Gas turbine pressure sensing systems and methods of assembly

A method of assembling a gas turbine engine, said method comprising:

• coupling a combustor assembly downstream from a compressor, wherein the combustor assembly includes a combustion chamber;
• coupling a turbine downstream from the combustor assembly;
• and
• coupling a pressure sensor to the combustor assembly, wherein the sensor includes a sensor body, a diaphragm mounted within the sensor body, a channel extending from an open end of the sensor body to the diaphragm to directly expose the diaphragm to a pressure in the combustion chamber, and a microwave radar sensing unit secured to the sensor body, wherein the sensing unit includes a head positioned a distance from the diaphragm.

A method for measuring a pressure within a combustion chamber of a gas turbine engine, said method comprising:

• generating a signal representative of the pressure within the combustion chamber;
• sampling the signal;
• correlating at least one characteristic of the sampled signal to a pre-stored value, wherein the pre-stored value is associated with the pressure;
• and
• transmitting a signal representative of the pre-stored value associated with the pressure to a controller.