Closed-loop control for a gas turbine with actively stabilized compressor
AssigneeMTU Aero Engines AG
InventorsWolfgang Horn, Klaus-Juergen Schmidt
Life of this patent
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Abstract
A regulating system for a gas turbine, in particular an aircraft engine, has devices for blade-tip injection for increasing the compressor stability, these devices being activated as needed. The regulating system has devices for active clearance control, preferably in the high-pressure compressor, with which the radial clearance in the high-pressure compressor is kept in an optimum operating range, and the regulating system has a shared engine regulator for both devices. The technical problems of the prior art are avoided through the present invention, and an improved regulating system for a gas turbine, in particular an aircraft engine, is made available for active stabilization of the compressor.
Claims10
A regulating system for a gas turbine, comprising:
- devices for blade-tip injection which enhance a stability of a compressor and which are activated as needed;
- devices for active clearance control in the compressor, with which a radial clearance in the compressor is kept in an optimum operating range;
- and
- a joint engine regulator for the devices for blade-tip injection and active clearance control.
A method for regulating a gas turbine, comprising the steps of:
- controlling a casing adjustment mechanism according to a current flight status for adjusting a clearance height of at least one compressor;
- additionally measuring the clearance height and comparing an actual value with a target value;
- and
- detecting critical acceleration and/or deceleration maneuvers and activating a blade-tip injection as needed.
Dependencies are inferred from the claim text.