公开(公告)号：US20170314415A1

公开(公告)日：2017-11-02

申请号：US15651194

申请日：2017-07-17

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D25/12 ,  F02C7/14 ,  F28F7/02 ,  F28F1/12 ,  F28F1/40 ,  F28D15/00 ,  F01D25/10

CPC classification number: F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/232 ,  F28D15/00 ,  F28F1/124 ,  F28F1/40 ,  F28F7/02 ,  F28F2255/18 ,  Y02T50/676

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

公开(公告)号：US09739171B2

公开(公告)日：2017-08-22

申请号：US13679670

申请日：2012-11-16

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D5/14 ,  F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F28F1/40 ,  F28F7/02 ,  F28D15/00 ,  F28F1/12

CPC classification number: F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/232 ,  F28D15/00 ,  F28F1/124 ,  F28F1/40 ,  F28F7/02 ,  F28F2255/18 ,  Y02T50/676

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

公开(公告)号：US20150227677A1

公开(公告)日：2015-08-13

申请号：US14428021

申请日：2013-02-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Om P. Sharma ,  Michael F. Blair

IPC: G06F17/50 ,  F02C3/10 ,  F01D9/02

CPC classification number: G06F17/5086 ,  F01D9/02 ,  F01D9/023 ,  F02C3/10

Abstract: A gas turbine engine design process includes the steps of determining the location of a hot streak downstream of a combustor nozzle, and determining whether it would be most beneficial to have the hot streak initially impact a pressure side of a first static turbine vane or whether it would be more beneficial to have it impact a suction side. A location is designed for the first static turbine vane such that the hot streak will impact the more beneficial side of the first static turbine vane.

Abstract translation: 燃气涡轮发动机设计过程包括以下步骤：确定燃烧器喷嘴下游的热条的位置，以及确定是否最有利的是使热条件最初影响第一静态涡轮叶片的压力侧，或者是否 将会更有利于使其影响吸力。 一个位置被设计用于第一静态涡轮叶片，使得热条纹将影响第一静态涡轮叶片的更有利的侧面。

公开(公告)号：US20140140829A1

公开(公告)日：2014-05-22

申请号：US13679670

申请日：2012-11-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/232 ,  F28D15/00 ,  F28F1/124 ,  F28F1/40 ,  F28F7/02 ,  F28F2255/18 ,  Y02T50/676

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

Abstract translation: 涡轮发动机系统包括热源，热交换器，冷却介质入口和冷却介质出口。 热源包括第一通道。 热交换器包括第二通道和第三通道。 第一和第二通道配置在闭环回路中。 第三通道在开环电路中配置在入口和出口之间。

公开(公告)号：US11085325B2

公开(公告)日：2021-08-10

申请号：US16033356

申请日：2018-07-12

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D15/12 ,  F01D25/12 ,  F28F1/40 ,  F28F7/02 ,  F28D15/00 ,  F28F1/12 ,  F01D25/10 ,  F02C7/14

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

公开(公告)号：US10156359B2

公开(公告)日：2018-12-18

申请号：US14655059

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark F. Zelesky ,  Joel H. Wagner ,  Tracy A. Propheter-Hinckley ,  Michael F. Blair ,  Thomas N. Slavens ,  Dominic J. Mongillo

IPC: F23R3/00 ,  F01D25/12 ,  F01D11/08 ,  F01D25/24 ,  F02C7/18 ,  F01D5/18 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.

公开(公告)号：US10047631B2

公开(公告)日：2018-08-14

申请号：US15651194

申请日：2017-07-17

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F04D29/38 ,  F01D25/12 ,  F28F1/12 ,  F28D15/00 ,  F28F7/02 ,  F02C7/14 ,  F01D25/10 ,  F28F1/40

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

公开(公告)号：US10480326B2

公开(公告)日：2019-11-19

申请号：US15701008

申请日：2017-09-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David J. Candelori ,  Michael F. Blair

IPC: F04D29/54 ,  F01D5/14 ,  F01D17/14 ,  F01D9/04 ,  F01D17/16 ,  F01D5/18

Abstract: Disclosed is a vane stage for a variable area turbine, comprising vane platforms comprising a first vane platform and a second vane platform, one of the vane platforms being a radial inner vane platform and another of the vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath; a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, a secondary vane body movably secured at the first vane platform, the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension.

公开(公告)号：US20190078440A1

公开(公告)日：2019-03-14

申请号：US15701008

申请日：2017-09-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David J. Candelori ,  Michael F. Blair

IPC: F01D5/14 ,  F01D17/16 ,  F01D5/18

CPC classification number: F01D5/148 ,  F01D5/142 ,  F01D5/145 ,  F01D5/186 ,  F01D9/041 ,  F01D17/148 ,  F01D17/16 ,  F01D17/162 ,  F04D29/544 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2260/202

Abstract: Disclosed is a vane stage for a variable area turbine, comprising vane platforms comprising a first vane platform and a second vane platform, one of the vane platforms being a radial inner vane platform and another of the vane platforms being a radial outer vane platform, and a space therebetween defining an air flowpath; a primary vane body secured at opposing radial ends to the first vane platform and the second vane platform, a secondary vane body movably secured at the first vane platform, the secondary vane body being movable between a stowed position, wherein the secondary vane body is outside of the air flow path, and a deployed position, wherein the secondary vane body is extended between the plurality of vane platforms to form a vane trailing edge extension.

公开(公告)号：US20180320548A1

公开(公告)日：2018-11-08

申请号：US16033356

申请日：2018-07-12

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D25/12 ,  F28F7/02 ,  F28F1/40 ,  F01D25/10 ,  F28D15/00 ,  F02C7/14 ,  F28F1/12

CPC classification number: F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/232 ,  F28D15/00 ,  F28F1/124 ,  F28F1/40 ,  F28F7/02 ,  F28F2255/18 ,  Y02T50/676

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.