Methods and apparatus for operating turbine engines using rotor temperature sensors

A temperature sensor assembly for a gas turbine engine including a multi-stage rotor assembly and at least one cavity defined within the rotor assembly, said temperature assembly comprising:

• a support system extending radially inward through the gas turbine engine;
• and
• a temperature sensor inserted through said support system, and configured to detect a temperature within the turbine rotor assembly cavity, said support system comprising a stop configured to position said temperature sensor relative to turbine rotor assembly cavity.

A gas turbine engine comprising:

• a multi-stage rotor assembly comprising at least one cavity defined therein;
• and
• a temperature sensor assembly configured to detect a temperature within said rotor assembly cavity, an operating power level of said engine adjusted in accordance with the temperature sensed within said rotor assembly cavity.