公开(公告)号：EP2798162A4

公开(公告)日：2015-08-26

申请号：EP12871636

申请日：2012-12-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KOHLENBERG GREGORY A ,  ZAMORA SEAN P ,  SCHWARZ FREDERICK M

IPC: F01D25/24 ,  F02K3/072 ,  F02K3/075

CPC classification number: F02K1/09 ,  F02K3/06 ,  F02K3/075

公开(公告)号：EP2834466A4

公开(公告)日：2015-06-03

申请号：EP13813554

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/04 ,  F02C7/36

CPC classification number: F01D1/24 ,  F01D15/12 ,  F02C3/067 ,  F02C3/107 ,  F02C7/36 ,  F05D2250/44 ,  F05D2260/4031

公开(公告)号：EP2844861A4

公开(公告)日：2015-05-06

申请号：EP13784265

申请日：2013-04-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  PRAISNER THOMAS J

IPC: F02K3/04

CPC classification number: F02K3/06 ,  F02C7/36 ,  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, the intermediate speed spool, and the fan drive turbine configured to rotate in the same first direction.

公开(公告)号：EP2834493A4

公开(公告)日：2015-04-15

申请号：EP13813981

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/04 ,  F02C3/107 ,  F02K3/06

CPC classification number: F02K3/075 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  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 rotor 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, the intermediate speed spool, and the fan drive turbine rotate in the same 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。 风扇驱动涡轮通过齿轮减速器驱动风扇转子。 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。 高速滑阀，中速滑阀和风扇驱动涡轮机沿同一方向旋转。

公开(公告)号：EP3084195A4

公开(公告)日：2017-09-06

申请号：EP14880953

申请日：2014-11-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL L

IPC: F02K3/06 ,  F02C9/16 ,  F02K3/075

CPC classification number: F02C7/36 ,  F02K3/06 ,  F05D2250/30 ,  F05D2260/40311

Abstract: A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pressure ratio is defined across the upstream and downstream compressor rotors. A bypass ratio is defined as a volume of air delivered as bypass flow compared to a volume of air delivered into the core housing. The overall pressure ratio is greater than or equal to about 45.0, and the bypass ratio is greater than or equal to about 11.0.

Abstract translation: 燃气涡轮发动机包括风扇，用于将作为旁路流的空气输送到旁路管道中，作为核心流动进入核心壳体，其中核心壳体包含上游压缩机转子和下游压缩机转子。 整个压力比定义在上游和下游压缩机转子之间。 旁路比定义为与输送到核心壳体内的空气量相比，作为旁路流量输送的空气体积。 总压比大于或等于约45.0，并且旁路比大于或等于约11.0。

公开(公告)号：EP3008323A4

公开(公告)日：2017-04-05

申请号：EP14795071

申请日：2014-05-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  SHERIDAN WILLIAM G

IPC: F02K3/06 ,  F02C3/04 ,  F02C7/32 ,  F02C7/36 ,  F16H1/28

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

公开(公告)号：EP3019721A4

公开(公告)日：2017-02-15

申请号：EP14822381

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ROACH JAMES T ,  WATSON CHARLES R ,  COOK III GRANT O ,  SCHWARZ FREDERICK M ,  BUGAJ SHARI L ,  SCHLICHTING KEVIN W

IPC: F02C7/00 ,  B05D1/00 ,  B64D29/00 ,  C25D1/00 ,  C25D5/56 ,  F02C7/30 ,  F02K1/06 ,  F02K3/02 ,  F04D29/44

CPC classification number: F01D25/005 ,  B64D29/00 ,  B64D2045/009 ,  C23C18/1641 ,  C23C18/31 ,  C25D1/00 ,  C25D5/56 ,  C25D7/00 ,  F01D5/282 ,  F01D5/3092 ,  F01D9/041 ,  F01D25/24 ,  F01D25/30 ,  F02C7/04 ,  F02K1/54 ,  F04D29/023 ,  F04D29/321 ,  F04D29/322 ,  F04D29/522 ,  F04D29/542 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/00 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/60 ,  F05D2250/283 ,  F05D2260/96 ,  F05D2300/10 ,  F05D2300/40 ,  F05D2300/43 ,  F05D2300/603 ,  F16C3/02 ,  Y02T50/672 ,  Y02T50/673

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

Abstract translation: 公开了用于制造轻质电镀聚合物燃气涡轮发动机部件的电镀聚合物燃气涡轮发动机部件和方法。 这些部件包括镀有一个或多个金属层的聚合物基材。 聚合物基材的聚合材料可以用可以包括碳，金属或玻璃的材料在结构上加强。 聚合物基材还可以包括多个层以形成复合铺层结构。

公开(公告)号：EP3084173A4

公开(公告)日：2016-12-28

申请号：EP14880333

申请日：2014-11-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  STAUBACH JOSEPH BRENT

IPC: F02K3/06 ,  F02C7/36

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

公开(公告)号：EP2920072A4

公开(公告)日：2016-08-10

申请号：EP13854460

申请日：2013-11-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WORTH EDWIN M ,  TILLMAN THOMAS G ,  SCHWARZ FREDERICK M

IPC: F01D5/14 ,  B23P15/04

CPC classification number: F01D5/18 ,  F01D5/141 ,  F01D5/145 ,  F01D5/147 ,  F01D5/225 ,  F01D5/28 ,  F02C7/36 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/31 ,  F05D2250/181 ,  F05D2250/311 ,  F05D2250/321 ,  F05D2250/322 ,  F05D2250/62 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/516 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336

Abstract: A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension.

Abstract translation: 风扇叶片包括具有在前缘和后缘之间延伸的翼型件的主体。 风扇叶片具有由盖封闭的通道中的至少一个以及覆盖前缘和后缘中的至少一个的端盖。 盖和端盖中的至少一个具有一对相对的端部。 限定从所述翼型件的吸入壁和压力壁中的至少一个延伸到所述相对端中的一个的盖和端盖中的一个的外表面，并且所述台阶小于或等于 到约0.010英寸（0.0254厘米）的尺寸。

公开(公告)号：EP2906806A4

公开(公告)日：2016-07-13

申请号：EP13845653

申请日：2013-03-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M

IPC: F02K3/00 ,  F01D25/24 ,  F02C3/04 ,  F02C3/10 ,  F02C3/36 ,  F02C6/08 ,  F02C7/04 ,  F02C7/36 ,  F02K99/00

CPC classification number: F01D25/24 ,  F01D25/243 ,  F02C3/10 ,  F02C6/08 ,  F02C7/36 ,  F05D2250/30 ,  F05D2260/40311

Abstract: A gas turbine engine has a compressor section, a compressor case substantially surrounding the compressor section, and a diffuser case attached at an attachment interface to the compressor case. The attachment interface is between a forward and an aft end of the compressor. A geared turbofan is also disclosed.