초록 ▼

A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition d

A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct includes fairings extending between platforms for channeling the combustion gases to the low pressure turbine with corresponding swirl. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation.

대표청구항 ▼

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A turbofan engine comprising: a fan, compressor, combustor, high pressure (HP) turbine (HPT), and multistage low pressure (L

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A turbofan engine comprising: a fan, compressor, combustor, high pressure (HP) turbine (HPT), and multistage low pressure (LP) turbine (LPT) joined in serial flow communication for sequentially pressurizing air in said fan and compressor to generate combustion gases in said combustor from which energy is extracted in said HPT and LPT; said compressor being joined to said HPT by a first rotor, and said fan being joined to said LPT by a second rotor; said HPT including two stages of HP rotor blades therein joined to said first rotor, with the second stage HP blades having an acute twist angle to effect a corresponding acute angle exit swirl in said combustion gases discharged therefrom; a transition duct disposed between said HPT and LPT, and including a row of fairings extending radially in span between radially outwardly inclined outer and inner platforms for channeling said combustion gases from said HPT to said LPT with corresponding acute swirl; said LPT including a first stage LP nozzle directly following said transition duct and being higher in radial elevation than said second stage HP blades, and having a row of first stage LP vanes extending radially in span between outer and inner bands, and followed in turn by a row of first stage LP blades joined to said second rotor; and said LP blades being oriented oppositely to said HP blades for counterrotating said first and second rotors. 2. An engine according to claim 1 wherein: said f airings have leading edges and a collective inlet flow area therebetween, and trailing edges and a collective outlet flow area therebetween; and said trailing edges of said fairings are higher in radial elevation than said leading edges, and extend in radial span so that said outlet flow area is greater than said inlet flow area for increasing swirl of said combustion gases between said HPT and said LPT. 3. An engine according to claim 2 wherein: said fairings have an acute twist angle, and said first stage LP vanes have an acute twist angle corresponding in orientation with said twist angle of said second stage HP blades; and said first stage LP blades have an acute twist angle oriented oppositely to said first stage LP vanes for effecting counterrotation of said first and second rotors. 4. An engine according to claim 3 further comprising a midframe disposed between said HPT and said LPT, and including a plurality of struts extending radially through corresponding ones of said fairings, and said fairings are wide at said struts and converge aft toward said first stage LP nozzle. 5. An engine according to claim 4 wherein said fairing trailing edges at said inner platform are higher in radial elevation than said fairing leading edges at said outer platform. 6. An engine according to claim 5 wherein: said outer and inner bands of said first stage LP nozzle are inclined radially outwardly between leading and trailing edges of said vanes; and said trailing edges of said vanes are disposed higher in radial elevation at said outer band than said leading edges thereof. 7. An engine according to claim 6 wherein said trailing edges of said first stage LP vanes are tilted upstream at said outer band, and said vanes have an axial width at said outer band being no greater than about the axial width of said vanes at said inner band. 8. An engine according to claim 6 wherein said fairing trailing edges are shorter in radial span than said fairing leading edges. 9. An engine according to claim 6 wherein said second stage HP blades have a total blade count about half of the total vane count of said first stage LP nozzle and about five times the total fairing count of said transition duct. 10. An engine according to claim 6 further comprising: a fan nacelle surrounding said fan and having a fan outlet; and a core cowl surrounding said compressor, combustor, HPT, and LPT, and having a core outlet, said cowl extending through said nacelle to define a bypass duct terminating at said fan outlet forward of said core outlet. 11. A turbofan engine comprising: a fan, compressor, combustor, high pressure (HP) turbine (HPT), and multistage low pressure (LP) turbine (LPT) joined in serial flow communication for sequentially pressurizing air in said fan and compressor to generate combustion gases in said combustor from which energy is extracted in said HPT and LPT; said compressor being joined to said HPT by a first rotor, and said fan being joined to said LPT by a second rotor; said HPT including two stages of HP rotor blades therein joined to said first rotor, with the second stage HP blades having an acute twist angle to effect a corresponding acute angle exit swirl in said combustion gases discharged therefrom; a transition duct disposed between said HPT and LPT, and including a row of fairings extending radially in span between radially outwardly inclined outer and inner platforms for channeling said combustion gases from said HPT to said LPT with corresponding acute swirl; said LPT including a first stage LP nozzle directly following said transition duct and having a row of first stage LP vanes extending radially in span between outer and inner bands, and followed in turn by a row of first stage LP blades joined to said second rotor; and said LP blades being oriented oppositely to said HP blades for counterrotating said first and second rotors. 12. An engine according to claim 11 wherein: said first stage LP nozzle is higher in radial elevation than said second stage HP blades; and said transition duct increases in radial elevation and flow area between said HPT and said LPT for increasing swirl of said combustion gases therebetween. 13. An engine according to claim 12 wherein: said fairings have an acute twist angle, and said first stage LP vanes have an acute twist angle corresponding in orientation with said twist angle of said second stage HP blades; and said first stage LP blades have an acute twist angle oriented oppositely to said first stage LP vanes for effecting counterrotation of said first and second rotors. 14. An engine according to claim 13 wherein: said fairings have leading edges and a collective inlet flow area therebetween, and trailing edges and a collective outlet flow area therebetween; and said trailing edges of said fairings are higher in radial elevation than said leading edges, and extend in radial span so that said outlet flow area is greater than said inlet flow area. 15. An engine according to claim 14 wherein said fairing trailing edges are shorter in radial span than said fairing leading edges. 16. An engine according to claim 14 wherein said fairing trailing edges at said inner platform are higher in radial elevation than said fairing leading edges at said outer platform. 17. An engine according to claim 14 wherein said first stage LP vanes are tilted upstream at said outer band. 18. An engine according to claim 17 wherein: said outer and inner bands of said first stage LP nozzle are inclined radially outwardly between leading and trailing edges of said vanes; and said trailing edges of said vanes are disposed higher in radial elevation at said outer band than said leading edges thereof. 19. An engine according to claim 18 wherein said trailing edges of said first stage LP vanes are tilted upstream at said outer band, and said vanes have an axial width at said outer band being no greater than about the axial width of said vanes at said inner band. 20. An engine according to claim 14 further comprising a midframe disposed between said HPT and said LPT, and including a plurality of struts extending radially through corresponding ones of said fairings, and said fairings are wide at said struts and converge aft toward said first stage LP nozzle. 21. An engine according to claim 14 wherein said second stage HP blades have a total blade count about half of the total vane count of said first stage LP nozzle and about five times the total fairing count of said transition duct.