Geared architecture for high speed and small volume fan drive turbine

• US 9,631,558 B2
• Filed: 06/03/2013
• Issued: 04/25/2017
• Est. Priority Date: 01/03/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: McCune, Michael E., Husband, Jason, Schwarz, Frederick M., Kupratis, Daniel Bernard, Suciu, Gabriel L., Ackermann, William K.
• Primary Examiner(s): LEE JR, WOODY A
• Application Number:
  US13/908,177
• Publication Number:
  US 20130287575A1
• Time in Patent Office: 1,422 Days
• Field of Search: 415112, 4151241, 4151242, 415175, 60 3908, 60805, 184 611, 184 612, 1841041
• CPC Class Codes: F01D 15/12 Combinations with mechanical gearing driven by multiple engines F01D13/00
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F04D 19/002 Axial flow fans
• CPC Class Codes: F04D 25/045 the pump wheel carrying the fluid driving means, e.g. turbine blades
• CPC Class Codes: F04D 29/053 Shafts
• CPC Class Codes: F04D 29/325 for axial flow fans blade mountings F04D29/34, blades F04D29/38
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2240/60 Shafts
• CPC Class Codes: F05D 2260/4031 as in toothed gearing
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F05D 2300/501 Elasticity
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine includes a flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

Claims

1. A gas turbine engine comprising:

a fan shaft driving a fan;

a frame which supports said fan shaft;

a plurality of gears to drive said fan shaft;

a flexible support which at least partially supports said plurality of gears;

a lower pressure turbine section providing a drive input into said plurality of gears; and

a higher pressure turbine section,

wherein said lower pressure turbine section has a first exit area at a first exit point and is configured to rotate at or below a first speed,

wherein said higher pressure turbine section has a second exit area at a second exit point and is configured to rotate at or below 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,

wherein a ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5; and

said frame includes a frame lateral stiffness and a frame transverse stiffness, and said flexible support includes a flexible support transverse stiffness and a flexible support lateral stiffness, and said flexible support lateral stiffness being less than said frame lateral stiffness and said flexible support transverse stiffness being less than said frame transverse stiffness.

2. The gas turbine engine as set forth in claim 1, wherein said ratio is above or equal to about 0.8.

3. The gas turbine engine as set forth in claim 1, wherein said lower pressure turbine section has at least 3 stages.

4. The gas turbine engine as set forth in claim 1, wherein said lower pressure turbine section has up to 6 stages.

5. The gas turbine engine as set forth in claim 1, wherein said higher pressure turbine section has 2 or fewer stages.

6. The gas turbine engine as set forth in claim 1, wherein a pressure ratio across the lower pressure turbine section is greater than about 5:

1.

7. The gas turbine engine as set forth in claim 1, including a ratio of a thrust provided by said engine, to a volume of a turbine section including both said higher pressure turbine section and said lower pressure turbine section being greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/inch³.

8. The gas turbine engine as set forth in claim 1, wherein a flexible coupling connects at least one of said plurality of gears to be driven by said lower pressure turbine section.

9. The gas turbine engine as set forth in claim 8, wherein said flexible coupling has a flexible coupling lateral stiffness and a flexible coupling transverse stiffness, and said flexible coupling lateral stiffness being less than said frame lateral stiffness, and said flexible coupling transverse stiffness being less than said frame transverse stiffness.

10. The gas turbine engine as set forth in claim 1, wherein said plurality of gears include a gear mesh that defines a gear mesh lateral stiffness and a gear mesh transverse stiffness, said gear mesh lateral stiffness being greater than said flexible support lateral stiffness and said gear mesh transverse stiffness being greater than said flexible support transverse stiffness.

11. The gas turbine engine as set forth in claim 1, wherein said ratio is above or equal to about 1.0.

12. A gas turbine engine comprising:

a fan shaft driving a fan;

a frame which supports said fan shaft;

a plurality of gears which drives the fan shaft;

a flexible support which at least partially supports said plurality of gears, said flexible support having a lesser stiffness than said frame;

a first turbine, said first turbine being configured to drive one of said plurality of gears;

a second turbine;

a ratio of a thrust provided by said engine, to a volume of a turbine section including both said first turbine and said second turbine being greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/inch³.

13. The gas turbine engine as set forth in claim 12, wherein said ratio is greater than or equal to about 2.0.

14. The gas turbine engine as set forth in claim 13, wherein said ratio is greater than or equal to about 4.0.

15. The gas turbine engine as set forth in claim 12, wherein said thrust is sea level take-off, flat-rated static thrust.

16. The gas turbine engine as set forth in claim 12, wherein said frame includes a frame lateral stiffness and a frame transverse stiffness, and said flexible support includes a flexible support transverse stiffness and a flexible support lateral stiffness, and said flexible support lateral stiffness being less than said frame lateral stiffness and said flexible support transverse stiffness being less than said frame transverse stiffness.

17. The gas turbine engine as set forth in claim 16, wherein a flexible coupling connects at least one of said plurality of gears to be driven by said first turbine section.

18. The gas turbine engine as set forth in claim 17, wherein said flexible coupling has a flexible coupling lateral stiffness and a flexible coupling transverse stiffness, and said flexible coupling lateral stiffness being less than said frame lateral stiffness, and said flexible coupling transverse stiffness being less than said frame transverse stiffness.

19. The gas turbine engine as set forth in claim 16, wherein said plurality of gears include a gear mesh that defines a gear mesh lateral stiffness and a gear mesh transverse stiffness, said gear mesh lateral stiffness being greater than said flexible support lateral stiffness and said gear mesh transverse stiffness being greater than said flexible support transverse stiffness.

20. A gas turbine engine comprising:

a fan shaft;

a frame which supports said fan shaft, said frame defines at least one of a frame lateral stiffness and a frame transverse stiffness;

a gear system which drives said fan shaft;

a flexible support which at least partially supports said gear system, said flexible support defines at least one of a flexible support lateral stiffness with respect to said frame lateral stiffness and a flexible support transverse stiffness with respect to said frame transverse stiffness, wherein at least one of said flexible support lateral stiffness and said flexible support transverse stiffness is less than said frame lateral stiffness and said frame transverse stiffness; and

an input coupling to said gear system, said input coupling defines at least one of an input coupling lateral stiffness with respect to said frame lateral stiffness and an input coupling transverse stiffness with respect to said frame transverse stiffness.