公开(公告)号：US20160298550A1

公开(公告)日：2016-10-13

申请号：US14685166

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Daniel B. Kupratis ,  Christopher J. Hanlon ,  Walter A. Ledwith, JR.

IPC: F02C9/18 ,  F02C3/13

CPC classification number: F02C9/18 ,  F02C3/13 ,  F02K3/075 ,  F02K3/077 ,  F05D2220/323 ,  F05D2260/213 ,  Y02T50/675

Abstract: Aspects of the disclosure are directed to an engine of an aircraft. The engine may include a first fan configured to output a first air flow, a second fan configured to receive a first portion of the first air flow and output a second air flow, a core configured to receive a first portion of the second air flow and generate a first stream, and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.

Abstract translation: 本公开的方面涉及飞机的发动机。 发动机可以包括构造成输出第一空气流的第一风扇，被配置为接收第一气流的第一部分并输出第二空气流的第二风扇，被配置为接收第二气流的第一部分的芯和 产生第一流，以及至少一个阀，其配置为基于第一气流和第二空气流中的至少一个，与第二流和第三流的产生相关联地呈现至少三个状态中的一个。

公开(公告)号：US20170328231A1

公开(公告)日：2017-11-16

申请号：US14640060

申请日：2015-03-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Walter A. Ledwith, JR. ,  Scott A. Carr ,  Christopher J. Hanlon ,  Peter A. White ,  Theodore W. Hall ,  John R. Farris ,  Andrew S. Miller ,  Christopher W. Robak ,  David C. Pimenta ,  David Richard Griffin

IPC: F01D11/24 ,  F02C7/18

CPC classification number: F02C3/055 ,  F01D11/24 ,  F02C7/185 ,  F05D2260/213 ,  F05D2270/20 ,  F05D2270/44 ,  Y02T50/676

Abstract: A method of assembling a gas turbine engine includes setting a build clearance at assembly in response to a running tip clearance defined with a cooled cooling air. A method of operating a gas turbine engine includes supplying a cooled cooling air to a high pressure turbine in response to an engine rotor speed.

公开(公告)号：US20160312740A1

公开(公告)日：2016-10-27

申请号：US14519272

申请日：2014-10-21

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Walter A. Ledwith, JR. ,  Christopher J. Hanlon

IPC: F02K3/075 ,  F02K3/077 ,  F02C3/10

CPC classification number: F02K3/075 ,  F02C3/10 ,  F02K3/077

Abstract: A gas turbine engine includes an auxiliary airflow control system to provide selective communication of a portion of a second stream from a second stream flow path into a third stream flow path, the auxiliary airflow control system in communication with a high temperature flow sourced from the turbine section.

Abstract translation: 燃气涡轮发动机包括辅助气流控制系统，以提供将第二流的一部分从第二流动路径选择性地连通到第三流动流动路径中，所述辅助气流控制系统与来自涡轮机的高温流体相通 部分。