Geared architecture for high speed and small volume fan drive turbine
A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is between 0.5 and 1.5.
1. A gas turbine engine comprising:
a fan shaft driving a fan;
a nacelle extending about the fan to define a bypass duct;
a plurality of gears in driving engagement with said fan shaft, wherein said plurality of gears provide an epicyclic gear system, said epicyclic gear system including a ring gear having a ring gear lateral stiffness and a ring gear transverse stiffness and said epicyclic gear system having a gear mesh lateral stiffness and a gear mesh transverse stiffness, and at least one of said ring gear lateral stiffness and said ring gear transverse stiffness being less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness;
a first turbine section providing a drive input into said plurality of gears;
a two stage second turbine section, and
wherein said first turbine section has a first exit area at a first exit point and rotates at a first speed,
wherein said second turbine section has a second exit area at a second exit point and rotates at a second speed, said second speed being more than twice said first speed,
wherein a first performance quantity is defined as the product of said first speed squared and said first area,
wherein a second performance quantity is defined as the product of said second speed squared and said second area,
a performance quantity ratio of said first performance quantity to said second performance quantity is greater than or equal to 0.5 and less than or equal to 1.5.
2. The gas turbine engine as set forth in claim 1 , wherein there being a flexible support to support said epicyclic gear system, said flexible support having a flexible support lateral stiffness and a flexible support transverse stiffness, and at least one of said flexible support lateral stiffness and said flexible support transverse stiffness being less than 8% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
3. The gas turbine engine as set forth in claim 2 , wherein a frame which supports said fan shaft, at least one of said flexible support lateral stiffness and said flexible support transverse stiffness being less than 11% of a respective one of a frame lateral stiffness and a frame transverse stiffness.
4. The gas turbine engine as set forth in claim 3 , wherein a flexible connection connects a sun gear of said epicyclic gear system to be driven by said first turbine section, and said flexible connection having at least one of a flexible connection lateral stiffness and a flexible connection transverse stiffness that is less than 11% of a respective one of said frame lateral stiffness and said frame transverse stiffness.
5. The gas turbine engine as set forth in claim 2 , wherein said first turbine section having between three and six stages and said plurality of gears provide a planetary gear system.
6. The gas turbine engine as set forth in claim 5 , wherein a mid-turbine frame is positioned intermediate said first and second turbine sections, and has at least one vane in a gas flowpath between said first and second turbine section.
7. The gas turbine engine as set forth in claim 1 , wherein said first turbine having between three and six stages, and there is a flexible coupling connecting said first turbine to said plurality of gears, with said flexible coupling having a flexible coupling lateral stiffness and a flexible coupling transverse stiffness, and at least one of said flexible coupling lateral stiffness and said flexible coupling transverse stiffness being less than 5% of a respective one of a gear mesh lateral stiffness and a gear mesh transverse stiffness of said plurality of gears.
8. A gas turbine engine comprising:
a fan shaft driving a fan;
a nacelle extending about the fan to define a bypass duct;
an epicyclic gear system in driving engagement with said fan shaft having a gear mesh lateral stiffness and a gear mesh transverse stiffness and a flexible support to support said epicyclic gear system, said flexible support having a flexible support lateral stiffness and a flexible support transverse stiffness, and at least one of said flexible support lateral stiffness and said flexible support transverse stiffness being less than 8% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness; and
a first turbine section providing a drive input into said epicyclic gear system;
a second turbine section,
wherein said first turbine section has a first exit area at a first exit point and rotates at a first speed,
wherein said second turbine section has a second exit area at a second exit point and rotates at a second speed, said second speed being more than twice said first speed,
wherein a first performance quantity is defined as the product of said first speed squared and said first area,
wherein a second performance quantity is defined as the product of said second speed squared and said second area,
wherein a performance quantity ratio of the first performance quantity to said second performance quantity is between 0.5 and 1.5.
9. The gas turbine engine as set forth in claim 8 , wherein said first turbine section having between three and six stages and said epicyclic gear system provide a planetary gear system.
10. The gas turbine engine as set forth in claim 9 , wherein a frame which supports said fan shaft, at least one of said flexible support lateral stiffness and said flexible support transverse stiffness being less than 11% of a respective frame lateral stiffness and frame transverse stiffness.
11. The gas turbine engine as set forth in claim 10 , wherein said second turbine section having two stages.
12. The gas turbine engine as set forth in claim 11 , wherein a flexible connection connects a sun gear of said epicyclic gear system to be driven by said first turbine section, and said flexible connection having at least one of a flexible connection lateral stiffness and a flexible connection transverse stiffness that is less than 11% of a respective one of said frame lateral stiffness and said frame transverse stiffness.
13. The gas turbine engine as set forth in claim 8 , wherein a flexible connection connects a sun gear of said epicyclic gear system to be driven by said first turbine section, a frame which supports said fan shaft, and said flexible connection having at least one of a flexible connection lateral stiffness and a flexible connection transverse stiffness that is less than 11% of a respective one of a frame lateral stiffness and a frame transverse stiffness.
14. The gas turbine engine as set forth in claim 13 , wherein said second turbine section having two stages and said flexible support lateral stiffness is less than 8% of said gear mesh lateral stiffness.
15. The gas turbine engine as set forth in claim 11 , wherein said epicyclic gear system includes a ring gear having at least one of a ring gear lateral stiffness and a ring gear transverse stiffnesses being less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffnesses.
16. A gas turbine engine comprising:
a fan shaft driving a fan having fan blades;
a nacelle extending about the fan to define a bypass duct;
a plurality of gears in driving engagement with said fan shaft;
a first turbine section providing a drive input into said plurality of gears;
a second turbine section, and
wherein said first turbine section has a first exit area at a first exit point and rotates at a first speed,
wherein said second turbine section has a second exit area at a second exit point and rotates at a second speed, said second speed being more than twice said first speed,
wherein a first performance quantity is defined as the product of said first speed squared and said first area,
wherein a second performance quantity is defined as the product of said second speed squared and said second area,
a performance quantity ratio of said first performance quantity to said second performance quantity is greater than or equal to 0.5 and less than or equal to 1.5; and
wherein a power ratio of a flat-rated Sea Level Take-Off thrust provided by said engine in lbf, to a volume of a turbine section including both said first and second turbine sections in inch 3 being greater than or equal to 1.5 lbf/inch 3 and less than or equal to 5.5 lbf/inch 3 .
17. The gas turbine engine as set forth in claim 16 , wherein said plurality of gears provide an epicyclic gear system, said epicyclic gear system including a ring gear having a ring gear lateral stiffness and a ring gear transverse stiffness and said epicyclic gear system having a gear mesh lateral stiffness and a gear mesh transverse stiffness, and at least one of said ring gear lateral stiffness and said ring gear transverse stiffness being less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
18. The gas turbine engine as set forth in claim 17 , wherein there being a flexible support to support said epicyclic gear system, said flexible support having a flexible support lateral stiffness and a flexible support transverse stiffness, and at least one of said flexible support lateral stiffness and said flexible support transverse stiffness being less than 8% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
19. The gas turbine engine as set forth in claim 18 , wherein said first turbine section having between three and six stages, and said second turbine section having two stages and said epicyclic gear system is a planetary gear system.
20. The gas turbine engine as set forth in claim 18 , wherein a frame which supports said fan shaft, at least one of said flexible support lateral stiffness and said flexible support transverse stiffness being less than 11% of a respective one of a frame lateral stiffness and a frame transverse stiffness.
21. The gas turbine engine as set forth in claim 20 , wherein a flexible connection connects a sun gear of said epicyclic gear system to be driven by said first turbine section, and said flexible connection having at least one of a flexible connection lateral stiffness and a flexible connection transverse stiffness that is less than 11% of a respective one of said frame lateral stiffness and said frame transverse stiffness.
22. The gas turbine engine as set forth in claim 18 , wherein a low fan pressure ratio across the fan blades alone is less than 1.45.
23. The gas turbine engine as set forth in claim 22 , wherein a frame is positioned intermediate said first and second turbine sections, and has a vane in a flowpath between said first and second turbine section.
24. The gas turbine engine as set forth in claim 18 , wherein said power ratio being greater than or equal to 4.0 lbf/inch 3 and less than or equal to 5.5 lbf/inch 3 .
25. The gas turbine engine as set forth in claim 24 , wherein said first turbine section having between three and six stages, and said second turbine section having two stages.
26. The gas turbine engine as set forth in claim 25 , wherein a flexible support supports said epicyclic gear system, and a frame which supports said fan shaft, and said flexible support having at least one of a flexible support lateral stiffness and a flexible support transverse stiffness that is less than 11% of a respective one of a frame lateral stiffness and a frame transverse stiffness.
27. The gas turbine engine as set forth in claim 26 , wherein a flexible connection connects a sun gear of said epicyclic gear system to be driven by said first turbine section, and said flexible connection having at least one of a flexible connection lateral stiffness and a flexible connection transverse stiffness that is less than 11% of a respective one of said frame lateral stiffness and said frame transverse stiffness.
28. The gas turbine engine as set forth in claim 27 , wherein a low fan pressure ratio across the fan blades alone is less than 1.45.