GAS TURBINE ENGINE CASE WITH HEATING LAYER AND METHOD
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United States of America Patent
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Issued Date -
Sep 26, 2013
app pub date -
Mar 23, 2012
filing date -
Mar 23, 2012
priority date (Note) -
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Abstract
An assembly of a rotor and case for a gas turbine engine comprises a rotor having a plurality of circumferential blades each with a blade tip. A case comprises a structural layer forming an annular body receiving therein the rotor, with a tip clearance being defined between the blade tips and the annular body, and a heating layer connected to the at least one structural layer. The heating layer has a resistivity to heat the structural layer when an electric current passes through the heating layer. An electric power source supplies current to the heating layer, the heating layer configured to in use change the diameter of the annular body to adjust the tip clearance. A method for adjusting a tip clearance between blade tips of a rotor and inner surface of a case in a gas turbine engine is also provided.
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