公开(公告)号：US20210324758A1

公开(公告)日：2021-10-21

申请号：US17359894

申请日：2021-06-28

Applicant: Raytheon Technologies Corporation

Inventor： Subhradeep Chowdhury ,  David M. Bostwick ,  David Gelwan ,  Frederick M. Schwarz

IPC: F01D19/02 ,  F02C9/00 ,  B64D27/12 ,  B64D41/00 ,  B64F1/36 ,  F01D25/34 ,  F02C3/04 ,  F02C6/20 ,  F02C7/277

Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.

公开(公告)号：US11674411B2

公开(公告)日：2023-06-13

申请号：US17359894

申请日：2021-06-28

Applicant: Raytheon Technologies Corporation

Inventor： Subhradeep Chowdhury ,  David M. Bostwick ,  David Gelwan ,  Frederick M. Schwarz

IPC: F01D19/02 ,  B64D27/12 ,  B64D41/00 ,  F02C9/00 ,  B64F1/36 ,  F01D25/34 ,  F02C3/04 ,  F02C6/20 ,  F02C7/277

CPC classification number: F01D19/02 ,  B64D27/12 ,  B64D41/00 ,  B64F1/364 ,  F01D25/34 ,  F02C3/04 ,  F02C6/20 ,  F02C7/277 ,  F02C9/00 ,  B64D2041/002 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2260/85 ,  F05D2270/303

Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.

公开(公告)号：US20230090879A1

公开(公告)日：2023-03-23

申请号：US17407874

申请日：2021-08-20

Applicant: Raytheon Technologies Corporation

Inventor： Boris Karpman ,  Mark A. Bushman ,  Subhradeep Chowdhury ,  Richard P. Meisner

IPC: F02C9/00

Abstract: An engine control system includes an engine controller configured to execute an open-loop model of the engine control system. The open-loop model receives a measured effector and boundary condition parameter vector and generates a synthesized engine operating parameter based on the measured effector and boundary condition parameter vector. The engine controller calculates a corrector error value between the synthesized engine operating parameter and a measured engine operating parameter, and determines an open loop corrector error calculated as a difference between the corrector error and a vector-matrix product of corrector state vector and a gain map/function. The engine controller applies the gain map/function to the open loop corrector error to determine an effector and boundary condition error vector of the measured effector and boundary condition parameter vector.

公开(公告)号：US20220243653A1

公开(公告)日：2022-08-04

申请号：US17720900

申请日：2022-04-14

Applicant: Raytheon Technologies Corporation

Inventor： Stephen A. Witalis ,  Ramesh Rajagopalan ,  Subhradeep Chowdhury

IPC: F02C6/08 ,  F02C9/42

Abstract: An engine system for an aircraft includes a first gas turbine engine, a second gas turbine engine, and a control system. The control system is configured to operate the first gas turbine engine with a sub-idle fuel burn schedule based on detecting landing of the aircraft, where the sub-idle fuel burn schedule includes a reduction of an idle fuel burn schedule. The control system is configured to operate the second gas turbine engine with the idle fuel burn schedule based on detecting landing of the aircraft.