公开(公告)号：US20200347787A1

公开(公告)日：2020-11-05

申请号：US16783512

申请日：2020-02-06

Applicant: United Technologies Corporation

Inventor： Timothy J. Crowley ,  Sorin Bengea ,  Manuj Dhingra ,  David Gelwan ,  Kevin Hendricks ,  Joshua Adams ,  Martin Richard Amari ,  Richard P. Meisner ,  David Lei Ma

IPC: F02C9/00 ,  B64D27/02

Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine an estimate of hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a model predictive control state and a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the model predictive control state and the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.

公开(公告)号：US10378455B2

公开(公告)日：2019-08-13

申请号：US15688614

申请日：2017-08-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Sorin Bengea ,  Jeffrey C. Simmons

IPC: F02C9/26 ,  G05B17/02 ,  G06F9/455 ,  F23N1/00

Abstract: A system for generating a base point database for use by a full authority digital engine control (FADEC) to control a gas turbine engine includes a memory configured to store a model of the gas turbine engine. The system also includes a model generation processor coupled to the memory and designed to perform an initial simulation of the gas turbine engine using the model to determine ranges of sensitivity of desired engine parameters throughout an operating envelope, divide the operating envelope into a multiple regions based on the ranges of sensitivity of the desired engine parameters, select multiple combinations of base points within each of the multiple regions, perform an additional simulation of the gas turbine engine to determine an accuracy of interpolation between each of the multiple combinations of base points for each of the multiple regions, and select final base points from the multiple combinations of base points based on the accuracy.

公开(公告)号：US10260425B2

公开(公告)日：2019-04-16

申请号：US15147173

申请日：2016-05-05

Applicant: United Technologies Corporation

Inventor： Timothy J. Crowley ,  Tyler J. Selstad ,  Sorin Bengea ,  Robert H. Luppold

IPC: F02C7/22 ,  F02C7/232 ,  F02C7/236 ,  F02C9/00 ,  F02C9/28

Abstract: A fuel system for a gas turbine engine includes, among other things, a plurality of components defining a plurality of localized nodes at distinct locations relative to a fuel flow path, each of the plurality of localized nodes characterized by a distinct set of failure parameters. One or more fuel sensors are configured to measure at least one fuel condition relating to flow through the fuel flow path. A fuel observation assembly is coupled to one or more engine sensors configured to measure at least one engine condition. The fuel observation assembly comprises an estimation module operable to calculate an expected condition of each of the plurality of localized nodes based upon the set of failure parameters, an observation module operable to calculate an observed condition of each of the plurality of localized nodes, the observed condition based on present values of the at least one fuel condition and the at least one engine condition, and a comparison module operable to determine an abnormality corresponding to a first one of the plurality of localized nodes based upon a comparison of the expected condition and the observed condition for each of the plurality of localized nodes.