Gas turbine aeroengine control system
AssigneeHonda Giken Kogyo Kabushiki Kaisha
InventorHironori Muramatsu
Life of this patent
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Abstract
In a control system for a gas turbine aero engine, without using the engine inlet sensors, the engine inlet condition data including the intake air temperature and the intake air pressure is estimated based at least on the detected rotational speed of the turbine, the detected inlet pressure of the turbine and the detected atmospheric pressure, etc. through reasoning. Thus, the system can remove the engine inlet sensors (which are generally expensive) and instead, enables to estimate the engine inlet condition data necessary for controlling the engine with a relatively simple configuration.
Claims11
A system for controlling a gas turbine aeroengine having at least a turbine which is rotated by gas produced by the engine to rotate a rotor that sucks in air, comprising;
- turbine rotational speed detecting means for detecting a rotational speed of the turbine;
- turbine inlet pressure detecting means for detecting an inlet pressure of the turbine;
- atmospheric pressure detecting means for detecting an atmospheric pressure exerting on the engine;
- and
- engine inlet condition data estimating means for estimating engine inlet condition data including at least a Mach number and a pressure altitude based at least on the detected rotational speed of the turbine, the detected inlet pressure of the turbine and the detected atmospheric pressure.
A method of controlling a gas turbine aeroengine having at least a turbine which is rotated by gas produced by the engine to rotate a rotor that sucks in air, comprising the steps of:
- detecting a rotational speed of the turbine;
- detecting an inlet pressure of the turbine;
- detecting an atmospheric pressure exerting on the engine;
- and
- estimating engine inlet condition data including at least a Mach number and a pressure altitude based at least on the detected rotational speed of the turbine, the detected inlet pressure of the turbine and the detected atmospheric pressure.
A computer program embodied on a computer-readable medium for controlling a gas turbine aeroengine having at least a turbine which is rotated by gas produced by the engine to rotate a rotor that sucks in air, comprising the steps of:
- detecting a rotational speed of the turbine;
- detecting an inlet pressure of the turbine;
- detecting an atmospheric pressure exerting on the engine;
- and
- estimating engine inlet condition data including at least a Mach number and a pressure altitude based at least on the detected rotational speed of the turbine, the detected inlet pressure of the turbine and the detected atmospheric pressure.
Dependencies are inferred from the claim text.