Controlling a compressor of a turbine engine

Patent metadata

Field	Value
Publication number	US-12123359-B2
Application number	US-201815978097-A
Country	US
Kind code	B2
Filing date	May 12, 2018
Priority date	May 25, 2017
Publication date	Oct 22, 2024
Grant date	Oct 22, 2024

Abstract

An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.

First claim

What is claimed is:

1. A method of real-time controlling of a compressor of a turbine engine having a controller in which is stored a compressor map including a surge line and an operating line, wherein a difference between the surge line and the operating line defines a stall margin, the method comprising:
a) during the operation of the turbine engine, sensing, via at least one sensor, in real time at least two engine parameters corresponding to aircraft horsepower extraction, environmental control system bleed, or foreign object debris door deployment for the turbine engine;
b) providing the sensed at least two engine parameters from the at least one sensor to the controller;
c) setting, via the controller, a real-time operating line for the compressor based on the sensed at least two engine parameters, which provides a real-time stall margin less than a maximum safety factor stall margin for the sensed at least two engine parameters;
d) operating, via the controller, the turbine engine according to a compressor map using the real-time operating line;
e) providing a controller signal, via the controller, to at least one dump valve based on the sensed at least two engine parameters; and
f) dumping bleed air from the compressor, by the at least one dump valve, when the sensed at least two engine parameters for the environmental control system bleed is below a predetermined amount to control an amount of bleed air flowing into an environmental control system.

2. The method of claim 1 further comprising sensing, via the at least one sensor, each of aircraft horsepower extraction, environmental control system bleed, or foreign object debris door deployment for the turbine engine.

3. A method of real-time controlling of a compressor of a turbine engine having a controller in which is stored a compressor map including a surge line and an operating line, wherein a difference between the surge line and the operating line defines a stall margin, the method comprising:
a) during the operation of the engine, sensing, via at least one sensor, in real time one or more engine parameters corresponding to aircraft horsepower extraction, environmental control system bleed, or foreign object debris door deployment;
b) during the operation of the engine, sensing, via the at least one sensor, in real time one or more secondary parameters corresponding to engine age, transient effects, temperature effects, minimum airspeed, altitude, aircraft attitude, or engine inlet distortion;
c) providing the sensed one or more engine parameters and the sensed one or more secondary parameters to the controller;
d) setting, via the controller, a real-time operating line for the compressor based on the sensed one or more engine parameters and the sensed one or more secondary parameters, which provides a real-time stall margin less than a maximum safety factor stall margin for the sensed one or more engine parameters and the sensed one or more secondary parameters;
e) operating, via the controller, the engine according to a compressor map using the real-time operating line;
f) providing a controller signal, via the controller, to at least one dump valve based on the sensed one or more engine parameters and the sensed one or more secondary parameters; and
g) dumping bleed air from the compressor, by the at least one dump valve, when the sensed one or more engine parameters for the environmental control system bleed is below a predetermined amount to control an amount of bleed air flowing into an environmental control system.

4. A method of real-time controlling of a compressor of a turbine engine having a controller in which is stored a compressor map including a surge line and an operating line, wherein a difference between the surge line and the operating line defines a stall margin, the method comprising:
during the operation of the engine, sensing, with at least one sensor communicatively coupled to the controller, in real time a demand for environmental control system bleed air for an environmental control system;
further sensing, via the at least one sensor, in real time an engine parameter other than the demand for environmental control system bleed air, wherein the sensed engine parameter comprises at least one of: horsepower, foreign object door deployment, engine age, transient effects, temperature effects, minimum airspeed, altitude, attitude, inlet distortion, or inclement weather conditions;
providing the sensed engine parameter to the controller;
using the sensed engine parameter in combination with the demand for environmental control system bleed air, via the controller, to set a real-time operating line;
providing, via the controller, a controller signal to a dump valve based on the sensed demand;
controlling, by the controller, the dumping of the environmental control system bleed air to maintain the real-time operating line below the surge line; and
dumping environmental control system bleed air from the compressor to atmosphere, in response to the controller signal by the dump valve, when the sensed demand is indicative of no demand in order to control an amount of environmental control system bleed air flowing into the environmental control system.

5. A turbine engine comprising:
a compressor with multiple stages;
at least one sensor providing a real time signal of an engine operating parameter indicative of a demand for environmental control system bleed air;
the engine operating parameter further includes at least one of:
a) engine horsepower,
b) aircraft horsepower extraction,
c) foreign object debris door deployment,
d) engine age,
e) transient effects,
f) temperature effects,
g) minimum airspeed,
h) altitude,
i) attitude,
j) engine inlet distortion, or
k) inclement weather conditions;

an engine controller comprising a memory in which is stored a compressor map including a surge line and an operating line, wherein a difference between the surge line and the operating line defines a stall margin, and wherein the engine controller receives as input the engine operating parameter and updates the operating line in the compressor map in real time, the engine controller being communicatively coupled to the at least one sensor; and
a dump valve communicatively coupled to the engine controller;
wherein the engine controller is configured to provide a control signal to the dump valve based on the sensed engine operating parameter such that the dump valve is configured to dump bleed air from the compressor when the demand for environmental control system bleed air is below a predetermined amount in order to control an amount of bleed air that flows into an environmental control system.

6. The turbine engine of claim 5 wherein the engine operating parameter comprises at least two of the engine operating parameters a)-k).

Assignees

• Ge Avio Srl

Inventors

• Baladi Mehdi Milani
• Mcquiston Robert Jon
• Esposito Aniello
• Donofrio Joseph
• Simone Nicholas William
• Castellani Simone

Classifications

• F05D2270/30

  Control parameters, e.g. input parameters · CPC title

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F04D27/0215

  Arrangements therefor, e.g. bleed or by-pass valves · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title