Gas turbine engine compressor arrangement
A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
1. A gas turbine engine comprising:
a fan section rotatable about an engine centerline axis and configured for operation at a fan pressure ratio of less than about 1.45;
a fan drive turbine that includes six (6) or less stages;
a second spool including a compressor section that includes between eight to fifteen (8-15) stages, and a second turbine section coupled to the second compressor section, wherein the fan drive turbine is axially aft of the second turbine section; and
a gear train defined along an engine centerline axis, said fan drive turbine is operable to drive said fan section through said gear train.
2. The engine as recited in claim 1 , the compressor section being a second compressor section, the engine including a first compressor section disposed forward of the second compressor section and wherein an overall compressor pressure ratio provided by the combination of the first compressor section and the second compressor section is above or equal to about fifty (50).
3. The engine as recited in claim 2 , wherein said first compressor includes four (4) stages.
4. The engine as recited in claim 1 , wherein said compressor includes eight (8) stages.
5. The engine as recited in claim 1 , wherein said fan drive turbine includes three to six (3-6) stages.
6. The engine as recited in claim 5 , wherein said fan drive turbine defines a low pressure turbine pressure ratio that is greater than about five (5).
7. The engine as recited in claim 5 , wherein said fan drive turbine defines a low pressure turbine pressure ratio that is greater than five (5).
8. The engine as recited in claim 1 , wherein said gear train defines a gear reduction ratio of greater than or equal to about 2.3.
9. The engine as recited in claim 1 , wherein said gear train defines a gear reduction ratio of greater than or equal to 2.3.
10. The engine as recited in claim 1 , wherein said gear train defines a gear reduction ratio of greater than or equal to about 2.5.
11. The engine as recited in claim 1 , wherein said gear train defines a gear reduction ratio of greater than or equal to 2.5.
12. The gas turbine engine as set forth in claim 1 , further comprising a fan variable area nozzle to vary a fan nozzle exit area and adjust a pressure ratio of a fan bypass airflow of said fan section during engine operation.
13. The engine as recited in claim 1 , wherein said engine is a high bypass engine including a fan bypass airflow ratio greater than about ten (10).
14. The engine as recited in claim 1 , wherein said engine is a high bypass engine including a fan bypass airflow bypass ratio greater than ten (10).
15. The engine as recited in claim 12 , further comprising:
a controller operable to control said fan variable area nozzle to vary a fan nozzle exit area and adjust the pressure ratio of the fan bypass airflow to reduce a fan instability.
16. A gas turbine engine comprising:
a gear train defined along an engine centerline axis, said gear train defines a gear reduction ratio of greater than or equal to about 2.3;
a spool along said engine centerline axis which drives said gear train, said spool includes a fan drive turbine with three to six (3-6) stages to drive the gear train;
a second turbine section disposed axially forward of the fan drive turbine; and
a fan section rotatable about the centerline axis and configured to be driven through the gear train at a fan tip speed less than about 1150 ft/second and to provide a fan pressure ratio less than about 1.45.
17. The engine as recited in claim 16 , wherein said fan drive turbine defines a turbine pressure ratio that is greater than five (5).
18. The engine as recited in claim 16 , wherein said gear train drives said fan section to generate a fan bypass airflow having a bypass ratio greater than ten (10).
19. The engine as recited in claim 16 , wherein said gear train defines a gear reduction ratio of greater than or equal to 2.5.
20. The engine as recited in claim 16 , wherein said fan drive turbine defines a pressure ratio that is greater than five (5), said gear train defines a gear reduction ratio of greater than or equal to 2.5 to drive said fan section and to generate a fan bypass airflow having a bypass ratio greater than ten (10).
21. The engine as recited in claim 16 , including a low pressure compressor driven by the fan drive turbine that includes four to eight (4-8) stages.