Geared turbine engine with relatively lightweight propulsor module
An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.
1. A gas turbine engine comprising:
a propulsor assembly including at least a fan module and a fan drive turbine module;
a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a second turbine in fluid communication with the combustor; and
a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module, wherein a weight of the fan module and the fan drive turbine module is from 28 to 34 percent of a total weight of the gas turbine engine;
wherein the gas turbine engine includes a high spool and a low spool, the compressor section includes a low pressure compressor and a high pressure compressor, a first shaft interconnecting the second turbine and the high pressure compressor, a second shaft interconnecting the fan drive turbine module and the low pressure compressor, the high spool comprising the high pressure compressor and the second turbine, and the low spool comprising the low pressure compressor and the fan drive turbine module; and
wherein the fan module comprises no more than 20 fan blades, and a ratio between a total number of the fan blades and a total number of turbine rotors of the fan drive turbine module is between 3.3 and 8.6, and the fan drive turbine module includes at least three stages but fewer than six stages.
2. The gas turbine engine of claim 1 , wherein the fan blades are shrouded fan blades.
3. The gas turbine engine of claim 1 , wherein the turbine rotors of the fan drive turbine module are configured to rotate more than 2.6 times for every single rotation of the fan.
4. The gas turbine engine of claim 1 , wherein the fan drive turbine module comprises directionally solidified blades.
5. A method of distributing weight between a propulsor assembly and a gas generator assembly of a gas turbine engine comprising:
providing a propulsor assembly that have a first weight, the propulsor assembly including a fan module and a fan drive turbine module; and
configuring the propulsor assembly for installation within the gas turbine engine having a second weight when the propulsor assembly is installed, wherein the first weight is less than 40 percent of the second weight; and
wherein the fan module comprises no more than 20 fan blades, and a ratio between a total number of the fan blades and a total number of turbine rotors of the fan drive turbine module is between 3.3 and 8.6, and the fan drive turbine module includes at least three stages but fewer than six stages.
6. The method of claim 5 , wherein the fan blades are shrouded fan blades.
7. The method of claim 5 , wherein the turbine rotors of the fan drive turbine module are configured to rotate at least 2.6 times for every single rotation of the fan.
8. The method of claim 5 , wherein the first weight is from 28 and 34 percent of the second weight.
9. The gas turbine engine of claim 1 , wherein the gas generator assembly includes a mid-turbine frame supporting a bearing system, the mid-turbine frame including vanes in a core airflow path between the second turbine and the fan drive turbine module.