GEARED TURBOFAN ENGINE WITH POWER DENSITY RANGE
A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.
1 . A gas turbine engine turbine comprising:
a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis;
a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in said first direction about said central axis;
a fan connected to the low pressure spool via a speed changing mechanism and will rotate in said first direction,
wherein the engine is configured to have a ratio of a thrust provided by said engine, to a volume of a turbine section including both said high pressure turbine and said low pressure turbine that is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/in 3 .
2 . (canceled)
3 . The engine as set forth in claim 1 , wherein said ratio is greater than or equal to about 2.0.
4 . The engine as set forth in claim 3 , wherein said ratio is greater than or equal to about 4.0.
5 . The engine as set forth in claim 1 , wherein said thrust is sea level take-off, flat-rated static thrust.
6 . The engine as set forth in claim 5 , wherein guide vanes are positioned upstream of a first stage in said low pressure turbine to direct gases downstream of said high pressure turbine as the gases approach said low pressure turbine.
7 . The engine as set forth in claim 6 , wherein a mid-turbine frame supports said high pressure turbine.
8 . The engine as set forth in claim 7 , wherein said guide vanes are positioned intermediate said mid-turbine frame and said low pressure turbine.
9 . (canceled)
10 . The engine as set forth in claim 1 , wherein said fan section delivering a portion of air into a bypass duct and a portion of the air into said low pressure compressor as core flow, and having a bypass ratio greater than about 6.0.
11 . The engine as set forth in claim 10 , wherein said speed changing mechanism is a gear reduction.
12 . The engine as set forth in claim 11 , wherein a planet gear is utilized to maintain the first direction of rotation between said fan and said low pressure spool.
13 . The engine as set forth in claim 12 , wherein said planet gear arrangement having a gear ratio above 2.3:1, meaning that the low pressure spool turns at least or equal to about 2.3 times as fast as said fan.
14 . The engine as set forth in claim 1 , wherein said speed changing mechanism is a gear reduction.
15 . The engine as set forth in claim 14 , wherein a planet gear is utilized to maintain the first direction of rotation between said fan and said low pressure spool.
16 . The engine as set forth in claim 15 , wherein said planet gear arrangement having a gear ratio above 2.3:1, meaning that the low pressure spool turns at least or equal to about 2.3 times as fast as said fan.
17 . A gas turbine engine turbine comprising:
a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis;
a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in said first direction about said central axis; and
a fan connected to the low pressure spool via a speed changing mechanism and will rotate in said first direction,
wherein the engine is configured to have a ratio of a sea level take-off, flat-rated static thrust provided by said engine, to a volume of a turbine section including both said high pressure turbine and said low pressure turbine that is greater than about 4.0 lbf/in 3 .
18 . (canceled)
19 . The engine as set forth in claim 17 , wherein said fan section delivering a portion of air into a bypass duct and a portion of the air into said low pressure compressor as core flow, and having a bypass ratio greater than about 6.0.
20 . The engine as set forth in claim 17 , wherein a planet gear is utilized to maintain the first direction of rotation between said fan and said low pressure spool.