Low noise compressor rotor for geared turbofan engine
View Patent ↗A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute.
1. A gas turbine engine comprising:
a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion, the low pressure turbine portion driving said low pressure compressor portion and the fan;
a gear reduction effecting a reduction in the speed of said fan relative to a speed of the low pressure turbine and the low pressure compressor portion;
at least one of said low pressure turbine portion and said low pressure compressor portion having a number of blades in each of a plurality of rows, and said blades operating at least some of the time at a rotational speed, and said number of blades and said rotational speed being such that the following formula holds true for at least one of the blade rows of said at least one of the low pressure turbine portion and/or the low pressure compressor sections:
(number of blades×rotational speed)/60≧5500; and
said rotational speed being an approach speed in revolutions per minute.
2. The gas turbine engine as set forth in claim 1 , wherein the formula results in a number greater than or equal to 6000 Hz.
3. The gas turbine engine as set forth in claim 2 , wherein said gas turbine engine is rated to produce 15,000 pounds of thrust or more.
4. The gas turbine engine as set forth in claim 1 , wherein the at least one of the low pressure turbine portion and the low pressure compressor portion is the low pressure compressor portion.
5. The gas turbine engine as set forth in claim 4 , wherein the formula holds true for a plurality of the blade rows of the low pressure compressor portion.
6. The gas turbine engine as set forth in claim 4 , wherein the formula results in a number greater than or equal to 6000.
7. The gas turbine engine as set forth in claim 4 , wherein said gas turbine engine is rated to produce 15,000 pounds of thrust or more.
8. The gas turbine engine as set forth in claim 4 , wherein said gear reduction has a gear ratio of greater than about 2.3.
9. The gas turbine engine as set forth in claim 8 , wherein said gear reduction has a gear ratio of greater than about 2.5.
10. The gas turbine engine as set forth in claim 4 , wherein said fan delivers air into a bypass duct, and a portion of air into said compressor section, with a bypass ratio defined as the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor section, and said bypass ratio being greater than about 6.
11. The gas turbine engine as set forth in claim 10 , wherein said bypass ratio is greater than about 10.
12. The gas turbine engine as set forth in claim 1 , wherein said gear reduction has a gear ratio of greater than about 2.3.
13. The gas turbine engine as set forth in claim 1 , wherein said fan delivers air into a bypass duct, and a portion of air into said compressor section, with a bypass ratio defined as the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor section, and said bypass ratio being greater than about 6.
14. The gas turbine engine as set forth in claim 13 , wherein said bypass ratio is greater than about 10.
15. A compressor module comprising:
a low pressure portion having a number of blades in each of a plurality of rows of said low pressure portion, and said blades operating at least some of the time at a rotational speed, and said number of blades and said rotational speed being such that the following formula holds true for at least one of the blade rows of the low pressure portion
(number of blades×rotational speed)/60≧5500 Hz; and
said rotational speed being an approach speed in revolutions per minute.
16. The compressor module as set forth in claim 15 , wherein the formula results in a number greater than or equal to 6000 Hz.
17. The compressor module as set forth in claim 16 , wherein said gas turbine engine is rated to produce 15,000 pounds of thrust or more.
18. The compressor module as set forth in claim 17 , wherein the formula holds true for a plurality of the blade rows of the low pressure portion.
19. The compressor module as set forth in claim 18 , wherein the formula holds true for all of the blade rows of the low pressure portion.
20. The compressor module as set forth in claim 15 , wherein the formula holds true for a plurality of the blade rows of the low pressure portion.