Gas turbine engine with higher low spool torque-to-thrust ratio
A gas turbine engine includes a fan drive turbine driving a low pressure compressor, and driving a gear reduction to in turn drive a fan rotor at a speed slower than the fan drive turbine. The turbine section further includes a high pressure turbine driving the high pressure compressor. The fan drive turbine and low pressure compressor are connected by a shaft and the fan drive turbine, the shaft and the low pressure compressor define a low pressure spool. The gas turbine engine is rated to provide an amount of thrust at maximum takeoff, and a low spool thrust ratio defined as a ratio of a torque on the low pressure spool at maximum takeoff in ft-lbs and the maximum takeoff thrust being defined in lbf, with the low spool torque ratio being greater than or equal to 0.70 ft-lb/lbf, and less than or equal to 1.2 ft-lb/lbf.
1. A gas turbine engine comprising:
a fan rotor surrounded by a fan case and delivering air into a bypass duct defined between said fan and an inner core housing, said fan rotor also delivering air into said inner core housing and into a compressor section, said compressor section including a low pressure compressor and a high pressure compressor, said high pressure compressor delivering air into a combustor where it is mixed with fuel and ignited, and products of the combustion passing downstream into a turbine section, said turbine section including a fan drive turbine driving said low pressure compressor, and driving a gear reduction to in turn drive said fan rotor at a speed slower than said fan drive turbine, said turbine section further including a high pressure turbine driving said high pressure compressor, said fan drive turbine and low pressure compressor connected by a shaft and said fan drive turbine, said shaft and said low pressure compressor defining a low pressure spool; and
said gas turbine engine being rated to provide an amount of thrust at maximum takeoff, and a low spool torque ratio defined as a ratio of a torque on said low pressure spool at maximum takeoff in ft-lbs and said maximum takeoff thrust being defined in lbf, with said low spool torque ratio being greater than or equal to 0.70 ft-lb/lbf, and less than or equal to 1.2 ft-lb/lbf; and
a bypass ratio defined as a volume of air delivered into the bypass duct compared to the volume of air delivered into the inner core housing, and the bypass ratio being greater than or equal to 10.0 and less than or equal to 18.0, a low pressure turbine pressure ratio being greater than or equal to 8.0 and less than or equal to 13.0, and defined as a pressure measured prior to the inlet of the fan drive turbine as related to a pressure at an outlet of the fan drive turbine prior to any exhaust nozzle, and a fan pressure ratio measured across fan blades on the fan rotor alone, which is greater than or equal to 1.25 and less than or equal to 1.45.
2. The gas turbine engine as set forth in claim 1 , wherein a gear ratio of said gear reduction being greater than or equal to 3.2 and less than or equal to 4.0.
3. The gas turbine engine as set forth in claim 2 , wherein said low spool thrust ratio being greater than or equal to 0.8 ft-lb/lbf.
4. The gas turbine engine as set forth in claim 3 , wherein said low spool thrust ratio being greater than or equal to 0.9 ft-lb/lbf.
5. The gas turbine engine as set forth in claim 1 , wherein a pressure ratio at cruise condition can be defined across said fan rotor and said low pressure compressor, and said pressure ratio being greater than or equal to 3.5 and less than or equal to 6.0.
6. The gas turbine engine as set forth in claim 5 , wherein said low pressure spool also having a low pressure spool power, and a ratio of said low pressure spool torque to said low pressure spool power at maximum takeoff being defined, with said low pressure spool power being defined in horsepower, and a ratio of said low pressure spool torque to said low pressure spool power being greater than or equal to 0.5 ft-lb/hp and less than or equal to 1.2 ft-lb/hp.
7. The gas turbine engine as set forth in claim 6 , wherein said power extraction ratio being greater than or equal to 0.70 ft-lb/hp.
8. The gas turbine engine as set forth in claim 1 , wherein said low pressure spool also having a low pressure spool power, and a ratio of said low pressure spool torque to said low pressure spool power at maximum takeoff being defined, with said low pressure spool power being defined in horsepower, and a ratio of said low pressure spool torque to said low pressure spool power being greater than or equal to 0.5 ft-lb/hp and less than or equal to 1.2 ft-lb/hp.
9. The gas turbine engine as set forth in claim 8 , wherein said power extraction ratio being greater than or equal to 0.70 ft-lb/hp.
10. The gas turbine engine as set forth in claim 1 , wherein said low spool thrust ratio being greater than or equal to 0.9 ft-lb/lbf.