专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US5984630A Reduced windage high pressure turbine forward outer seal 失效
标题翻译：降低风挡高压汽轮机正向外密封
公开(公告)号：US5984630A
公开(公告)日：1999-11-16
申请号：US997833
申请日：1997-12-24
申请人： David A. Di Salle , Robert Proctor , Edward P. Brill , Steven A. Ross , Robert J. Albers , John C. Brauer , Gulcharan S. Brainch , Dean T. Lenahan
发明人： David A. Di Salle , Robert Proctor , Edward P. Brill , Steven A. Ross , Robert J. Albers , John C. Brauer , Gulcharan S. Brainch , Dean T. Lenahan
IPC分类号： F01D5/08 , F01D11/02 , F01D11/04 , F02C7/18 , F03B11/00
CPC分类号： F01D11/02 , F01D11/04
摘要： A blocker and swirl inducer hole configuration for use in connection with a high pressure turbine is described. In one embodiment, the blocker holes are oriented to a 45-degree tangential angle with respect to the direction of rotation of the seal, which results in pre-swirling the air before being injected into the swirl cavity. In addition, the number of blocker holes is reduced by as much as 50% of the number of blocker holes used in the known CFM56 turbine. Further, rather than injecting the air into the first swirl cavity as is known, the air is injected into a second swirl cavity. The combined effect of orienting the holes to the 45-degree tangential angle with respect to the direction of rotation of the seal, locating the holes to open into the second swirl cavity, and reducing the flow area by about 50%, results in an increase in blocker hole pressure ratio. Increasing the blocker hole pressure ratio results in a higher hole exit velocity which maximizes the cavity inlet swirl. The blocker holes therefore not only provide back-pressure, but also function as swirl-inducers. By inducing swirl into the air injected into the second swirl cavity, better turbine disk rim cooling effectiveness is provided. This result facilitates maintaining reasonable metal temperatures at increasingly severe cycle conditions without the normally expected engine performance penalties.
摘要翻译：描述了与高压涡轮机相关联使用的阻塞器和涡流诱导器孔构造。在一个实施例中，阻挡孔相对于密封件的旋转方向被定向成45度的切向角，这导致在注入到涡流腔内之前预先旋转空气。此外，阻塞孔的数量减少了已知CFM56涡轮机中使用的阻塞孔数量的多达50％。此外，如已知的那样，不是将空气注入到第一涡流腔中，所以空气被注入到第二涡流腔中。相对于密封件的旋转方向将孔定向到45度切向角的组合效果，将孔定位到第二涡流腔中，并将流动面积减少约50％，导致增加阻塞孔压力比。增加阻塞孔压力比导致更高的孔出口速度，这使空腔入口涡流最大化。因此，阻挡孔不仅提供背压，而且还起到旋流诱发器的作用。通过在注入到第二涡流腔中的空气中引起漩涡，提供更好的涡轮盘边缘冷却效果。该结果有助于在越来越严格的循环条件下保持合理的金属温度，而不会发生通常预期的发动机性能

2. 发明授权

US5735671A Shielded turbine rotor 失效
标题翻译：屏蔽涡轮转子
公开(公告)号：US5735671A
公开(公告)日：1998-04-07
申请号：US759093
申请日：1996-11-29
申请人： John C. Brauer , David A. Di Salle , Edward P. Brill , Robert J. Albers , Dean T. Lenahan
发明人： John C. Brauer , David A. Di Salle , Edward P. Brill , Robert J. Albers , Dean T. Lenahan
IPC分类号： F01D5/08 , F01D5/28 , F01D5/30 , F01D11/00 , F01D25/00
CPC分类号： F01D11/008 , F01D5/081 , F01D5/288 , F05D2230/90 , F05D2260/231 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： A turbine rotor includes a rotor disk having a plurality of dovetail slots defining therebetween respective disk posts. Each post has a top land and a plurality of tangs spaced radially therebelow inside adjacent ones of the slots. A plurality of turbine blades each having a dovetail are mounted in respective ones of the dovetail slots for radially retaining the blades. A platform is joined integrally with the dovetail and extends circumferentially to adjoin adjacent ones of the platforms to define a radially inner flowpath. An airfoil extends integrally from the platform for extracting energy from combustion gases flowable thereover. A thermal barrier coating is fixedly bonded to each of the disk post top lands for providing thermal insulation between the platforms and the disk posts for reducing disk post temperature.
摘要翻译：涡轮转子包括具有多个燕尾槽的转子盘，所述燕尾槽在其间限定各自的盘柱。每个柱具有顶部区域和在其中相邻的狭槽内部沿径向放置的多个柄脚。每个具有燕尾榫的多个涡轮叶片安装在各个燕尾槽中，用于径向保持叶片。平台与燕尾榫整体连接并且周向地延伸以邻接相邻的平台以限定径向内部的流动路径。机翼从平台一体地延伸，用于从其中可流动的燃烧气体提取能量。隔热涂层固定地粘合到每个盘柱顶部焊盘上，以在平台和盘柱之间提供热绝缘，以减少磁盘后端温度。

3. 发明授权

US4807433A Turbine cooling air modulation 失效
标题翻译：涡轮冷却空气调节
公开(公告)号：US4807433A
公开(公告)日：1989-02-28
申请号：US143494
申请日：1988-01-13
申请人： Harvey M. Maclin , Dean T. Lenahan , Tuley, Eugene N.
发明人： Harvey M. Maclin , Dean T. Lenahan , Tuley, Eugene N.
IPC分类号： F01D5/08 , F02C7/18 , F02C7/12
CPC分类号： F01D5/081 , F02C7/18 , Y02T50/673 , Y02T50/676
摘要： Disclosed are a cooling air modulation apparatus for and method of operation for a gas turbine engine which are effective for increasing engine operating efficiency. According to one embodiment of the invention, the apparatus includes a first inducer means effective for channeling a first portion of cooling air to a rotor component during both first and second modes of operation of the engine. A second inducer means is also provided and is effective for channeling a second portion of the cooling air to the rotor component. Valve means are provided for selectively modulating the amount of cooling air flowing through the second inducer for preventing flow therethrough during the first mode of operation and for allowing unrestricted flow therethrough during the second mode of operation.
摘要翻译：公开了一种用于燃气涡轮发动机的冷却空气调节装置和操作方法，其对于提高发动机运转效率是有效的。根据本发明的一个实施例，该装置包括在发动机的第一和第二操作模式期间有效地将冷却空气的第一部分引导到转子部件的第一诱导装置。还提供了第二诱导装置，并且有效地将冷却空气的第二部分引导到转子部件。提供阀装置，用于选择性地调节流过第二导流器的冷却空气的量，以防止在第一操作模式期间流过其中，并且允许在第二操作模式期间不受限制地流过。

4. 发明授权

US5555721A Gas turbine engine cooling supply circuit 失效
标题翻译：燃气轮机发动机冷却供电电路
公开(公告)号：US5555721A
公开(公告)日：1996-09-17
申请号：US313951
申请日：1994-09-28
申请人： John J. Bourneuf , Dean T. Lenahan , Daniel E. Demers , Larry W. Plemmons
发明人： John J. Bourneuf , Dean T. Lenahan , Daniel E. Demers , Larry W. Plemmons
IPC分类号： F02C7/18 , F02C7/12
CPC分类号： F02C7/18
摘要： A turbine cooling supply circuit for a gas turbine engine is disclosed in which the flow of coolant through the engine is directed to minimize temperature rise prior to discharge into the turbine. Bleed air from an impeller stage of a compressor is channeled along a backwall thereof into a cavity disposed radially inwardly of a combustor casing. The cavity is divided by a lightweight tubular member having a circumferentially uniform contour into a non-flow zone proximate the casing and a flow zone proximate a rotor. Maintenance of a high tangential flow component in the bleed flow in the flow zone facilitates discharge of the flow through apertures in a rotor into a bore portion thereof, minimizing work input and temperature rise of the coolant. Further, the coolant is isolated from the hot casing wall and nonuniform structures disposed thereon, thereby reducing heat flux and temperature rise associated with aerodynamic drag caused by increased surface area, nonuniform interruptions in the stationary surface or any combination thereof. Features are incorporated in the tubular member to provide margin against buckling.
摘要翻译：公开了一种用于燃气涡轮发动机的涡轮冷却供应回路，其中通过发动机的冷却剂流被引导以在排放到涡轮机之前使温度上升最小化。来自压缩机的叶轮级的排出空气沿其后壁被引导到设置在燃烧器壳体的径向内侧的空腔中。空腔由具有周向均匀轮廓的轻质管状构件分隔成靠近壳体的非流动区域和靠近转子的流动区域。在流动区域中的排出流中维持高切向流动分量有助于将流过转子中的孔的流体排放到其孔部分中，从而最小化冷却剂的工作输入和温度上升。此外，冷却剂与热套管壁和设置在其上的不均匀结构隔离，从而减少与由增加的表面积，固定表面的不均匀中断或其任何组合引起的空气动力学阻力相关联的热通量和温度升高。特征被并入管状构件以提供抵抗屈曲的边缘。

5. 发明授权

US5281085A Clearance control system for separately expanding or contracting individual portions of an annular shroud 失效
标题翻译：用于单独扩展或收缩环形护罩的各个部分的间隙控制系统
公开(公告)号：US5281085A
公开(公告)日：1994-01-25
申请号：US631512
申请日：1990-12-21
申请人： Dean T. Lenahan , L. D. Shotts , Bandadi S. Shetty , Jeffrey Glover
发明人： Dean T. Lenahan , L. D. Shotts , Bandadi S. Shetty , Jeffrey Glover
IPC分类号： F01D11/08 , F01D11/10 , F01D11/24 , F02C7/28 , F01D9/00
CPC分类号： F01D11/24
摘要： Improved operation can be achieved from an enhanced gas turbine engine having a segmented annular shroud which radially expands and contracts to match the expansion and contraction of engine rotor blades. The segmented annular shroud is supported by a structure which includes an annular ring having two radially outwardly extending flanges, and forward and aft annular segmented brackets which attach the segmented shroud to the forward and aft side of the ring respectively. In a preferred embodiment of the invention, two circumferentially extending separate and distinct air impingement manifolds surrounds each of the outwardly extending flanges. Each manifold is provided with a valve for controlling the amount and temperature of the airflow entering each manifold. The air from each manifold then impinges upon each of the outwardly extending flanges, thereby controlling the radial movement of the corresponding shroud segments and the associated clearances with the rotor blade tips. The use of separate and distinct manifolds and the corresponding values which regulate the amount and temperature of airflow to each manifold allows individual shroud portions to be separately expanded or contracted.
摘要翻译：可以从具有分段环形护罩的增强型燃气涡轮发动机实现改进的操作，径向膨胀和收缩以匹配发动机转子叶片的膨胀和收缩。分段的环形护罩由包括具有两个径向向外延伸的凸缘的环形环以及将分段的护罩分别附接到环的前侧和后侧的前部和后部环形分段支架的结构支撑。在本发明的一个优选实施例中，两个周向延伸的独立和不同的空气冲击歧管围绕每个向外延伸的凸缘。每个歧管设置有用于控制进入每个歧管的气流的量和温度的阀。来自每个歧管的空气然后撞击在每个向外延伸的凸缘上，由此控制相应的护罩段的径向运动和与转子叶片尖端相关联的间隙。使用单独的和不同的歧管以及调节每个歧管的气流的量和温度的相应值允许单独的护罩部分分开地膨胀或收缩。

6. 发明授权

US4882902A Turbine cooling air transferring apparatus 失效
标题翻译：涡轮冷却空气传送装置
公开(公告)号：US4882902A
公开(公告)日：1989-11-28
申请号：US168522
申请日：1988-03-07
申请人： James R. Reigel , Robert J. Corsmeier , James H. Bertke , Dean T. Lenahan
发明人： James R. Reigel , Robert J. Corsmeier , James H. Bertke , Dean T. Lenahan
IPC分类号： F01D5/08
CPC分类号： F01D5/082
摘要： An improved system provides cooling air to the turbine blades of a gas turbine engine. The improved system includes the combination of an inducer to receive pressurized cooling air from the compressor and then to direct this cooling air in a substantially tangential direction to a radial flow impeller which includes an air seal. Cooling air is directed to the turbine blades which are mounted on the rim of the rotating first turbine disk. In a preferred embodiment of the invention, a second portion of the cooling air from the inducer is conveyed through a deswirler to introduce the cooling air into a circumferential channel surrounding the rotor shaft. The cooling air is then directed to a second inducer means which is mounted on the higher pressure turbine disk. The cooling air is then directed to a second annular impeller mounted on the lower pressure turbine disk to convey this portion of cooling air to the lower pressure turbine rotor blades.
摘要翻译：改进的系统向燃气涡轮发动机的涡轮机叶片提供冷却空气。改进的系统包括诱导器的组合，以从压缩机接收加压的冷却空气，然后将该冷却空气沿包括空气密封件的径向流动叶轮的大致切线方向引导。冷却空气被引导到安装在旋转的第一涡轮盘的边缘上的涡轮机叶片。在本发明的一个优选实施例中，来自导流器的冷却空气的第二部分被输送通过冷却器，以将冷却空气引入围绕转子轴的周向通道。然后冷却空气被引导到安装在高压涡轮盘上的第二导流装置。冷却空气然后被引导到安装在低压涡轮盘上的第二环形叶轮，以将这部分冷却空气传送到低压涡轮转子叶片。

7. 发明授权

US4526509A Rub tolerant shroud 失效
标题翻译：耐磨护罩
公开(公告)号：US4526509A
公开(公告)日：1985-07-02
申请号：US526857
申请日：1983-08-26
申请人： Charles H. Gay, Jr. , Dean T. Lenahan
发明人： Charles H. Gay, Jr. , Dean T. Lenahan
IPC分类号： F01D11/08 , F01D11/12 , F16J15/32
CPC分类号： F16J15/3292 , F01D11/12 , F01D11/127 , Y10S277/939
摘要： A seal structure between first and second relatively moveable members for preventing gas flow in the space between the members and transverse to their general direction of motion is disclosed. The seal structure includes a plurality of substantially parallel strips within 30.degree. of normal to the radial plane generally containing these first and second relatively moveable members. The strips are thin and closely spaced and arranged so that one strip edge is attached to the first member and another edge is free to resiliently deflect when in rubbing contact with the second member.
摘要翻译：公开了一种用于防止气体在构件之间的空间中流动并横向于其大致运动方向的第一和第二相对可移动构件之间的密封结构。密封结构包括在通常包含这些第一和第二相对可移动构件的径向平面的30°内的多个基本上平行的条。条带是薄且紧密间隔并布置成使得一个条边缘附接到第一构件，而另一个边缘在与第二构件摩擦接触时自由地弹性偏转。

8. 发明授权

US4137705A Cooling air cooler for a gas turbine engine 失效
标题翻译：燃气轮机的冷却空气冷却器
公开(公告)号：US4137705A
公开(公告)日：1979-02-06
申请号：US818361
申请日：1977-07-25
申请人： Richard H. Andersen , Robert J. Corsmeier , James P. Rauf , Dean T. Lenahan
发明人： Richard H. Andersen , Robert J. Corsmeier , James P. Rauf , Dean T. Lenahan
IPC分类号： F02C7/141 , F02C7/14 , F02C7/16 , F02C7/18 , F28D7/16 , F28D9/00 , F28F1/16 , F28F13/06
CPC分类号： F28D9/0025 , F02C7/14 , F02C7/185 , F28D7/1684 , F28F1/16 , F28F13/06 , Y02T50/675
摘要： A gas turbine engine having a compressor and an air-cooled turbine is provided with a cooling system for decreasing the temperature of the turbine cooling air. A compact heat exchanger, rotatable with the compressor, receives a portion of the pressurized air which is bled from the compressor. Relatively cool engine lubrication oil is pumped through the heat exchanger into heat exchange relationship with the pressurized air, thereby cooling the air and heating the lubrication oil. The cooled air is then routed to and circulated through the turbine blades to provide improved internal cooling thereof. The heated lubrication oil is collected from the heat exchanger and routed to a second heat exchanger wherein it is placed in heat exchange relationship with engine fuel to recover the heat extracted from the compressor bleed air and to return the heat to the engine operating cycle. The cooling system is designed to contain the lubricant in the unlikely event of a leak developing in the heat exchanger. Incorporation of the heat exchanger of the present invention into a gas turbine engine permits a reduction in the quantity of compressor air required for turbine rotor blade cooling and, thus, provides an improvement in engine performance.
摘要翻译：具有压缩机和空气冷却涡轮机的燃气涡轮发动机设置有用于降低涡轮机冷却空气的温度的冷却系统。与压缩机一起旋转的紧凑型热交换器接收从压缩机排出的一部分加压空气。相对冷却的发动机润滑油通过热交换器被泵送到与加压空气的热交换关系，从而冷却空气并加热润滑油。然后冷却的空气被引导到涡轮机叶片并循环通过涡轮机叶片，以提供改进的内部冷却。加热的润滑油从热交换器收集并且被引导到第二热交换器，其中它与发动机燃料放置在热交换关系中，以回收从压缩机排气中提取的热量并将热量返回到发动机工作循环。冷却系统设计成在热交换器中不大可能发生泄漏的情况下容纳润滑剂。将本发明的热交换器并入燃气涡轮发动机允许减少涡轮转子叶片冷却所需的压缩机空气量，从而提供发动机性能的改进。

9. 发明授权

US5224822A Integral turbine nozzle support and discourager seal 失效
标题翻译：整体式涡轮喷嘴支架和气垫密封
公开(公告)号：US5224822A
公开(公告)日：1993-07-06
申请号：US699061
申请日：1991-05-13
申请人： Dean T. Lenahan , Charles F. Riedmiller , Andrew P. Elovic
发明人： Dean T. Lenahan , Charles F. Riedmiller , Andrew P. Elovic
IPC分类号： C23C4/00 , C23C30/00 , F01D5/00 , F01D5/28 , F01D9/02 , F01D11/00
CPC分类号： F01D11/005 , C23C30/00 , C23C4/01 , F01D5/00 , F01D5/288 , F01D9/02 , Y02T50/67
摘要： The invention comprises the use of a thermal barrier coating on a member of a gas turbine engine component with one surface of the member exposed to high temperature but not exposed to high velocity gases, as an insulating material to slow the heat transfer to the substrate of the component member and allow thermal gradients within acceptable material limits between the thermal barrier coated member and the remainder of the component. In a particular application, the use of a thermal barrier coating enables making a high pressure turbine nozzle integral with a discourager seal lip, eliminating fasteners protruding into the rotor/stator cavity and split lines between segments of the prior art that allowed high temperature gas ingestion further into the cavity and caused windage losses.
摘要翻译：本发明包括在燃气涡轮发动机部件的部件上使用热障涂层，其中该部件的一个表面暴露于高温但不暴露于高速气体作为绝缘材料，以减慢对基板的热传递并且允许热梯度在热障涂层构件和部件的其余部分之间的可接受的材料限度内。在特定应用中，使用热障涂层可以使高压涡轮喷嘴与气垫密封唇一体成型，消除了突出到转子/定子腔中的紧固件，并且在现有技术中允许高温气体摄入进一步进入腔体并造成风阻损失。

10. 发明授权

US4416111A Air modulation apparatus 失效
标题翻译：空气调节装置
公开(公告)号：US4416111A
公开(公告)日：1983-11-22
申请号：US238257
申请日：1981-02-25
申请人： Dean T. Lenahan , Robert J. Corsmeier , Albert P. Sterman, deceased
发明人： Dean T. Lenahan , Robert J. Corsmeier , Albert P. Sterman, deceased
IPC分类号： F02C7/18
CPC分类号： F02C7/18
摘要： An air modulation apparatus, such as for use in modulating cooling air to the turbine section of a gas turbine engine. The apparatus includes valve means disposed around an annular conduit, such as a nozzle, in the engine cooling air circuit. The valve means, when in a closed position, blocks a portion of the conduit, and thus reduces the amount and increases the velocity of cooling air flowing through the nozzle. The apparatus also includes actuation means, which can operate in response to predetermined engine conditions, for enabling opening and closing of the valve means.
摘要翻译：一种空气调节装置，例如用于调节到燃气涡轮发动机的涡轮部分的冷却空气。该装置包括围绕发动机冷却空气回路中的诸如喷嘴的环形导管设置的阀装置。当处于关闭位置时，该阀意味着堵塞导管的一部分，从而减少了流过喷嘴的冷却空气的量并增加了其速度。该装置还包括致动装置，其可以响应于预定的发动机状态而操作，以使得能够打开和关闭阀装置。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式