초록 ▼

A method for assembling a gas turbine engine includes providing a high pressure turbine, providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction, providing a low-pressure turbine outer rotor that includes a second p

A method for assembling a gas turbine engine includes providing a high pressure turbine, providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction, providing a low-pressure turbine outer rotor that includes a second plurality of turbine blade rows configured to rotate in a second direction that is opposite the first direction, and coupling a plurality of bearings between the outer rotor and a turbine mid-frame between the high pressure turbine and at least one of the inner and outer rotors such that the plurality of bearings support a forward end of the outer rotor.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing a high pressure turbine; providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction; providing a low-pressure turb

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising: providing a high pressure turbine; providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction; providing a low-pressure turbine outer rotor that includes a second plurality of turbine blade rows configured to rotate in a second direction that is opposite the first direction; and coupling a plurality of bearings between the outer rotor and a turbine mid-frame between the high pressure turbine and at least one of the inner and outer rotors such that the plurality of bearings support a forward end of the outer rotor. 2. A method in accordance with claim 1 further comprising coupling a support ring to the second plurality of turbine blades such that the plurality of bearings rotatably support the support ring. 3. A method in accordance with claim 1 wherein coupling a plurality of bearings between the outer rotor and a turbine mid-frame further comprises coupling at least four bearings between the outer rotor and a turbine mid-frame. 4. A method in accordance with claim 1 further comprising: coupling at least one support member to the turbine mid-frame; and coupling a bearing to the support member such that the bearing supports a forward end of the outer rotor. 5. A method in accordance with claim 1 wherein coupling a plurality of bearings between the outer rotor and a turbine mid-frame further comprises coupling a plurality of bearings between the outer rotor and the turbine mid-frame such that the plurality of bearings are space approximately equidistantly about an inner periphery of the outer rotor. 6. A method in accordance with claim 1 further comprising: coupling a support member to the outer rotor; coupling a first seal member to the support member in sealing contact between the support assembly and the turbine mid-frame; and coupling a second seal member to the support member in sealing contact between the support member and an inner rotor shaft. 7. A counter-rotating low-pressure turbine comprising: an inner rotor comprising a first plurality of turbine blade rows configured to rotate in a first direction; an outer rotor comprising a second plurality of turbine blade rows configured to rotate in a second direction that is opposite said first direction, said outer rotor positioned such that at least one of the second plurality of turbine blade rows is coupled axially forward of the first plurality of turbine blade rows; a turbine mid-frame coupled axially forward from said outer rotor; and a plurality of bearings coupled between said outer rotor and said turbine mid-frame such that said plurality of bearings support a forward end of said outer rotor. 8. A counter-rotating low-pressure turbine in accordance with claim 7 further comprising a support ring coupled to said second plurality of turbine blades such that said bearings rotatably support said support ring. 9. A counter-rotating low-pressure turbine in accordance with claim 7 further comprising a support member rotatably coupled to at least one of said plurality of bearings to said turbine mid-frame. 10. A counter-rotating low-pressure turbine in accordance with claim 7 wherein said plurality of bearings are spaced approximately equidistantly about an inner periphery of said outer rotor. 11. A counter-rotating low-pressure turbine in accordance with claim 10 wherein said each of said plurality of bearings is a foil bearing. 12. A counter-rotating low-pressure turbine in accordance with claim 7 further comprising: at least one support member securedly coupled to said turbine mid-frame, said plurality of bearings rotatably coupled to said support member such that said plurality of bearings support a forward end of said outer rotor. 13. A counter-rotating low-pressure turbine in accordance with claim 12 further comprising: a first seal member coupled to said at least one support member in sealing contact between said support member and said turbine mid-frame; and a second seal member coupled to said support member in sealing contact between said support member and an inner rotor shaft. 14. A counter-rotating low-pressure turbine in accordance with claim 13 wherein said first and second seal members define a cavity between said turbine mid-frame, said outer rotor, and said inner rotor shaft, said low-pressure turbine further comprises a bearing rotatably coupled between said support member and said first shaft within said cavity. 15. A gas turbine engine comprising: an inner rotor comprising a first plurality of turbine blade rows configured to rotate in a first direction; an outer rotor comprising a second plurality of turbine blade rows configured to rotate in a second direction that is opposite said first direction, said outer rotor coupled to said inner rotor such that at least one of said second plurality of turbine blade rows is coupled axially forward of said first plurality of turbine blade rows; a turbine mid-frame coupled axially forward from said outer rotor; and a plurality of bearings coupled between said outer rotor and said turbine mid-frame such that said plurality of bearings support a forward end of said outer rotor. 16. A gas turbine engine in accordance with claim 15 further comprising: a support ring coupled to said second plurality of turbine blades such that said plurality of bearings rotatably support said support ring; and a support member rotatably coupled to at least one of said plurality of bearings and to said turbine mid-frame. 17. A gas turbine engine in accordance with claim 15 wherein said plurality of bearings are spaced approximately equidistantly about an inner periphery of said outer rotor. 18. A gas turbine engine in accordance with claim 15 wherein at least one of said plurality of bearings comprises at least one of a foil bearing, a needle bearing, and a ball bearing. 19. A gas turbine engine in accordance with claim 15 further comprising: at least one support member securedly coupled to said turbine mid-frame; and at least one bearing rotatably coupled to said support member such that said bearing supports a forward end of said outer rotor. 20. A gas turbine engine in accordance with claim 15 further comprising: a first seal member coupled to said at least one support member in sealing contact between said support assembly and said turbine mid-frame; a second seal member coupled to said support member in sealing contact between said support member and an inner rotor shaft, wherein said first and second seal members define a cavity between said turbine mid-frame, said outer rotor, and said inner rotor shaft; and at least one bearing rotatably coupled between said support member and said first shaft within said cavity.