公开(公告)号：US20190048796A1

公开(公告)日：2019-02-14

申请号：US16048738

申请日：2018-07-30

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: F02C3/055 ,  F02C7/18 ,  F01D11/24

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：US10161316B2

公开(公告)日：2018-12-25

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: F02K3/075 ,  F02K3/077 ,  F02C9/18 ,  F02C3/13

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.