Aircraft engine with inter-turbine engine frame

• US 6,708,482 B2
• Filed: 11/29/2001
• Issued: 03/23/2004
• Est. Priority Date: 11/29/2001
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Seda, Jorge F.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US09/997,461
• Publication Number:
  US 20030097844A1
• Time in Patent Office: 845 Days
• Field of Search: 602/261, 607/91, 607/96, 607/97, 244/54, 248/554
• US Class Current: 60/226.1
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An aircraft engine turbine frame includes a first structural ring, a second structural ring disposed co-axially with and radially spaced inwardly of the first structural ring about a centerline axis. A plurality of circumferentially spaced apart struts extend between the first and second structural rings. Forward and aft sump members having forward and aft central bores are fixedly joined to forward and aft portions of the turbine frame respectively. A frame connecting means for connecting the engine to an aircraft is disposed on the first structural ring. The frame connecting means may include a U-shaped clevis. The frame may be an inter-turbine frame axially located between first and second turbines of first and second rotors of a gas turbine engine assembly. An axial center of gravity of the second turbine passes though or very near a second turbine frame bearing supported by the aft sump member.

Claims

1. An aircraft gas turbine engine turbine frame comprising:

a first structural ring,

a second structural ring disposed co-axially with and radially spaced inwardly of said first structural ring about a centerline axis,

a plurality of circumferentially spaced apart struts extending radially between said first and second structural rings,

forward and aft sump members having forward and aft central bores,

said forward and aft sump members fixedly joined to forward and aft portions of said turbine frame respectively, and

a frame connecting means for connecting said engine to an aircraft disposed on said first structural ring.

2. A frame as claimed in claim 1 wherein said forward and aft central bores are cylindrical.

3. A frame as claimed in claim 1 wherein said frame connecting means includes at least one U-shaped clevis.

4. A frame as claimed in claim 3 wherein said forward and aft central bores are cylindrical.

5. A gas turbine engine assembly comprising:

an inter-turbine frame axially located between first and second turbines of first and second rotors respectively,

said first turbine located forward of said second turbine,

said second rotor includes a second shaft which is at least in part rotatably disposed co-axially with and radially inwardly of said first rotor,

said inter-turbine frame comprising;

a first structural ring,

a second structural ring disposed co-axially with and radially spaced inwardly of said first structural ring about a centerline axis,

a plurality of circumferentially spaced apart struts extending radially between said first and second structural rings,

forward and aft sump members having forward and aft central bores,

said forward and aft sump members fixedly joined to forward and aft portions of said turbine frame respectively,

said second rotor supported by a respective aftwardmost second turbine frame bearing mounted in said aft central bore of said aft sump member,

said first rotor partly supported by a respective first turbine frame bearing mounted in said forward central bore of said forward sump member, and

a frame connecting means for connecting said engine to an aircraft located on said first structural ring.

6. An assembly as claimed in claim 5 wherein an axial center of gravity of said second turbine passes though or very near said second turbine frame bearing.

7. An assembly as claimed in claim 6 wherein said second turbine includes a turbine disk assembly comprising axially adjacent rotor disks interconnected by structural disk forward and aft spacer arms, respectively, and said turbine disk assembly is connected to said second shaft at or near said axial center of gravity.

8. An assembly as claimed in claim 7 further comprising a conical shaft extension drivingly connected said turbine disk assembly to said second shaft and said conical shaft extension connected to said turbine disk assembly at or near said axial center of gravity.

9. An assembly as claimed in claim 8 wherein said turbine disk assembly further comprises said rotor disks having pluralities of hubs connected to rims by webs extending radially outwardly from said hubs each of said rotor disks supports a row of blades supported in said disk rim.

10. A frame as claimed in claim 9 wherein said forward and aft central bores are cylindrical.

11. A frame as claimed in claim 9 wherein said frame connecting means includes at least one U-shaped clevis.

12. A frame as claimed in claim 11 wherein said forward and aft central bores are cylindrical.

13. An aircraft gas turbine engine assembly comprising:

an inter-turbine frame axially located between high and low pressure turbines of high and low pressure rotors respectively,

said high pressure turbine located forward of said low pressure turbine,

said low pressure rotor includes a low pressure shaft which is at least in part rotatably disposed co-axially with and radially inwardly of said high pressure rotor,

said inter-turbine frame comprising;

a first structural ring,

a second structural ring disposed co-axially with and radially spaced inwardly of said first structural ring about a centerline axis,

a plurality of circumferentially spaced apart struts extending radially between said first and second structural rings,

forward and aft sump members having forward and aft central bores,

said forward and aft sump members fixedly joined to forward and aft portions of said turbine frame respectively,

said low pressure rotor supported by a respective aftwardmost second turbine frame bearing mounted in said aft central bore of said aft sump member,

said high pressure rotor partly supported by a respective first turbine frame bearing mounted in said forward central bore of said forward sump member, and

a frame connecting means for connecting said engine to an aircraft local d on said first structural ring.

14. An assembly as claimed in claim 13 wherein said aft sump member has a first radius as measured from said engine centerline axis that is substantially greater than a second radius of said forward sump member.

15. An assembly as claimed in claim 14 wherein said first radius a range of 150 to 250 percent larger than said second radius.

16. An assembly as claimed in claim 13 wherein said low pressure turbine has an axial center of gravity that passes though or very near said second turbine frame bearing.

17. An assembly as claimed in claim 16 wherein said low pressure turbine includes a turbine disk assembly comprising axially adjacent rotor disks interconnected by structural disk forward and aft spacer arms, respectively, and said turbine disk assembly is connected to said low pressure shaft at or near said axial center of gravity.

18. An assembly as claimed in claim 17 further comprising a conical shaft extension drivingly connecting said turbine disk assembly to said second shaft and said conical shaft extension connected to said turbine disk assembly at or near said axial center of gravity.

19. An assembly as claimed in claim 18 wherein said turbine disk assembly further comprises said disks having pluralities of hubs connected to rims by webs extending radially outwardly from said hubs each of said rotor disks supports a row of blades supported in said disk rim.

20. An assembly as claimed in claim 19 wherein said aft sump member has a first radius as measured from said engine centerline axis that is substantially greater than a second radius of said forward sump member.

21. An assembly as claimed in claim 20 wherein said first radius a range of 150 to 250 percent larger than said second radius.

22. A frame as claimed in claim 21 wherein said frame connecting means includes at least one U-shaped clevis.

23. An aircraft gas turbine engine assembly comprising:

co-axial first and second rotors rotatably supported by only two axially spaced apart frames,

said frames being axially spaced apart forward and aft frames rotatably supporting said first and second rotors,

each of said frames comprising a first structural ring and a second structural ring, said second structural ring disposed co-axially with and radially spaced inwardly of said first structural ring about a centerline axis, and a plurality of circumferentially spaced apart struts extending radially between said first and second structural rings,

a first shaft of said second rotor disposed radially inwardly of said first rotor,

said aft frame located between turbines of said first and second rotors, and

forward and aft frame connecting means for connecting said engine to an aircraft disposed on said forward and aft frames.

24. An aircraft gas turbine engine assembly comprising:

axially spaced apart fan and inter-turbine frames rotatably supporting co-axial high and low pressure rotors,

each of said frames comprising a first structural ring and a second structural ring, said second structural ring disposed co-axially with and radially spaced inwardly of said first structural ring about a centerline axis, and a plurality of circumferentially spaced apart struts extending radially between said first and second structural rings.

said inter-turbine frame axially located between high and low pressure turbines of said high and low pressure rotors respectively,

said high pressure turbine located forward of said low pressure turbine,

said low pressure rotor includes a low pressure shaft which is at least in part rotatably disposed co-axially with and radially inwardly of said high pressure rotor,

forward and aft sump members having forward and aft central bores,

said forward and aft sump members fixedly joined to forward and aft portions of said turbine frame respectively,

said low pressure rotor supported by a respective aftwardmost second turbine frame bearing mounted in said aft central bore of said aft sump member,

said high pressure rotor partly supported by a respective first turbine frame bearing mounted in said forward central bore of said forward sump member, and

a frame connecting means for connecting said engine to an aircraft located on said first structural ring.

25. An assembly as claimed in claim 24 wherein said aft sump member has a first radius as measured from said engine centerline axis that is substantially greater than a second radius of said forward sump members.

26. An assembly as claimed in claim 25 wherein said first radius a range of 150 to 250 percent larger than said second radius.

27. An assembly as claimed in claim 24 wherein said low pressure turbine has an axial center of gravity and is connected to said low pressure shaft at or near said second turbine frame bearing.

28. An assembly as claimed in claim 27 wherein said low pressure turbine includes a turbine disk assembly comprising axially adjacent rotor disks interconnected by structural disk forward and aft spacer arms, respectively, and said turbine disk assembly is connected to said low pressure shaft at or near said axial center of gravity.

29. An assembly as claimed in claim 28 further comprising a conical shaft extension drivingly connecting said turbine disk assembly to said second shaft and said conical shaft extension connected to said turbine disk assembly at or near said axial center of gravity.

30. An assembly as claimed in claim 29 wherein said turbine disk assembly further comprises said disks having pluralities of hubs connected to rims by webs extending radially outwardly from said hubs each of said rotor disks supports a row of blades supported in said disk rim.

31. An assembly as claimed in claim 30 wherein said aft sump member has a first radius as measured from said engine centerline axis that is substantially greater than a second radius of said forward sump members.