公开(公告)号：US20040197190A1

公开(公告)日：2004-10-07

申请号：US10408293

申请日：2003-04-07

发明人： Philip Francis Stec ,  Daniel Edward Demers ,  Richard Ludwig Schmidt

IPC分类号： F01D005/08

CPC分类号： F01D5/20 ,  F01D5/141 ,  F05D2260/202

摘要： A turbine blade squealer tip has a continuous squealer tip wall extending radially outwardly from and continuously around a tip cap. A recessed tip wall portion of the tip wall is recessed inboard from a pressure side of an airfoil outer wall of an airfoil of the blade forming a tip shelf therebetween. A plurality of film cooling shelf holes are disposed through the tip shelf to an internal cooling circuit of the blade and are spaced away from a junction between the recessed tip wall portion and the tip shelf. The exemplary embodiment of the airfoil includes shelf hole centerlines of the holes passing through pierce points in the shelf. At least a majority of the shelf hole centerlines are angled in outboard directions away from and outboard of the squealer tip wall. A majority of centerlines are angled away from vertical lines passing through the pierce points at first component angles in a range between 2 degrees and 16 degrees.

摘要翻译： 涡轮叶片尖叫尖端具有从末端帽径向向外延伸并连续地延伸的连续的尖叫声尖端壁。 尖端壁的凹入的顶壁部分从叶片的翼型件的翼型件外壁的压力侧凹入，从而在其之间形成尖端架。 多个薄膜冷却搁板孔通过尖端架布置到叶片的内部冷却回路上，并且与凹入的顶端壁部分和顶端搁架之间的接合部分隔开。 翼型的示例性实施例包括穿过搁架中的穿刺点的孔的搁架孔中心线。 至少大多数货架孔中心线在外侧方向上偏离尖声尖端壁和外侧。 大多数中心线与第二组件角度在2度和16度之间的范围内穿过穿刺点的垂直线成角度。

公开(公告)号：US20040165986A1

公开(公告)日：2004-08-26

申请号：US10765729

申请日：2004-01-23

发明人： Danny S. Parker ,  John Sherwin ,  Bart Hibbs

IPC分类号： F01D001/20 ,  F03D001/04 ,  F01D001/04 ,  F01D001/00 ,  F03B001/00 ,  F04D029/58 ,  F03D011/02 ,  F01D025/24 ,  F04D019/00 ,  F03B011/02 ,  F01D009/00 ,  B63H001/14 ,  F03B003/04 ,  B63H007/02 ,  F04D003/00 ,  F01D005/08 ,  B64C011/00 ,  F01D005/18 ,  F04D029/52 ,  F25D019/00

CPC分类号： F28B1/06 ,  F04D29/164 ,  F04D29/328 ,  F04D29/384 ,  F04D29/664 ,  F24F1/38 ,  F24F1/40 ,  F24F1/50

摘要： Twisted blades for outdoor air conditioner condensers and heat pumps that improve airflow efficiency to minimize operating power requirements. The blades can run at approximately 850 rpm to produce approximately 1930 cfm of air flow using approximately 110 Watts of power from an 8-pole motor with an improved diffuser assembly. Using an OEM 6-pole null hp motor produced approximately 2610 cfm with approximately 145 Watts of power while running the blades at approximately 1100 rpm. Power savings were approximately 24% (40 to 50 Watts) over the conventional configuration with increased air flow. Embodiments of two, three, four and five blades can be equally spaced apart from one another about hubs. Additionally, a novel noise reduction configuration can include asymmetrically mounted blades such as five blades asymmetrically mounted about the hub. Additional features can include conical diffusers with or without conical center bodies were shown to further improve air moving performance by up to 21% at no increase in power. Embodiments coupled with electronically commutated motors (ECMs) showed additional reductions to condenser fan power of approximately 25%. A strip member, such as open cell foam can be applied as a liner to the interior walls of a condenser housing adjacent to the wall surface where the rotating blades sweep against. The porous edge can also be used with the trailing edge and/or tip edge of the blades. These member can both improve air flow by reducing dead air spacing between the rotating blade tips and the interior walls of the condenser housing, as well as lower undesirable noise sound emissions.

摘要翻译： 用于户外空调冷凝器和热泵的扭转叶片，可提高气流效率，以最大限度地减少操作功率需求。 刀片可以在大约850转/分钟运行，从而使用来自具有改进的扩散器组件的8极马达的大约110瓦的功率产生大约1930cfm的气流。 使用OEM 6极1/8马力的电机，以约1100转/分的速度运行叶片，产生大约2610立方英尺（约为145瓦）的功率。 与常规配置相比，节电量约为24％（40至50瓦），空气流量增加。 两个，三个，四个和五个叶片的实施例可以围绕轮毂相互间隔开。 此外，新颖的降噪配置可以包括不对称安装的叶片，例如围绕轮毂不对称地安装的五个叶片。 附加特征可以包括具有或不具有圆锥形中心体的圆锥形扩散器，以在不增加功率的情况下进一步将空气移动性能提高高达21％。 与电子换向马达（ECM）相结合的实施方案显示出约25％的冷凝器风扇功率的额外降低。 诸如开孔泡沫的带状构件可以作为衬垫施加到邻近壁面的冷凝器壳体的内壁，其中旋转叶片相对于扫掠。 多孔边缘也可以与叶片的后缘和/或尖端边缘一起使用。 这些构件可以通过减少旋转叶片尖端和冷凝器壳体的内壁之间的死气体空间以及较低的不期望的噪声声发射来改善气流。

公开(公告)号：US20040146401A1

公开(公告)日：2004-07-29

申请号：US10350635

申请日：2003-01-24

发明人： Wieslaw A. Chlus ,  Stanley J. Funk

IPC分类号： F01D005/08

CPC分类号： F01D5/147 ,  F01D5/187 ,  F01D5/20 ,  F05D2230/21 ,  F05D2230/235

摘要： A turbine blade tip plenum has means for preferentially directing or diverting cooling air from a cooling passageway network to cool areas subject to extreme heat.

摘要翻译： 涡轮叶片尖端气室具有用于优先地将冷却空气从冷却通道网络引导或转向冷却受极端热的区域的装置。

公开(公告)号：US20040042900A1

公开(公告)日：2004-03-04

申请号：US10231420

申请日：2002-08-29

发明人： James Steven Dougherty ,  Jeffrey Louis Brown ,  Domingo Resendez Barrera

IPC分类号： F01D005/08

CPC分类号： F01D5/3007 ,  F01D5/081 ,  F01D5/087 ,  F05D2250/70 ,  F05D2260/33

摘要： A gas turbine engine rotor disk assembly includes a disk having an annular hub circumscribed about a centerline. An annular web extends radially outwardly from the hub to an annular rim. A plurality of dovetail slots extend generally axially through the rim. A plurality of cooling air slots extending generally radially through the rim and are skewed circumferentially with respect to the centerline and slanted axially aftwardly with respect to a normal radius perpendicular to the centerline. In the exemplary embodiment, each cooling air slot has parallel side walls skewed circumferentially with respect to the centerline and an aft wall extending between the side walls and slanted axially aftwardly with respect to the normal radius. The side walls are skewed circumferentially about 5 degrees with respect to the centerline and the aft wall is slanted axially aftwardly about 18 degrees with respect to the normal radius.

摘要翻译： 燃气涡轮发动机转子盘组件包括具有围绕中心线限定的环形毂的盘。 环形腹板从轮毂径向向外延伸到环形边缘。 多个燕尾槽大致轴向延伸穿过轮缘。 多个冷却空气狭槽大致径向地延伸穿过边缘并且相对于中心线沿圆周方向倾斜并相对于垂直于中心线的正常半径轴向向后倾斜。 在示例性实施例中，每个冷却空气狭槽具有相对于中心线周向倾斜的平行侧壁和在侧壁之间延伸并相对于法向半径轴向向后倾斜的后壁。 侧壁相对于中心线周向地倾斜约5度，并且后壁相对于法向半径轴向向后倾斜约18度。

公开(公告)号：US20030228222A1

公开(公告)日：2003-12-11

申请号：US10162755

申请日：2002-06-06

发明人： Ronald Scott Bunker ,  Frederic Joseph Klug ,  Shyh-Chin Huang ,  Susan Marie Hyde ,  Nirm Velumylum Nirmalan

IPC分类号： F01D005/08

CPC分类号： F01D5/225 ,  B22C9/04 ,  B22C9/10 ,  F01D5/187 ,  F05D2260/22141 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

摘要： The present invention provides a cooling apparatus for cooling a turbine blade. The cooling apparatus comprises a pressure side plate comprising a plurality of pressure ribs, a suction side plate comprising a plurality of suction ribs, and a plurality of flow redirection areas. The pressure side plate is disposed over the suction side plate, where the pressure ribs are disposed at a first angle with respect to a blade span reference line and the suction ribs are disposed at a second angle with respect to the blade span reference line, to form the flow redirection areas. The present invention provides a method of fabricating the cooling apparatus for the turbine blade comprising aligning the pressure side plate and the suction side plate to form the plurality of flow redirection areas between the pressure side plate and the suction side plate.

摘要翻译： 本发明提供一种用于冷却涡轮叶片的冷却装置。 冷却装置包括压力侧板，其包括多个加压肋，包括多个吸入肋的吸力侧板和多个流动重定向区域。 压力侧板设置在吸力侧板上方，其中压力肋相对于叶片跨度基准线以第一角度设置，并且抽吸肋相对于叶片跨距参考线设置成第二角度， 形成流重定向区域。 本发明提供一种制造涡轮叶片的冷却装置的方法，包括使压力侧板和吸力侧板对准，以在压力侧板和吸力侧板之间形成多个流动重定向区域。

公开(公告)号：US20030185675A1

公开(公告)日：2003-10-02

申请号：US10063045

申请日：2002-03-14

申请人： General Electric CRD

发明人： Norman Arnold Turnquist ,  Christopher Edward Wolfe ,  Frederick George Baily ,  John Francis Nolan ,  George Ernest Reluzco

IPC分类号： F01D005/08

CPC分类号： F01D11/001 ,  F01D5/08 ,  Y02T50/676 ,  Y10T29/49316

摘要： An insert assembly is provided for a rotary machine wherein the rotary machine comprises a rotor and a casing. The rotor comprises a generally longitudinally-extending axis. The casing is generally coaxially aligned with the axis. The casing circumferentially surrounds and is radially spaced apart from the rotor. The insert assembly comprises a channel circumferentially disposed on the rotor and an insert circumferentially disposed in such channel such that the insert assembly is configured to thermally isolate frictional heat from the rotor to the insert.

摘要翻译： 提供了一种用于旋转机器的插入组件，其中旋转机器包括转子和壳体。 转子包括大致纵向延伸的轴线。 壳体通常与轴线同轴对准。 壳体周向地包围并且与转子径向间隔开。 插入组件包括周向设置在转子上的通道和沿周向设置在该通道中的插入件，使得插入组件构造成将摩擦热与转子热隔离到插入件。

公开(公告)号：US20030133798A1

公开(公告)日：2003-07-17

申请号：US10294666

申请日：2002-11-15

发明人： Geoffrey M. Dailey

IPC分类号： F01D005/08

CPC分类号： F01D5/187

摘要： An aerofoil blade or vane for a gas turbine engine comprises a body member having an inner end for mounting the blade on a shaft and an outer or tip end. A plurality of cooling passages are formed within the blade, the cooling passages comprising a plurality of inlet passages along which cooling air flows from the base towards the tip region of the blade and a plurality of return passages along which cooling air flows from the tip towards the base region of the blade. At least some of the passages are connected by a common chamber located within the tip region of the blade.

摘要翻译： 用于燃气涡轮发动机的机翼叶片或叶片包括主体构件，其具有用于将叶片安装在轴上的内端和外端或尖端。 多个冷却通道形成在叶片内，冷却通道包括多个入口通道，冷却空气从基座朝向叶片的顶端区域流过冷却空气，多个返回通道沿着冷却空气从顶端流向 叶片的基部区域。 至少一些通道通过位于叶片的尖端区域内的公共室连接​​。

公开(公告)号：US20030044278A1

公开(公告)日：2003-03-06

申请号：US10227864

申请日：2002-08-27

申请人： SNECMA MOTEURS

发明人： Patrice Eneau ,  Philippe Picot

IPC分类号： F01D005/08

CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2260/2212 ,  Y02T50/676

摘要： A gas turbine blade for an airplane engine, comprising in its central portion at least a first central cooling circuit comprising at least first and second cavities extending radially on the concave side of the blade, at least one cavity extending on the convex side of the blade, an air admission opening at a radial end of the first concave side cavity for feeding the first central cooling circuit with cooling air, a first passage putting the other radial end of the first concave side cavity into communication with an adjacent radial end of the convex side cavity, a second passage putting the other radial end of the convex side cavity into communication with an adjacent radial end of the second concave side cavity, and outlet orifices opening out into the second concave side cavity and through the concave face of the blade.

摘要翻译： 一种用于飞机发动机的燃气轮机叶片，在其中心部分包​​括至少一个第一中心冷却回路，该第一中心冷却回路包括至少第一和第二空腔，该第一和第二腔径向延伸在叶片的凹面上，至少一个空腔在叶片的凸面上延伸 在所述第一凹侧腔的径向端部的进气口，用于向所述第一中央冷却回路供给冷却空气;第一通路，其将所述第一凹侧腔的另一径向端与所述凸部的相邻径向端连通 所述第二通道将所述凸侧空腔的另一个径向端与所述第二凹侧腔的相邻径向端连通，以及通向所述第二凹侧腔的所述凹口和所述叶片的凹面的开口。

公开(公告)号：US20020154999A1

公开(公告)日：2002-10-24

申请号：US09841996

申请日：2001-04-24

申请人： Honeywell International, Inc.

发明人： Steven R. Eccles ,  Wayne G. Schindler

IPC分类号： F01D005/08

CPC分类号： B64D41/007 ,  B64D15/12 ,  F01D25/02 ,  F05D2220/34

摘要： The heating apparatus and method for the nose fairing of a rotating blade assembly has an electrical generator connected to a heating element attached to the interior of the forward end of the nose fairing. The electrical generator has a rotor with conductor windings attached to the aft end of the rotating blade assembly hub housing. The stator of the electrical generator is attached opposite the rotor on the support structure for the hub housing with stator magnets spaced from and opposite the rotor windings. When the hub housing is rotated by for example airflow through the blades of the rotating blade assembly the rotor moves relative to the stator thereby creating an induced current in the windings. This converts the rotational energy to electrical energy to power the heater to heat the nose fairing to inhibit the formation of ice thereon.

摘要翻译： 用于旋转叶片组件的鼻整流器的加热装置和方法具有连接到附接到鼻整流罩前端内部的加热元件的发电机。 发电机具有转子，导体绕组附接到旋转叶片组件毂壳体的后端。 发电机的定子与转子相对地安装在用于轮毂壳体的支撑结构上，定子磁体与转子绕组间隔开并与转子绕组相对。 当毂壳体通过例如气流旋转通过旋转叶片组件的叶片时，转子相对于定子移动，从而在绕组中产生感应电流。 这将旋转能量转换成电能来加热加热器以加热鼻整流罩以抑制其上形成冰​​。

公开(公告)号：US20020141869A1

公开(公告)日：2002-10-03

申请号：US09818312

申请日：2001-03-27

发明人： Ching-Pang Lee ,  Ramgopal Darolia ,  Robert Edward Schafrik

IPC分类号： F01D005/08

CPC分类号： F01D5/288 ,  F01D5/183 ,  F01D5/187 ,  F01D5/20 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49318

摘要： The present invention provides for cooling the squealer tip region of a high pressure turbine blade used in a gas turbine engine comprising coating the squealer tip with a metallic bond coat. Micro grooves oriented in the radial direction are fabricated into the airfoil on the interior surface of the squealer tip above and substantially perpendicular to the tip cap. A micro groove oriented in the axial direction is fabricated along the joint corner between the squealer tip side wall and the tip cap to connect and act as a plenum with all of the micro grooves oriented in the radial direction. Tip cap cooling holes are drilled through the tip cap and connected to the micro groove that ultimately forms a plenum. TBC ceramic is then deposited on both blade external surfaces and the tip cavity, forming micro channels from micro grooves as a result of self shadowing. In this manner, cooling fluid passes from a cooling fluid source through the tip cap holes and into the plenum created by the micro channel, subsequently passing into the micro channels that are oriented in the radial direction. Cooling fluid is thereby directed through the micro channels to cool the squealer, exiting in the vicinity of the tip. Since the TBC is porous, some of the cooling fluid will also flow through the TBC to provide transpiration cooling. The present invention further comprises both the cooled blade and squealer tip region formed by the foregoing methods and the blade and squealer tip with the micro channels for cooling the squealer tip.

摘要翻译： 本发明提供了用于冷却在燃气涡轮发动机中使用的高压涡轮机叶片的鸣响器尖端区域，其包括用金属粘结涂层涂覆尖叫尖端。 在径向方向上定向的微槽在尖端顶部的内表面上被制造成位于尖端顶部的内表面上且基本上垂直于顶盖。 沿着轴向定向的微槽沿着尖叫尖端侧壁和尖端盖之间的接合角制造，以连接并充当所有微槽沿径向定向的集气室。 顶盖冷却孔穿过尖端盖并连接到最终形成增压室的微槽。 然后将TBC陶瓷沉积在两个叶片外表面和尖端腔上，由于自身阴影而从微槽形成微通道。 以这种方式，冷却流体从冷却流体源通过顶盖孔并进入由微通道产生的增压室，随后进入沿径向定向的微通道。 因此，冷却流体被引导通过微通道，以冷却在尖端附近离开的鸣叫器。 由于TBC是多孔的，一些冷却流体也将流经TBC以提供蒸发冷却。 本发明还包括通过上述方法形成的冷却刀片和鸣响器尖端区域以及具有用于冷却鸣叫器尖端的微通道的刀片和尖叫尖端。