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    TAPERED THERMAL COATING FOR AIRFOIL
    2.
    发明申请
    TAPERED THERMAL COATING FOR AIRFOIL 审中-公开
    用于气流的热转印热涂层

    公开(公告)号：WO2013172903A3

    公开(公告)日：2014-01-09

    申请号：PCT/US2013027232

    申请日：2013-02-22

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LEVINE JEFFREY R ,  GREGG SHAWN J

    IPC: F01D5/28 ,  F01D5/14 ,  F02C7/00 ,  F02K3/00

    CPC classification number: F01D5/188 ,  Y02T50/676

    Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a span therebetween. A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil. A relative coating thickness of the thermal coating decreases by at least thirty percent at full span in the tip section, as compared to minimum span in the root section.

    Abstract translation: 翼型件包括从前缘到后缘轴向延伸的压力和抽吸表面，并且从根部到尖端部分径向延伸，根部和末端部分限定了它们之间的跨度。 热涂层从翼型的根部朝向翼型的末端部分延伸。 与根部中的最小跨度相比，热涂层的相对涂层厚度在末端部分的全跨度处降低至少30％。

    AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT
    4.
    发明申请
    AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT 审中-公开
    具有可变行程高度的气翼

    公开(公告)号：WO2014105236A3

    公开(公告)日：2014-08-21

    申请号：PCT/US2013061857

    申请日：2013-09-26

    Applicant: UNITED TECHNOLOGIES CORP ,  RILEY SARAH ,  BOEKE MARK A ,  DEGRAY JEFFREY J ,  GREGG SHAWN J

    Inventor： RILEY SARAH ,  BOEKE MARK A ,  DEGRAY JEFFREY J ,  GREGG SHAWN J

    IPC: F02C7/12 ,  F01D5/18 ,  F01D25/12

    CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D9/02 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2250/183 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个人字形的跳闸条从一个表面延伸到冷却通道中，沿一个长度的跳闸条高度。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部提供，所述第一和第二径向延伸的腿部彼此周向地间隔开并且通过周向通道彼此连接。 一对翼型件从相同的内平台径向延伸。 跳闸带沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 跳闸条高度沿长度变化。

    6.
    发明专利
    未知

    公开(公告)号：DE602005008311D1

    公开(公告)日：2008-09-04

    申请号：DE602005008311

    申请日：2005-05-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MONGILLO JR DOMINIC J ,  LEVINE JEFFREY R ,  GREGG SHAWN J ,  PIETRASZKIEWICZ EDWARD

    IPC: F01D5/18 ,  F02C7/18

    Abstract: A rotor blade (14) is provided that includes a root (20) and a hollow airfoil (22). The hollow airfoil (22) has a cavity defined by a suction side wall (38), a pressure side wall (36), a leading edge (32), a trailing edge (34), a base (28), and a tip (30). An internal passage configuration (40) is disposed within the cavity. The configuration includes a passage (50) disposed adjacent the leading edge (32), and an axially extending passage (52) disposed adjacent the tip (30). The first passage (50) is connected to the second passage (52). The second passage (52) includes an opening disposed at the trailing edge (34) of the airfoil. A conduit (42) is disposed within the root (20) that is operable to permit airflow through the root (20) and into the leading edge passage (50), wherein the conduit (42) provides the primary path into the leading edge passage (42).

    COOLED TURBINE AIRFOIL
    8.
    发明专利
    COOLED TURBINE AIRFOIL 未知

    公开(公告)号：CA2500503A1

    公开(公告)日：2005-11-06

    申请号：CA2500503

    申请日：2005-03-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GREGG SHAWN J ,  MERCADANTE RUTHANN ,  MONGILLO DOMINIC J

    IPC: F01D20060101 ,  F01D5/00 ,  F01D5/12 ,  F01D5/14 ,  F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F02C7/00 ,  F02C7/16

    Abstract: According to the present invention, a hollow airfoil is provided that comprises a leading edge wall portion, a plurality of cavities, one or more crossover ribs, a plurality of cooling apertures, and a plurality of impingement ribs. The cavities are disposed adjacent the leading edge wall portion, between the leading edge wall portion and a first rib. The crossover ribs extend between the leading edge wall portion and the first ri b, and at least one crossover rib is disposed between a pair of the cavities. The cooling apertures are disposed in the leading edge wall portion, providing a passage through which cooling air can exit the cavities. The impingement apertures are disposed in the first rib, providing a passage through which cooling air can enter the cavities. At least one of th e impingement apertures is contiguous with one of the crossover ribs.

    Cooled rotor blade with vibration damping device
    9.
    发明专利
    Cooled rotor blade with vibration damping device 未知

    公开(公告)号：AU2004240224A1

    公开(公告)日：2005-08-18

    申请号：AU2004240224

    申请日：2004-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND C ,  PROPHETER TRACY A ,  GREGG SHAWN J ,  OTERO EDWIN

    IPC: F01D5/16 ,  F01D5/10 ,  F01D5/18 ,  F01D25/06 ,  F02C7/24

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).

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