Gas turbine engine with high speed low pressure turbine section and bearing support features
A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.
1. A turbine section of a gas turbine engine comprising:
a fan drive turbine section; and
a second turbine section,
wherein said fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed,
wherein said second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed,
said first and second speeds being redline speeds,
wherein a first performance quantity is defined as the product of the first speed squared and the first area,
wherein a second performance quantity is defined as the product of the second speed squared and the second area; and
wherein a ratio of the first performance quantity to the second performance quantity is between 0.8 and 1.5.
2. The turbine section as set forth in claim 1 , wherein said ratio is above or equal to 1.0.
3. The turbine section as set forth in claim 1 , comprising a mid-turbine frame positioned intermediate said fan drive and second turbine sections, and said mid-turbine frame having a first bearing supporting an outer periphery of a first shaft rotating with said second turbine section.
4. The turbine section as set forth in claim 3 , wherein said mid-turbine frame also including a second bearing supporting an outer periphery of a second shaft rotating with said fan drive turbine section, and said second bearing supporting an intermediate portion of said second shaft.
5. The turbine section as set forth in claim 3 , wherein said mid-turbine frame being provided with a guide vane positioned intermediate said fan drive and second turbine sections.
6. The turbine section as set forth in claim 5 , wherein said fan drive and second turbine sections will rotate in opposed directions, and said guide vane is a turning guide vane.
7. A gas turbine engine comprising:
a fan;
a compressor section in fluid communication with the fan;
a combustion section in fluid communication with the compressor section;
a turbine section in fluid communication with the combustion section,
wherein the turbine section includes a fan drive turbine section and a second turbine section,
wherein said fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed,
wherein said second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is higher than the first speed,
said first and second speeds being redline speeds,
wherein a first performance quantity is defined as the product of the first speed squared and the first area,
wherein a second performance quantity is defined as the product of the second speed squared and the second area;
wherein a ratio of the first performance quantity to the second performance quantity is between 0.5 and 1.5; and
a gear reduction is included between said fan and a shaft driven by the fan drive turbine section such that the fan will rotate at a lower speed than the fan drive turbine section.
8. The gas turbine engine as set forth in claim 7 , wherein said ratio is above or equal to 0.8.
9. The gas turbine engine as set forth in claim 8 , wherein said ratio is above or equal to 1.0.
10. The gas turbine engine as set forth in claim 7 , wherein the compressor section includes a first compressor section and a second compressor section, wherein the fan drive turbine section and the first compressor section will rotate in a first direction, and wherein the second turbine section and the second compressor section will rotate in a second opposed direction.
11. The gas turbine engine as set forth in claim 10 , wherein said second turbine section and said second compressor section are straddle-mounted by bearings supported on an outer periphery of a first shaft rotating with said second compressor section and said second turbine section.
12. The gas turbine engine as set forth in claim 7 , said second turbine section being supported by a first bearing in a mid-turbine frame.
13. The gas turbine engine as set forth in claim 12 , wherein said mid-turbine frame further incorporating a second bearing, said second bearing supporting an outer periphery of a second shaft rotating with said fan drive turbine section.
14. The gas turbine engine as set forth in claim 13 , wherein said second bearing supporting an intermediate portion of the second shaft that will rotate with said fan drive turbine section and said first compressor section.
15. A gas turbine engine comprising:
a fan;
a compressor section in fluid communication with the fan;
a combustion section in fluid communication with the compressor section;
a turbine section in fluid communication with the combustion section,
wherein the turbine section includes a fan drive turbine section and a second turbine section,
wherein said fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed,
wherein said second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is higher than the first speed,
said first and second speeds being redline speeds,
wherein a first performance quantity is defined as the product of the first speed squared and the first area,
wherein a second performance quantity is defined as the product of the second speed squared and the second area;
wherein a ratio of the first performance quantity to the second performance quantity is between 0.5 and 1.5; and
said compressor section including a first compressor section and a second compressor section, a gear reduction included between said fan and said fan drive turbine section, such that the fan will rotate at a lower speed than the fan drive turbine section.
16. The gas turbine engine as set forth in claim 15 , wherein said ratio is above or equal to 0.8.
17. The gas turbine engine as set forth in claim 16 , further comprising a mid-turbine frame positioned intermediate said fan drive and second turbine sections, and said mid-turbine frame having a first bearing supporting an outer periphery of a first shaft rotating with said second turbine section.
18. The gas turbine engine as set forth in claim 17 , wherein said first shaft is supported on a second bearing on its outer periphery, with said second bearing being mounted to a static structure.
19. The gas turbine engine as set forth in claim 15 , wherein said ratio is above or equal to 1.0.
20. The gas turbine engine as set forth in claim 15 , wherein the fan drive turbine section and the first compressor section will rotate in a first direction and the second turbine section and the second compressor section will rotate in a second opposed direction, and said fan will rotate in the second opposed direction.
21. The gas turbine engine as set forth in claim 15 , wherein the gear reduction is included between the fan and the first compressor section.