燃气涡轮发动机的可冷却燃气涡轮发动机翼型件包括外翼型壁，其具有在翼型的前缘和后缘之间沿弦向延伸的压力和吸力侧;形成在前翼跨肋之间的前缘冷却气室以及沿着翼型的前缘的外壁，以及在翼型内部由最前肋部分限定的冷却空气通道。一个开槽的冷却空气冲击元件设置在该跨度肋中，用于沿着该翼型的前缘沿着该外翼型壁的内表面上的通道冲击冷却空气。开槽的冷却空气冲击元件的一个实施例是沿着最前面的肋的几乎整个长度延伸的单个纵向延伸的狭槽，并且纵向狭槽优选地包括纵向间隔开的圆形端部。在翼型的另一实施例中，开槽的冷却空气冲击元件包括两个或更多个紧密间隔开的纵向延伸的狭槽，其沿着最前面的肋的几乎整个长度延伸，并且每个纵向延伸的槽优选地具有纵向间隔开的圆形端

4. 发明授权

US5183385A Turbine blade squealer tip having air cooling holes contiguous with tip interior wall surface 失效
标题翻译：涡轮叶片尖头尖端具有与尖端内壁表面相邻的空气冷却孔
公开(公告)号：US5183385A
公开(公告)日：1993-02-02
申请号：US830975
申请日：1992-02-10
申请人： Ching-Pang Lee , Harold P. Rieck, Jr. , Nicholas C. Palmer , David G. W. Fargher
发明人： Ching-Pang Lee , Harold P. Rieck, Jr. , Nicholas C. Palmer , David G. W. Fargher
IPC分类号： F01D5/20 , F01D11/10
CPC分类号： F01D11/10 , F01D5/20
摘要： A turbine blade squealer tip has a plurality of holes defined through the end cap of the blade tip portion and located contiguous with an interior surface of the squealer tip wall along at least one of the turbine blade pressure and suction sides of the tip cap for providing effective cooling air on the squealer tip wall. Each tip hole has an inner portion which communicates with the interior of the blade and an outer portion which communicates with a cavity defined by the blade end cap and the peripheral wall of the squealer tip. The cross-section of the inner hole portion is circular and the inner hole portion overall defines a right cylinder. The cross-section of the outer hole portion is rectangular and the outer hole portion overall defines a rectangular trapezoid.
摘要翻译：涡轮叶片尖叫尖端具有多个孔，其限定穿过叶片尖端部分的端盖并且沿尖端盖的涡轮叶片压力和吸力侧中的至少一个定位成与鼓风机顶端壁的内表面相邻，以提供有效的冷却空气在鸣叫器顶端壁上。每个尖端孔具有与叶片内部连通的内部部分和与由叶片端盖和鼓风机尖端的周壁限定的空腔连通的外部部分。内孔部分的横截面为圆形，内孔部分整体形成右圆柱体。外孔部分的横截面是矩形的，外孔部分总体上限定了矩形梯形。

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