Patent ID: 8291712

Claim:
A method for determining sensor locations in a gas turbine engine, said method comprising: providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts; providing a plurality of fuel nozzles that are each aligned with a strut sector; selecting one of the plurality of fuel nozzles as a primary index nozzle; determining an incremental angle by dividing three hundred sixty degrees by a product comprising a number of sensors multiplied by a number of nozzles where the number of nozzles equals the plurality of nozzles; and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles.