System and method for an integral drive engine with a forward main gearbox

1. A method of assembling a three-frame gas turbine engine, the method comprising:

providing an engine core, the engine core including a high pressure compressor, a combustor, and a high pressure turbine each coupled together in a serial flow arrangement;

coupling the engine core to a forward frame member and a middle frame member;

coupling a low pressure turbine to a first shaft, the low pressure turbine positioned axially aft of the middle frame member and axially aft of the engine core;

coupling an aft frame member to the low pressure turbine, the aft frame member positioned axially aft of the low pressure turbine;

coupling a fan assembly to the first shaft, the fan assembly positioned axially forward of the forward frame member and axially forward of the engine core;

coupling a low pressure compressor to the first shaft, the low pressure compressor positioned between the engine core and the fan assembly;

coupling a gearbox to the first shaft, the gearbox positioned axially forward of the fan assembly;

providing a lubrication system in flow communication with the gearbox, the lubrication system comprising a lubricant scavenge pump and a lubrication supply pump, the lubricant scavenge pump being positioned axially forward of the gearbox; and

providing a forward frame member positioned axially between the low pressure compressor and the high pressure compressor, wherein the lubrication system is configured to direct lubricant through the forward frame member, and wherein the lubrication supply pump is positioned aft of the forward frame member.

2. The method of claim 1 , wherein the low pressure compressor is positioned axially forward of the forward frame member and axially aft of the fan assembly.

3. The method of claim 1 , wherein the middle frame member is positioned axially aft of the high pressure turbine.

4. A gas turbine engine assembly comprising:

a low pressure spool comprising:

a low pressure compressor,

a fan assembly positioned axially forward of said low pressure compressor, and

a gearbox positioned axially forward of said fan assembly;

the gas turbine engine assembly further comprising:

a lubrication system in flow communication with said gearbox, wherein said lubrication system comprises a lubricant scavenge pump and a lubrication supply plump, said lubricant scavenge pump being positioned axially forward of said gearbox; and

a forward frame member positioned axially aft of said low pressure compressor, wherein said lubrication system is configured to direct lubricant to and from said gearbox through said forward frame member, and wherein said lubricant supply pump is positioned aft of said forward frame member.

5. The gas turbine engine assembly of claim 4 , the low pressure spool further comprising a low pressure turbine, wherein said low pressure compressor is rotatably coupled to the low pressure turbine through said gearbox.

6. The gas turbine engine assembly of claim 4 , the low pressure spool further comprising a low pressure turbine, wherein said low pressure compressor and said fan assembly are rotatably coupled to the low pressure turbine through said gearbox.

7. The gas turbine engine assembly of claim 4 , wherein said gearbox comprises a gearbox housing, said gearbox housing being configured to channel lubricant to said gearbox and channel scavenged lubricant from said lubricant scavenge pump axially aft toward a core engine.

8. A gas turbine engine assembly comprising:

a core engine comprising a high pressure compressor, a combustor, and a high pressure turbine in a serial flow arrangement;

a low pressure turbine positioned axially aft of said core engine;

a fan assembly positioned axially forward of said core engine;

a low pressure compressor positioned between said core engine and said fan assembly;

a gearbox positioned axially forward of said fan assembly;

a lubrication system in flow communication with said gearbox, wherein said lubrication system comprises a lubricant scavenge pump and a lubrication supply pump, said lubricant scavenge pump being positioned axially forward of said gearbox; and

a forward frame member positioned axially between said low pressure compressor and said high pressure compressor, wherein said lubrication system is configured to direct lubricant through said forward frame member, and wherein said lubrication supply pump is positioned aft of said forward frame member.

9. The gas turbine engine assembly of claim 8 , wherein said low pressure compressor is rotatably coupled to said low pressure turbine through said gearbox.

10. The gas turbine engine assembly of claim 8 , wherein said low pressure compressor and said fan assembly are rotatably coupled to said low pressure turbine through said gearbox.

11. The gas turbine engine assembly of claim 10 , wherein said gearbox is configured to reduce each of a speed of said low pressure compressor and a speed of said fan assembly relative to a speed of an input shaft.

12. The gas turbine engine assembly of claim 8 further comprising a frame assembly comprising only three frame members, the three frame members consisting of: the forward frame member, a middle frame member positioned axially between said high pressure turbine and the low pressure turbine, and an aft frame member positioned axially aft of said low pressure turbine.

13. The gas turbine engine assembly of claim 12 further comprising a longitudinal centerline, wherein each of said forward frame member, said middle frame member, and said aft frame member are coaxially aligned with said longitudinal centerline.

14. The gas turbine engine assembly of claim 12 , wherein said core engine comprises a high pressure rotor shaft and said gas turbine assembly further comprises a low pressure rotor shaft, said middle frame member configured to rotatably support an aft end portion of said high pressure rotor shaft and an aft end portion of said low pressure rotor shaft.

15. The gas turbine engine assembly of claim 14 , wherein said aft frame member is configured to rotatably support the aft end portion of said high pressure rotor shaft and the aft end portion of said low pressure rotor shaft.

16. The gas turbine engine assembly of claim 8 further comprising a frame assembly comprising only two frame members, the two frame members consisting of: the forward frame member, and a middle frame member positioned axially between said high pressure turbine and the low pressure turbine.

17. The gas turbine engine assembly of claim 8 , wherein said fan assembly is rotatably coupled to said low pressure turbine through said gearbox.

18. The gas turbine engine assembly of claim 8 , wherein said gearbox comprises a gearbox housing configured to channel lubricant to said gearbox and channel scavenged lubricant from said lubricant scavenge pump axially aft toward said core engine.

19. The gas turbine engine assembly of claim 8 , wherein the lubrication system further comprises:

a lubrication tank;

a lubrication return pump coupled in flow communication with the lubrication tank; and

wherein said lubrication supply pump is coupled in flow communication with said gearbox by a gearbox supply conduit, wherein the lubricant scavenge pump is configured to pump scavenged lubrication from the gearbox axially aft to the lubrication return pump and the lubrication tank via a lubrication tank conduit, the lubrication tank conduit extending through the forward frame member.