THREE SPOOL TURBOFAN ENGINE WITH LOW NOISE INTERMEDIATE TURBINE ROTOR

Abstract

A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relative to an input speed from the fan drive turbine and said high pressure turbine driving a high pressure compressor, and the intermediate pressure turbine driving a low pressure compressor, with the intermediate pressure turbine having a number of turbine blades in at least one row, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row, and the rotational speed being such that the following formula holds true for the at least one row of the intermediate pressure turbine: (number of bladesspeed)/605500 Hz.

Claims

1. A gas turbine engine comprising: a turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine; said fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relative to an input speed from said fan drive turbine; said high pressure turbine driving a high pressure compressor; said intermediate pressure turbine driving a low pressure compressor; said intermediate pressure turbine having a number of turbine blades greater than one in at least one row, and said turbine blades operating at least some of the time at an intermediate pressure turbine rotational speed, and said number of turbine blades in said at least one row, and said rotational speed being such that the following formula holds true for said at least one row of the intermediate pressure turbine
(number of bladesintermediate pressure turbine rotational speed in revolutions per minute)/605500 Hz; and wherein said gas turbine engine is rated to produce 15,000 lbs. of thrust or more, and said rotational speed being an approach speed.

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 the formula holds true for the majority of blade rows of the intermediate pressure turbine.

4. The gas turbine engine as set forth in claim 1, wherein the formula holds true for the majority of blade rows of the intermediate pressure turbine.

5. The gas turbine engine as set forth in claim 1, wherein the fan delivers air into a bypass duct and into a compressor section as core air, and a bypass ratio of the volume of air delivered into the bypass duct compared to the volume of air delivered as core air being greater than or equal to 6.

6. The gas turbine engine as set forth in claim 5, wherein bypass ratio is greater than or equal to 10.

7. The gas turbine engine as set forth in claim 6, wherein a gear ratio is greater than or equal to 2.3.

8. The gas turbine engine as set forth in claim 1, wherein a gear ratio is greater than or equal to 2.3.

9. A method of designing a gas turbine engine comprising the steps of: including a gear reduction between a fan drive turbine and a fan, a high pressure turbine driving a high pressure compressor downstream of said fan, and including an intermediate pressure turbine intermediate said high pressure turbine and said fan drive turbine, said intermediate pressure turbine driving a low pressure compressor which is intermediate said fan and said high pressure compressor; and selecting a number of blades in at least one row of the intermediate pressure turbine, in combination with a rotational speed in revolutions per minute of the intermediate pressure turbine, such that the following formula holds true for said at least one row of the intermediate pressure turbine
(number of bladesspeed)/605500 Hz.

10. The method of designing a gas turbine engine as set forth in claim 9, wherein the formula results in a number greater than or equal to 6000.

11. The method of designing a gas turbine engine as set forth in claim 10, wherein said gas turbine engine is rated to produce 15,000 pounds of thrust or more.

12. The method as set forth in claim 10, wherein the formula holds true for the majority of the blade rows of the fan drive turbine.

13. The method as set forth in claim 9, wherein said rotational speed being an approach speed.

14. The method as set forth in claim 9, wherein said rotational speed being an approach speed.

15. The method as set forth in claim 9, wherein said gas turbine engine is rated to produce 15,000 lbs. of thrust or more.

16. A turbine module comprising: a fan drive rotor, a high pressure turbine, and an intermediate pressure turbine; and said intermediate pressure turbine having a first blade row that includes a number of blades, the first blade row being capable of rotating at a rotational speed, so that when measuring said rotational speed in revolutions per minute:
(number of bladessaid rotational speed)/605500 Hz.

17. The turbine module as set forth in claim 16, wherein the formula results in a number greater than or equal to 6000.

18. The turbine module as set forth in claim 17, wherein the formula holds true for the majority of blade rows of the fan drive rotor.

19. The turbine module as set forth in claim 16, wherein said rotational speed being an approach speed.

20. The turbine module as set forth in claim 16, wherein the formula holds true for the majority of blade rows of the fan drive rotor.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0031] FIG. 1 shows a gas turbine engine.

[0032] FIG. 2A shows a first feature of an intermediate turbine.

[0033] FIG. 2B shows another feature.

DETAILED DESCRIPTION

[0034] FIG. 1 schematically shows a gas turbine engine 20. A fan 22 is driven by a fan drive turbine 30 through a gear reduction 28. The fan 22 delivers air into a bypass duct 24 as bypass air B. The fan also delivers air within a housing 26 as core air flow C to a low pressure compressor 34.

[0035] The low pressure compressor 34 delivers compressed air into a high pressure compressor 38. The high pressure compressor 38 delivers air into a combustion section 44. The high pressure compressor 38 is driven through a shaft 42 by a high pressure turbine 40. The low pressure compressor 34 is driven by an intermediate pressure turbine 36 through a shaft 35. The gear reduction 28 is driven by the fan drive turbine 30 through a shaft 29.

[0036] Products of combustion pass serially over turbine sections 40, 36 and then 30, and then exit through an exhaust nozzle 32.

[0037] As shown in FIG. 2A, the intermediate pressure turbine 36 has a rotor 50 including a plurality of blades 52, shown schematically. As shown in FIG. 2B, there may be several rows 52 and 152 of the blades.

[0038] The terms low and high as applied to speed or pressure for the spools, compressors and turbines are of course relative to each other. That is, the low speed spool operates at a lower speed than the high speed spool and the low pressure sections operate at lower pressures than the higher pressure sections.

[0039] The engine 20 may be a high-bypass engine. In one example, a bypass ratio, defined as the volume of air delivered as bypass air B compared to the volume delivered as core air flow C is greater than or equal to about 6. In a further example, the bypass ratio may be greater than or equal to about 10.

[0040] A gear ratio provided by the gear reduction 28 may be greater than or equal to about 2.3, and in other embodiments greater than or equal to about 2.5.

[0041] It has been discovered that a careful design between the number of rotating blades 52, and the rotational speed of the intermediate pressure turbine can be selected to result in noise frequencies that are less sensitive to human hearing.

[0042] A formula has been developed as follows:

(blade countrotational speed)/60 s5500 Hz.

[0043] That is, the number of rotating blades 52 in any intermediate pressure turbine stage, multiplied by the rotational speed of the intermediate pressure turbine 36 (in revolutions per minute), divided by 60 seconds should be greater than or equal to 5500 Hz. More narrowly, the amounts should be above 6000 Hz. A worker of ordinary skill in the art would recognize that the 60 second factor is to change revolutions per minute to Hertz, or revolutions per one second.

[0044] The operational speed of the intermediate pressure turbine 36 as utilized in the formula should correspond to the engine operating conditions at each noise certification point defined in Part 36 or the Federal Airworthiness Regulations. More particularly, the rotational speed may be taken as an approach certification point as defined in Part 36 of the Federal Airworthiness Regulations. For purposes of this application and its claims, the term approach speed equates to this certification point.

[0045] It is envisioned that all of the rows in the intermediate pressure turbine 36 may meet the above formula. However, this application may also extend to intermediate pressure turbines wherein only one of the blade rows in the intermediate pressure turbine meet the above formula. In other embodiments, plural rows meet the formula and in other embodiments, the majority of the rows meet the formula.

[0046] This will result in operational noise that would be less sensitive to human hearing.

[0047] In embodiments, it may be that the formula can result in a range of greater than or equal to 5500 Hz, and moving higher. Thus, by carefully designing the number of blades 52 and controlling the operational speed of the intermediate pressure turbine 36 (and a worker of ordinary skill in the art would recognize how to control this speed) one can assure that the noise frequencies produced by the low pressure turbine are of less concern to humans.

[0048] This invention is most applicable to jet engines rated to produce 15,000 pounds of thrust or more. In this thrust range, prior art jet engines have typically had frequency ranges of about 4000 hertz. Thus, the noise problems as mentioned above have existed.

[0049] Lower thrust engines (<15,000 pounds) may have operated under conditions that sometimes passed above the 4000 Hz number, and even approached 6000 Hz, however, this has not been in combination with the geared architecture, nor in the higher powered engines which have the larger fans, and thus the greater limitations on low pressure turbine or low pressure compressor speed.

[0050] Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.