Geared turbine engine with relatively lightweight propulsor module

1. A gas turbine engine comprising:

a propulsor assembly consisting of a propulsor and a low pressure turbine, the propulsor including a hub and an array of no more than 20 blades extending from the hub;

an epicyclic gear train defining a gear reduction ratio of greater than 2.3;

wherein a weight of the propulsor assembly is less than 40 percent of a total weight of the gas turbine engine, excluding any nacelle;

a high spool including an outer shaft connecting a high pressure turbine and a high pressure compressor;

a low spool including an inner shaft concentric with the outer shaft, the inner shaft connecting a low pressure compressor and the low pressure turbine, the inner shaft driving the propulsor through the gear train to drive the propulsor at a lower speed than the low speed spool, the low pressure compressor including three stages, and the high pressure compressor including a greater number of stages than the low pressure compressor; and

wherein the high pressure turbine includes two stages, the low pressure turbine includes three turbine rotors, and a weight of the propulsor is greater than a weight of the low pressure turbine.

2. The gas turbine engine as recited in claim 1 , wherein the gear reduction ratio is greater than 2.6.

3. The gas turbine engine as recited in claim 2 , wherein the high pressure compressor has a greater number of stages than the low pressure turbine.

4. The gas turbine engine as recited in claim 3 , wherein a ratio between a total number of the blades of the propulsor and a total number of turbine rotors of the low pressure turbine is between 3.3 and 8.6.

5. The gas turbine engine as recited in claim 4 , wherein the low pressure compressor has a greater number of stages than the high pressure turbine.

6. The gas turbine engine as recited in claim 5 , wherein the low pressure turbine includes an inlet, an outlet, and a pressure ratio greater than 5:1, wherein the pressure ratio is a ratio of a pressure measured prior to the inlet as related to a pressure at the outlet prior to any exhaust nozzle.

7. The gas turbine engine as recited in claim 6 , wherein the high pressure turbine is a two-stage turbine.

8. The gas turbine engine as recited in claim 7 , wherein the weight of the propulsor assembly is 28.4 percent to 33.2 percent of the total weight of the gas turbine engine, excluding any nacelle.

9. The gas turbine engine as recited in claim 8 , wherein the low pressure turbine includes no more than six turbine rotors.

10. The gas turbine engine as recited in claim 9 , wherein the epicyclic gear train is a star gear system.

11. The gas turbine engine as recited in claim 9 , wherein the epicyclic gear train is a planetary gear system.

12. The gas turbine engine as recited in claim 11 , further comprising a mid-turbine frame between the high pressure turbine and the low pressure turbine, wherein the mid-turbine frame supports a bearing system and includes a plurality of vanes that serve as inlet guide vanes for the low pressure turbine.

13. The gas turbine engine as recited in claim 12 , wherein:

the low pressure turbine is a three-stage or four-stage turbine; and

the weight of the propulsor is between 712 pounds and 1261 pounds, and the weight of the low pressure turbine is between 321 pounds and 577 pounds.

14. The gas turbine engine as recited in claim 7 , wherein a first blade row of the low pressure compressor is axially aft of the epicyclic gear train relative to an engine longitudinal axis.

15. The gas turbine engine as recited in claim 14 , wherein the epicyclic gear train is a star gear system.

16. The gas turbine engine as recited in claim 15 , wherein the propulsor is a fan, and further comprising a bypass ratio of greater than 10 and a nacelle circumscribing the fan, wherein the propulsor assembly excludes the nacelle, and the total weight of the gas turbine engine excludes the nacelle.

17. The gas turbine engine as recited in claim 16 , further comprising a low fan pressure ratio of less than 1.45 at cruise at 0.8 Mach and 35,000 feet, the fan pressure ratio measured across the blade alone.

18. The gas turbine engine as recited in claim 17 , wherein the low pressure turbine includes no more than six turbine rotors.

19. The gas turbine engine as recited in claim 18 , further comprising a mid-turbine frame between the high pressure turbine and the low pressure turbine, wherein the mid-turbine frame supports a bearing system and includes a plurality of vanes that serve as inlet guide vanes for the low pressure turbine.

20. The gas turbine engine as recited in claim 19 , wherein the weight of the propulsor assembly is 28.4 percent to 33.2 percent of the total weight of the gas turbine engine, excluding the nacelle.

21. The gas turbine engine as recited in claim 20 , wherein the weight of the fan is between 712 pounds and 1261 pounds, the weight of the low pressure turbine is between 321 pounds and 577 pounds, the weight of the propulsor assembly is between 1033 pounds and 1838 pounds, and the total weight of the gas turbine engine is between 3637 pounds and 6162 pounds.

22. The gas turbine engine as recited in claim 14 , wherein the epicyclic gear train is a planetary gear system.

23. The gas turbine engine as recited in claim 22 , wherein the propulsor is a fan, and further comprising a bypass ratio of greater than 10 and a nacelle circumscribing the fan, wherein the propulsor assembly excludes the nacelle, and the total weight of the gas turbine engine excludes the nacelle.

24. The gas turbine engine as recited in claim 23 , further comprising a low fan pressure ratio of less than 1.45 at cruise at 0.8 Mach and 35,000 feet, the fan pressure ratio measured across the blade alone.

25. The gas turbine engine as recited in claim 24 , wherein the low pressure turbine has an equal or greater number of stages than the low pressure compressor.

26. The gas turbine engine as recited in claim 25 , wherein the low pressure turbine includes no more than six turbine rotors.

27. The gas turbine engine as recited in claim 26 , further comprising a mid-turbine frame between the high pressure turbine and the low pressure turbine, wherein the mid-turbine frame supports a bearing system and includes a plurality of vanes that serve as inlet guide vanes for the low pressure turbine.

28. The gas turbine engine as recited in claim 27 , wherein the weight of the propulsor assembly is 28.4 percent to 33.2 percent of the total weight of the gas turbine engine, excluding the nacelle.

29. The gas turbine engine as recited in claim 28 , wherein:

the low pressure turbine is a three-stage or four-stage turbine; and

the weight of the fan is between 712 pounds and 1261 pounds, the weight of the low pressure turbine is between 321 pounds and 577 pounds, and the weight of the propulsor assembly is between 1033 pounds and 1838 pounds.

30. The gas turbine engine as recited in claim 29 , wherein the total weight of the gas turbine engine is between 3637 pounds and 6162 pounds.