公开(公告)号：US20190219484A1

公开(公告)日：2019-07-18

申请号：US16264760

申请日：2019-02-01

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Marnie A. Rizo ,  David P. Houston ,  David M. Nissley ,  Paul J. Hiester ,  Timothy Dale ,  Timothy B. Winfield ,  Madeline Campbell ,  James R. Midgley

IPC: G01M15/14 ,  G05B23/02 ,  F02C9/00 ,  B64D27/10

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

公开(公告)号：US20180347474A1

公开(公告)日：2018-12-06

申请号：US15610188

申请日：2017-05-31

Applicant: United Technologies Corporation

Inventor： Richard P. Meisner ,  David L. Ma ,  Timothy B. Winfield ,  James R. Midgley

IPC: F02C9/28 ,  F01D17/08 ,  F01D17/06 ,  F01D5/02

CPC classification number: F02C9/28 ,  F05D2260/941 ,  F05D2270/11 ,  F05D2270/112 ,  F05D2270/114 ,  F05D2270/303 ,  F05D2270/3032 ,  F05D2270/332

Abstract: A full authority digital engine controller (FADEC) based system is also disclosed. The system includes a processor, and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the FADEC to perform operations. The operations may include measuring a first temperature at a first sensor disposed at a first known location of an engine, measuring a second temperature at a second sensor disposed at a second known location of the engine, and estimating at least one of a stress or a strain of a part or component in the engine based on the first temperature and the second temperature. The system may control fuel flow and/or other engine effectors during a thrust transient to limit the estimated stress or the estimated strain of the component from exceeding a predetermined threshold.

公开(公告)号：US11293353B2

公开(公告)日：2022-04-05

申请号：US15610188

申请日：2017-05-31

Applicant: United Technologies Corporation

Inventor： Richard P. Meisner ,  David L. Ma ,  Timothy B. Winfield ,  James R. Midgley

IPC: F02C9/28 ,  F01D5/02 ,  F01D17/06 ,  F01D17/08

Abstract: A full authority digital engine controller (FADEC) based system is also disclosed. The system includes a processor, and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the FADEC to perform operations. The operations may include measuring a first temperature at a first sensor disposed at a first known location of an engine, measuring a second temperature at a second sensor disposed at a second known location of the engine, and estimating at least one of a stress or a strain of a part or component in the engine based on the first temperature and the second temperature. The system may control fuel flow and/or other engine effectors during a thrust transient to limit the estimated stress or the estimated strain of the component from exceeding a predetermined threshold.

公开(公告)号：US10704989B2

公开(公告)日：2020-07-07

申请号：US16264760

申请日：2019-02-01

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Marnie A. Rizo ,  David P. Houston ,  David M. Nissley ,  Paul J. Hiester ,  Timothy Dale ,  Timothy B. Winfield ,  Madeline Campbell ,  James R. Midgley

IPC: G06F11/00 ,  G01M15/14 ,  F02C9/00 ,  G05B23/02 ,  B64D27/10

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

公开(公告)号：US10234359B2

公开(公告)日：2019-03-19

申请号：US15161323

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Marnie A. Rizo ,  David P. Houston ,  David M. Nissley ,  Paul J. Hiester ,  Timothy Dale ,  Timothy B. Winfield ,  Madeline N. Campbell ,  James R. Midgley

IPC: G06F11/30 ,  G01M15/14 ,  B64D27/10 ,  F02C9/00 ,  G05B23/02

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

公开(公告)号：US20170336288A1

公开(公告)日：2017-11-23

申请号：US15161323

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Marnie A. Rizo ,  David P. Houston ,  David M. Nissley ,  Paul J. Hiester ,  Timothy Dale ,  Timothy B. Winfield ,  Madeline N. Campbell ,  James R. Midgley

IPC: G01M15/14 ,  B64D27/10

CPC classification number: G01M15/14 ,  B64D27/10 ,  F02C9/00 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2260/80 ,  F05D2260/82 ,  F05D2260/94 ,  G05B23/0283

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.