公开(公告)号：EP2800876A4

公开(公告)日：2015-12-02

申请号：EP13733733

申请日：2013-01-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  WEISSE MICHAEL A

IPC: F01D5/18

CPC classification number: B23K20/1265 ,  B23K2201/001 ,  F01D5/147 ,  F01D5/28 ,  F05D2220/36 ,  F05D2230/232 ,  F05D2300/121

公开(公告)号：EP2809953A4

公开(公告)日：2015-11-25

申请号：EP13743282

申请日：2013-01-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL ,  ACKERMANN WILLIAM K ,  KUPRATIS DANIEL BERNARD

IPC: F04D29/04 ,  F02C7/06 ,  F02C7/20 ,  F02K3/06 ,  F04D29/056

CPC classification number: F04D29/056 ,  F02C7/06 ,  F02C7/20 ,  F02K3/06

公开(公告)号：EP2841739A4

公开(公告)日：2015-11-18

申请号：EP13823513

申请日：2013-04-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  SCHWARZ FREDERICK M

IPC: F02C3/107 ,  F01D1/26 ,  F02C3/067 ,  F02K3/072

CPC classification number: F02C3/107 ,  F01D1/10 ,  F01D1/26 ,  F01D5/06 ,  F01D15/12 ,  F02C3/06 ,  F02C3/067 ,  F02C3/073 ,  F05D2220/32 ,  F05D2250/44 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second direction.

Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮驱动风扇通过齿轮减速。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 所述高速滑阀和所述风扇驱动涡轮机构造成沿相同的第一方向旋转。 中间速度卷轴以相对的第二方向旋转。

公开(公告)号：EP2834494A4

公开(公告)日：2015-11-11

申请号：EP13831207

申请日：2013-03-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C7/36 ,  F02C3/107 ,  F02K3/06

CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F05D2260/40311

Abstract: A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

Abstract translation: 燃气涡轮发动机涡轮机具有高压涡轮机，该高压涡轮机被构造为以围绕中心轴线的第一方向的高压压缩机作为高压压缩机旋转，以及构造成作为低压阀芯的低压压缩机旋转的低压涡轮机 关于中心轴的第一个方向。 功率密度大于或等于约1.5且小于或等于约5.5lbf /立方英寸。 风扇通过变速机构连接到低压阀芯，并沿第一方向旋转。

公开(公告)号：EP2776318A4

公开(公告)日：2014-11-26

申请号：EP12863186

申请日：2012-12-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  MERRY BRIAN D ,  DYE CHRISTOPHER M ,  JOHNSON STEVEN B ,  SCHWARZ FREDERICK M

IPC: B64D27/10 ,  F02K3/06

CPC classification number: B64D27/26 ,  B64D2027/264 ,  B64D2027/266 ,  F01D25/162 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06 ,  F02K3/075 ,  F05D2260/4031 ,  F05D2260/40311

公开(公告)号：EP3063374A4

公开(公告)日：2017-08-09

申请号：EP14857657

申请日：2014-10-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F01D5/14 ,  F01D17/16 ,  F04D29/38 ,  F04D29/46 ,  F04D29/56 ,  F04D29/68

CPC classification number: F01D5/147 ,  F01D5/145 ,  F01D5/146 ,  F01D9/041 ,  F01D17/14 ,  F01D17/162 ,  F04D29/563 ,  F04D29/682 ,  F04D29/684 ,  F05D2220/32 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2240/35 ,  F05D2260/60 ,  Y02T50/673

Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.

Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括翼型，所述翼型包括在前缘和后缘连接在一起的压力侧表面和吸力侧表面以及流动 在压力侧表面和吸力侧表面之间延伸的通道。

公开(公告)号：EP3071824A4

公开(公告)日：2017-07-26

申请号：EP14864738

申请日：2014-09-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  SHERIDAN WILLIAM G

IPC: F02K3/02 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06

CPC classification number: F02C7/06 ,  F01D5/02 ,  F01D5/06 ,  F01D9/06 ,  F01D17/105 ,  F02C3/04 ,  F02C3/06 ,  F02C3/10 ,  F02C3/107 ,  F02C7/28 ,  F02C7/36 ,  F02C9/18 ,  F02K1/06 ,  F02K1/09 ,  F02K3/04 ,  F02K3/06 ,  F04D29/321 ,  F04D29/325 ,  F04D29/38 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/52 ,  F05D2240/54 ,  F05D2240/60 ,  F05D2260/40311 ,  F16H1/28

Abstract: A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.

Abstract translation: 根据本公开的示例性方面的涡轮风扇发动机除了别的之外还包括具有多个叶片的风扇，并且变速器构造成驱动风扇。 风扇叶片具有尖峰半径RT。 风扇叶片在流道的内侧边界处具有内侧前缘半径RH。 RH与RT的比率小于约0.40。

公开(公告)号：EP3052790A4

公开(公告)日：2017-05-24

申请号：EP14861230

申请日：2014-08-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M

IPC: F02C7/36

CPC classification number: F02C7/36 ,  F02C3/06 ,  F02K3/06 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/606

公开(公告)号：EP3084135A4

公开(公告)日：2016-12-21

申请号：EP14873099

申请日：2014-12-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  WEISSE MICHAEL A

IPC: F01D5/14 ,  B23K20/12 ,  B23K101/00 ,  F01D5/18 ,  F04D29/32 ,  F04D29/38

CPC classification number: F04D29/388 ,  B23K20/122 ,  B23K2201/001 ,  F01D5/147 ,  F01D5/18 ,  F02C3/04 ,  F04D29/325 ,  F05D2220/36 ,  F05D2230/239 ,  Y02T50/671 ,  Y02T50/676

Abstract: An airfoil for a turbine engine includes an airfoil body with a cover mounting support, a first cover, and a second cover. The airfoil body includes a solid perimeter portion surrounding a recess formed into at least one of a suction side and a pressure side of the airfoil body, while the cover mounting support extends through the recess. The first cover can be engaged with a first edge of the recess and joined to a first portion of the cover mounting support by a first stir weld. The second cover can be engaged with a second edge of the recess, and joined to a second portion of the cover mounting support by a second stir weld.

公开(公告)号：EP2971608A4

公开(公告)日：2016-11-30

申请号：EP13878963

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  BRILLIANT LISA I

IPC: F01D25/24 ,  F01D5/02 ,  F01D5/08 ,  F01D5/12 ,  F01D9/04 ,  F01D25/14 ,  F01D25/26 ,  F02C3/04 ,  F02C7/00 ,  F02C7/14 ,  F02C7/24 ,  F02C7/36

CPC classification number: F01D25/145 ,  F01D5/02 ,  F01D5/08 ,  F01D5/12 ,  F01D9/041 ,  F01D25/24 ,  F01D25/26 ,  F02C3/04 ,  F02C7/14 ,  F02C7/24 ,  F02C7/36 ,  F05D2220/32 ,  F05D2260/231 ,  F05D2260/40311 ,  Y02T50/676