公开(公告)号：WO2014052323A1

公开(公告)日：2014-04-03

申请号：PCT/US2013/061432

申请日：2013-09-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BALES, Daniel A. ,  KLUCHA, Agnes ,  DOLANSKY, Gregory M.

IPC: F02C7/12 ,  F01D5/18 ,  F02K3/00

CPC classification number: F01D5/187 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B22F2998/10 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/00 ,  B33Y70/00 ,  B33Y80/00 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2230/42 ,  F05D2230/90 ,  F05D2300/606 ,  Y02P10/295 ,  B22F3/15 ,  B22F2003/248 ,  C23C28/00

Abstract: A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer.

Abstract translation: 具有内部冷却通道的燃气轮机翼型通过附加制造形成。 超级合金粉末的层通过能量束熔合，使用二维图案，提供在其中形成通道的未熔化区域。 使用足够的二维图案加入并熔化粉末层，以形成具有所需图案的内部冷却通道的整个翼型。 在翼型形成完成之后，可以进行热等静压，定向重结晶，粘结涂层，并覆盖有热障层。

公开(公告)号：WO2014099067A3

公开(公告)日：2014-06-26

申请号：PCT/US2013/061571

申请日：2013-09-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BALES, Daniel A. ,  WATSON, Thomas J.

IPC: F04D29/38

Abstract: A fan blade includes first and second titanium portions that are secured to one another with an aluminum alloy braze. A method of manufacturing a fan blade includes providing first and second titanium portions, applying an aluminum alloy braze to at least one of the first and second titanium portions, and heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour.

公开(公告)号：WO2014052320A1

公开(公告)日：2014-04-03

申请号：PCT/US2013/061427

申请日：2013-09-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： BALES, Daniel A. ,  JENKEL, Steve D. ,  FISK, Benjamin T.

IPC: F01D5/30 ,  F01D5/28 ,  F02C7/00

CPC classification number: F01D5/18 ,  F01D5/28 ,  F01D5/30 ,  F01D5/34 ,  F02C7/00 ,  F05D2230/40 ,  Y10T29/49339

Abstract: Uber-cooled multi-alloy integrally bladed rotors (IBR) are made having blades with internal cooling passages with a cavity in the root portion attached to a disk having a protrusion on the periphery of the disk. The blades are put on the protrusion and the blade and disk are forced together, followed by locally heating the blade cavity/disk protrusion to a temperature between the blade and disk material softening temperatures, causing the protrusion to deform against the blade cavity, and holding them in place until bonding occurs. Subsequent to bonding the portion of the blade that defines the cavity is removed.

Abstract translation: Uber冷却的多合金整体叶片式转子（IBR）制成具有内部冷却通道的叶片，其中根部部分中的腔体附接到具有在盘周边上的突起的盘。 将刀片放在突起上，将刀片和盘片压在一起，随后将刀片腔/盘突起局部加热到刀片与盘材料软化温度之间的温度，导致突起相对于刀片腔变形，并保持 它们到位，直到粘合发生。 在粘合之后，去除限定空腔的叶片的部分。

公开(公告)号：WO2013115949A2

公开(公告)日：2013-08-08

申请号：PCT/US2013/020969

申请日：2013-01-10

Applicant: UNITED TECHNOLOGIES CORPORATION ,  WATSON, Thomas J. ,  BALES, Daniel A.

Inventor： WATSON, Thomas J. ,  BALES, Daniel A.

IPC: F01D5/14 ,  B21D53/88

CPC classification number: F04D29/388 ,  B21D53/88 ,  B23K1/00 ,  B23K1/0018 ,  B23K1/19 ,  B23K3/08 ,  B23K35/002 ,  B23K35/0233 ,  B23K35/282 ,  B23K35/284 ,  B23K2201/001 ,  C22C21/10 ,  F01D5/14 ,  F01D5/28 ,  F01D9/041 ,  F02C3/06 ,  F04D19/002 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/32 ,  F05D2230/237 ,  F05D2240/12 ,  F05D2300/1616 ,  F05D2300/173 ,  Y10T29/49622

Abstract: A method of making an aluminum airfoil includes brazing a first airfoil piece and a second airfoil piece together using a braze material that includes an element selected from magnesium and zinc, to form a braze joint between the first airfoil piece and the second airfoil piece. At least one of the first airfoil piece or the second airfoil piece has an aluminum alloy composition that includes greater than 0.8% by weight of zinc.

Abstract translation: 制造铝型材的方法包括使用包括选自镁和锌的元素的钎焊材料将第一翼型件和第二翼型件钎焊在一起，以在第一翼型件和第二翼型件之间形成钎焊接头。 第一翼型件或第二翼型件中的至少一个具有包括大于0.8重量％的锌的铝合金组合物。

公开(公告)号：EP3680060A1

公开(公告)日：2020-07-15

申请号：EP20151545.9

申请日：2020-01-13

Applicant: United Technologies Corporation

Inventor： BALES, Daniel A. ,  DEMICHAEL, Thomas

IPC: B23P15/04 ,  B21D26/055 ,  B21D53/78 ,  F01D5/14 ,  F01D5/18

Abstract: A method of forming a gas turbine engine component (160) includes attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to define pressure and suction sides of an airfoil (161), and moving the airfoil (161) in a forming line (178) including a plurality of stations (180). The plurality of stations (180) include a set of heating stations (180B), a deforming station (180C) and a set of cool down stations (180D). The moving step includes positioning the airfoil (161) in the set of heating stations (180B) to progressively increase a temperature of the airfoil (161), then positioning the airfoil (161) in the deforming station (180C) including causing the airfoil (161) to deform between first and second dies (188, 189), and then positioning the airfoil (161) in the set of cool down stations (180D) to progressively decrease the temperature of the airfoil (161).

公开(公告)号：EP3187284B1

公开(公告)日：2020-02-05

申请号：EP16206426.5

申请日：2016-12-22

Applicant: United Technologies Corporation

Inventor： BALES, Daniel A. ,  WATSON, Thomas J.

IPC: B22F3/08 ,  B22F3/087 ,  B22F5/04 ,  F01D5/00

公开(公告)号：EP2809884B1

公开(公告)日：2019-11-13

申请号：EP13743677.0

申请日：2013-01-10

Applicant: United Technologies Corporation

Inventor： WATSON, Thomas J. ,  BALES, Daniel A.

IPC: B23K1/00 ,  B23K1/19 ,  B23K3/08 ,  B23K35/28 ,  B23K35/00 ,  B23K35/02 ,  C22C21/10 ,  F01D5/28 ,  F01D9/04 ,  F04D19/00 ,  F02C3/06 ,  F04D29/02 ,  F04D29/32 ,  F04D29/38 ,  B23K101/00

公开(公告)号：EP2900964A1

公开(公告)日：2015-08-05

申请号：EP13842446.0

申请日：2013-09-24

Applicant: United Technologies Corporation

Inventor： BALES, Daniel A. ,  KLUCHA, Agnes ,  DOLANSKY, Gregory M.

IPC: F02C7/12 ,  F01D5/18 ,  F02K3/00

CPC classification number: F01D5/187 ,  B22F3/1055 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B22F2998/10 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/00 ,  B33Y70/00 ,  B33Y80/00 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2230/42 ,  F05D2230/90 ,  F05D2300/606 ,  Y02P10/295 ,  B22F3/15 ,  B22F2003/248 ,  C23C28/00

Abstract: A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer.

Abstract translation: 具有内部冷却通道的燃气轮机翼型通过添加剂制造形成。 超级合金粉末的层由能量束熔合，使用二维图案，提供在其中形成通道的未熔化区域。 使用足够的二维图案添加和熔化粉末层，以形成具有所需图案的内部冷却通道的整个翼型。 在形成翼型之后，可以进行热等静压，定向重结晶，粘结涂层，并覆盖有热障层。

公开(公告)号：EP3385026B1

公开(公告)日：2020-09-23

申请号：EP18161954.5

申请日：2018-03-15

Applicant: United Technologies Corporation

Inventor： VARGAS, Chris ,  JENKEL, Steven D. ,  BALES, Daniel A.

IPC: B23K20/12 ,  B21J15/02 ,  B23K20/233 ,  F01D5/14 ,  B23K101/00 ,  B23K103/18 ,  B23K103/10 ,  B23K103/14

公开(公告)号：EP3513903A1

公开(公告)日：2019-07-24

申请号：EP19152097.2

申请日：2019-01-16

Applicant: United Technologies Corporation

Inventor： HANSEN, James O. ,  GRAVES, William R ,  WEISSE, Michael A. ,  HERTEL, Christopher J. ,  BALES, Daniel A.

IPC: B23P15/04 ,  F01D5/16 ,  F01D5/28

Abstract: A fan of a gas turbine engine includes a plurality of fan blades (70) secured to a rotor, each of the plurality of fan blades having an airfoil (72) secured to the rotor at one end, wherein the airfoil comprises pockets (90) filled with an elastomeric composite.