公开(公告)号：EP2820256A4

公开(公告)日：2016-01-13

申请号：EP13754324

申请日：2013-01-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL L ,  KUPRATIS DANIEL BERNARD

IPC: F01D25/16 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06 ,  F02K3/072

CPC classification number: F01D25/162 ,  F02C3/107 ,  F02C7/20 ,  F02K3/06 ,  F02K3/072 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/52 ,  F05D2250/311 ,  F05D2260/30 ,  F05D2260/40311

Abstract: A mid-turbine frame is incorporated into a turbine section of a gas turbine engine intermediate a high pressure turbine and a low pressure turbine. The high pressure and low pressure turbines rotate in opposite directions. A plurality of vanes redirect the flow downstream of the high pressure turbine as it approaches the low pressure turbine.

公开(公告)号：EP2809931A4

公开(公告)日：2015-09-16

申请号：EP13743042

申请日：2013-01-30

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOUSTON DAVID P ,  KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/02 ,  B63H5/10 ,  F01D1/24 ,  F01D5/02 ,  F02C3/107 ,  F02K3/06

CPC classification number: F02K3/06 ,  F01D5/02 ,  F01D5/026 ,  F01D5/066 ,  F02C3/107 ,  F02C7/36 ,  F05D2240/24 ,  F05D2260/40311 ,  F05D2270/02 ,  F05D2270/07 ,  Y02T50/671 ,  Y02T50/673

公开(公告)号：EP2809903A4

公开(公告)日：2015-09-16

申请号：EP13744229

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F02K3/02 ,  B63H5/10 ,  F01D1/24 ,  F01D5/02 ,  F01D25/16 ,  F02C3/067 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F02K3/072 ,  F02K3/075

CPC classification number: F02K3/06 ,  F01D25/162 ,  F02C3/067 ,  F02C7/06 ,  F02C7/36 ,  F02K3/072 ,  F02K3/075 ,  F05D2260/40311

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing.

公开(公告)号：EP3090160A4

公开(公告)日：2016-12-28

申请号：EP14877384

申请日：2014-12-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  HASEL KARL L

IPC: F02C3/04 ,  F02C7/00 ,  F02K3/06

CPC classification number: F02C3/04 ,  F02K3/06 ,  F05D2220/321 ,  F05D2220/3216

公开(公告)号：EP2841718A4

公开(公告)日：2016-03-02

申请号：EP13822569

申请日：2013-04-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  MERRY BRIAN D ,  ACKERMANN WILLIAM K

IPC: F01D25/16 ,  F02C7/06

CPC classification number: F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02K3/06

公开(公告)号：EP2834504A4

公开(公告)日：2015-11-25

申请号：EP13816584

申请日：2013-03-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDRICK M

IPC: F02C7/36 ,  F02K3/06

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

Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan.

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：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：EP2825760A4

公开(公告)日：2015-10-21

申请号：EP13760947

申请日：2013-01-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  STAUBACH JOSEPH B

IPC: F02K3/12 ,  F02C3/04 ,  F02C3/13 ,  F02C6/02 ,  F02C9/18

CPC classification number: F02C3/04 ,  F02C3/13 ,  F02C6/00 ,  F02C6/02 ,  F02C9/18 ,  F02K3/12 ,  F05D2250/30 ,  F05D2250/311 ,  F05D2270/07

Abstract: A gas turbine engine system includes a fan section, a low pressure compressor section downstream of the fan section, a first engine core downstream from the low pressure compressor section, a second engine core downstream from the low pressure compressor section, and a flowpath control mechanism configured to selectively restrict fluid flow through the second engine core. The first engine core includes a first engine core compressor section, a first engine core combustor downstream of the first engine core compressor section, and a first engine core turbine section downstream of the first engine core combustor. The second engine core includes a second engine core compressor section, a second engine core combustor downstream of the second engine core compressor section, and a second engine core turbine section downstream of the second engine core combustor.

Abstract translation: 燃气涡轮发动机系统包括风扇部分，风扇部分下游的低压压缩机部分，低压压缩机部分下游的第一发动机芯，低压压缩机部分下游的第二发动机芯，以及流路控制机构 被配置为选择性地限制流过第二发动机芯的流体。 第一发动机机芯包括第一发动机核心压缩机部分，第一发动机核心压缩机部分下游的第一发动机核心燃烧器和第一发动机核心燃烧器下游的第一发动机芯涡轮机部分。 第二发动机机芯包括第二发动机芯压缩机部分，第二发动机芯压缩机部分下游的第二发动机核心燃烧器和第二发动机核心燃烧器下游的第二发动机芯涡轮机部分。

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。