Model-based optimal control for stall margin limit protection in an aircraft engine

Abstract

A control system for a gas turbine engine, a method for controlling a gas turbine engine, and a gas turbine engine are disclosed. The control system may include a hybrid model predictive control (HMPC) module, the HMPC module receiving power goals and operability limits and determining a multi-variable control command for the gas turbine engine, the multi-variable control command determined using the power goals, the operability limits, actuator goals, sensor signals, and synthesis signals. The control system may further include system sensors for determining the sensor signals and a non-linear engine model for estimating corrected speed signals and synthesis signals using the sensor signals, the synthesis signals including an estimated stall margin remaining. The control system may further include a goal generation module for determining actuator goals for the HMPC module using the corrected speed signals and an actuator for controlling the gas turbine engine based on the multivariable control command.

Description

CROSS-REFERENCE TO RELATED APPLICATION[0001]This application is a non-provisional patent application claiming priority under 35 USC §119(e) to U.S. Provisional Patent Application Ser. No. 62 / 006,653 filed on Jun. 2, 2014.TECHNICAL FIELD OF THE DISCLOSURE[0002]The present disclosure relates to gas turbine engines, and more particularly, to control systems for gas turbine engines.BACKGROUND OF THE DISCLOSURE[0003]Over the course of an operating cycle of a gas turbine engine, a compressor section of the engine may experience compressor stall. Compressor stall is a limiting factor in the operation of gas turbine engines. In modern gas turbine engines, unstable flow may develop in the compressor during acceleration phases and / or under high altitude and lower speed flight conditions. Such unstable flow may lead to stall, which may increase turbine temperature and mechanical vibration along with simultaneously reducing the cooling air supplied to the turbine. Stall may lead to turbine fail...

AI Technical Summary

Problems solved by technology

Over the course of an operating cycle of a gas turbine engine, a compressor section of the engine may experience compressor stall.

Compressor stall is a limiting factor in the operation of gas turbine engines.

In modern gas turbine engines, unstable flow may develop in the compressor during acceleration phases and / or under high altitude and lower speed flight conditions.

Such unstable flow may lead to stall, which may increase turbine temperature and mechanical vibration along with simultaneously reducing the cooling air supplied to the turbine.

Stall may lead to turbine failure if the compressor stall is not recognized and corrective action is not taken.

In addition, other transient effects such as heat transfer, tip clearance, and variable geometry and bleed control may result in large variations in the overall compressor operating line.

Such variations may in turn, affect individual compressor stage operating conditions and a margin to aerodynamic instability.