Split-zone flow metering T-tube

1. A gas turbine engine comprising:

a fan configured to deliver airflow to a bypass duct, the fan having a pressure ratio of less than 1.5;

a low pressure turbine section configured to drive the fan and a first compressor section, wherein the low pressure turbine section has a greater number of stages than the first compressor section and the first compressor section includes three stages;

a high pressure turbine section configured to drive a second compressor section, wherein the high pressure turbine section includes two stages;

wherein the gas turbine engine has a bypass ratio of greater than 10;

wherein the fan has a fan diameter, Dfan, the low pressure turbine section has a maximum rotor diameter, Dturb, and a ratio of the maximum rotor diameter Dturb divided by the fan diameter Dfan is less than 0.6; and

a thermal management system configured to receive a cooling stream, the thermal management system including a metering device that is configured to divide the cooling stream between a first passage and a second passage that is concentric with the first passage.

2. The gas turbine engine as recited in claim 1 , wherein the metering device includes a plurality of orifices opening to the first passage, and a central orifice opening to the second passage.

3. The gas turbine engine as recited in claim 1 , wherein the thermal management system is configured to receive the cooling stream from the second compressor section.

4. The gas turbine engine as recited in claim 3 , wherein the thermal management system is configured to deliver the cooling stream to at least one of the high pressure turbine section and the low pressure turbine section.