公开(公告)号：US20170175646A1

公开(公告)日：2017-06-22

申请号：US14978236

申请日：2015-12-22

Applicant: General Electric Company

Inventor： Sridhar Adibhatla

IPC: F02C9/18 ,  F02C7/12 ,  F04D19/02 ,  F02C9/20 ,  F01D17/08

CPC classification number: F02C9/18 ,  F01D17/08 ,  F01D17/085 ,  F02C7/12 ,  F02C9/20 ,  F02C9/52 ,  F04D19/02 ,  F04D27/0223 ,  F04D27/0246 ,  F04D27/0284 ,  F05D2220/32 ,  F05D2260/80 ,  F05D2270/101

Abstract: A stall margin modulation (SMM) control system in communication with a gas turbine engine including a compressor is described herein. The SMM control system is configured to determine the stall margin of the compressor, operate the gas turbine engine using the determined stall margin, assess a health of the compressor, and modify the stall margin based on the assessed health of the compressor.

公开(公告)号：US09145202B2

公开(公告)日：2015-09-29

申请号：US14159490

申请日：2014-01-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Harry Kirk Mathews, Jr. ,  Sridhar Adibhatla ,  Jeffrey Russell Bult

IPC: B64C19/00 ,  H04B7/185 ,  B64D31/06

CPC classification number: B64C19/00 ,  B64D31/06 ,  F05D2260/80 ,  H04B7/18506

Abstract: A method of operating an aircraft system includes receiving flight information and trajectory intent information other than current values by an engine control system associated with an engine of the aircraft system from a flight control system associated with the aircraft system; and operating an engine associated with the engine control system using the received non-current information. An aircraft includes an engine positioned on the aircraft; a full authority digital engine controller (FADEC) communicatively coupled to the engine; and a flight control system positioned on the aircraft and communicatively coupled to the FADEC, the flight control system configured to transmit other than current values of flight information and trajectory intent information to the FADEC and to receive other than current values of at least one of engine health and parameters used to estimate engine health from at least one of the FADEC and a separate flight control center positioned offboard the aircraft.

Abstract translation: 一种操作飞行器系统的方法包括从与飞行器系统相关联的飞行控制系统的飞行器系统的发动机相关联的发动机控制系统接收除当前值以外的飞行信息和轨迹意图信息; 以及使用所接收的非当前信息来操作与所述发动机控制系统相关联的发动机。 飞机包括位于飞机上的发动机; 通信地耦合到发动机的全权限数字引擎控制器（FADEC）; 以及飞行控制系统，其定位在所述飞行器上并且通信地耦合到所述FADEC，所述飞行控制系统被配置为向所述FADEC发送除飞行信息和轨迹意图信息的当前值之外的其它值，并且接收不同于发动机中的至少一个的当前值 卫生和参数用于从至少一个FADEC和位于飞机外侧的单独的飞行控制中心估计发动机健康。

公开(公告)号：US20140058644A1

公开(公告)日：2014-02-27

申请号：US13954541

申请日：2013-07-30

Applicant: General Electric Company

Inventor： Sridhar Adibhatla ,  Steven Edward Nolte ,  Gerhard Walter Moeller ,  Christopher Timothy Gallagher ,  John William Hanify ,  Grant Alan Ingram

IPC: B64D31/06

CPC classification number: B64D31/06 ,  F01D11/24

Abstract: A method for reducing a turbine clearance between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. Said method includes determining, with a flight operation controller, that an airplane is in a first flight condition, wherein the first flight condition is associated with a first turbine clearance and a first engine responsiveness level, determining, with the flight operation controller, that the airplane is in a second flight condition, adjusting an engine responsiveness level from the first engine responsiveness level to a second engine responsiveness level based on determining the airplane is in the second flight condition, and adjusting the turbine clearance from the first turbine clearance to a second turbine clearance based on the engine responsiveness level.

Abstract translation: 提供了一种用于减小涡轮发动机的多个转子叶片和涡轮发动机的护罩之间的涡轮间隙的方法。 所述方法包括使用飞行操作控制器确定飞机处于第一飞行状态，其中第一飞行条件与第一涡轮机间隙和第一发动机响应度水平相关联，用飞行操作控制器确定： 飞机处于第二飞行状态，基于确定飞机处于第二飞行状态，将发动机响应性水平从第一发动机响应水平调整到第二发动机响应水平，并且将涡轮机间隙从第一涡轮机间隙调整到第二飞行器间隙 基于发动机响应性水平的涡轮间隙。