A jet engine includes a fan arranged upstream of a core engine having a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, and a low pressure turbine. The high pressure turbine is drive-connected to the high pressure compressor. The low pressure turb
A jet engine includes a fan arranged upstream of a core engine having a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine, and a low pressure turbine. The high pressure turbine is drive-connected to the high pressure compressor. The low pressure turbine is drive-connected through a transmission to the low pressure compressor and to the fan, which are respectively driven in opposite rotation directions. A compressor disk of the low pressure compressor is positioned downstream directly after the fan so that a hub end section of the fan and the compressor disk together form a counter-rotating compressor stage.
대표청구항▼
What is claimed is: 1. A jet engine comprising: a fan; a low pressure compressor including a low pressure compressor rotor having at least a first compressor disk; a high pressure compressor; a combustion chamber; a high pressure turbine; a low pressure turbine; a first drive line connecting said h
What is claimed is: 1. A jet engine comprising: a fan; a low pressure compressor including a low pressure compressor rotor having at least a first compressor disk; a high pressure compressor; a combustion chamber; a high pressure turbine; a low pressure turbine; a first drive line connecting said high pressure turbine to said high pressure compressor; a second drive line connecting said low pressure turbine to said low pressure compressor and to said fan; and an engine housing defining therein a core engine flow passage passing through said fan, said low pressure compressor, said high pressure compressor, said combustion chamber, said high pressure turbine, and said low pressure turbine; wherein said first compressor disk is arranged downstream directly after said fan in a flow direction along said core engine flow passage so that a hub-end section of said fan and said first compressor disk together form a counter-rotating compressor stage. 2. The jet engine according to claim 1, wherein said low pressure compressor is a single-stage compressor, and said first compressor disk is a single only rotor disk comprised by said low pressure compressor rotor. 3. The jet engine according to claim 1, excluding a bearing spider between said fan and said first compressor disk. 4. The jet engine according to claim 1, excluding all mechanical components in a space in said core engine flow passage between said fan and said first compressor disk. 5. The jet engine according to claim 1, having a floating support arrangement of said fan and said low pressure compressor rotor relative to one another. 6. The jet engine according to claim 1, wherein said second drive line includes a first output shaft connected to said fan, and a second output shaft connected to said low pressure compressor rotor and arranged coaxially around said first output shaft, and further comprising a rotation bearing coaxially between said first and second output shafts. 7. The jet engine according to claim 1, wherein said second drive line includes a transmission that is so constructed and so couples said fan and said low pressure compressor such that said fan and said low pressure compressor have respective opposite rotation directions relative to one another. 8. The jet engine according to claim 7, wherein said transmission is so constructed such that said fan has a same rotation direction as said low pressure turbine, and said low pressure compressor has an opposite rotation direction as said low pressure turbine. 9. The jet engine according to claim 7, wherein said transmission is arranged on an opposite side of said low pressure compressor from said fan. 10. The jet engine according to claim 7, wherein said transmission is so constructed such that said fan and said low pressure compressor and said low pressure turbine respectively have different rotation speeds relative to one another. 11. The jet engine according to claim 7, wherein said transmission is a planetary gearing transmission. 12. The jet engine according to claim 7, wherein said transmission is a differential planetary gearing transmission. 13. The jet engine according to claim 1, further comprising a fan housing that surrounds said fan and said engine housing and that defines a bypass flow passage between said fan housing and said engine housing, and wherein said fan comprises a fan rotor disk with fan blades and a flow guide element that separates said bypass flow passage from said core engine flow passage. 14. The jet engine according to claim 13, wherein said flow guide element is a flow divider. 15. The jet engine according to claim 13, wherein said flow guide element is arranged on said fan blades at a location aligning with a forward end of said engine housing, and said flow guide element transitions aerodynamically smoothly into said forward end of said engine housing. 16. A jet engine comprising: a fan; a low pressure compressor including a low pressure compressor rotor having at least a first compressor disk; a high pressure compressor; a combustion chamber; a high pressure turbine; a low pressure turbine; a first drive line connecting said high pressure turbine to said high pressure compressor; a second drive line connecting said low pressure turbine to said low pressure compressor and to said fan; an engine housing defining therein a core engine flow passage passing through said fan, said low pressure compressor, said high pressure compressor, said combustion chamber, said high pressure turbine, and said low pressure turbine; and a fan housing that surrounds said fan and said engine housing and that defines a bypass flow passage between said fan housing and said engine housing; wherein said first compressor disk is arranged downstream directly after said fan in a flow direction along said core engine flow passage so that a hub-end section of said fan and said first compressor disk together form a counter-rotating compressor stage; and wherein said fan comprises a fan rotor disk with fan blades and a flow guide element that separates said bypass flow passage from said core engine flow passage. 17. A jet engine comprising: a fan; a low pressure compressor including a low pressure compressor rotor having at least a first compressor disk; a high pressure compressor; a combustion chamber; a high pressure turbine; a low pressure turbine; a first drive line connecting said high pressure turbine to said high pressure compressor; a second drive line connecting said low pressure turbine to said low pressure compressor and to said fan; and an engine housing defining therein a core engine flow passage passing through said fan, said low pressure compressor, said high pressure compressor, said combustion chamber, said high pressure turbine, and said low pressure turbine; wherein said first compressor disk is arranged downstream directly after said fan in a flow direction along said core engine flow passage so that a hub-end section of said fan and said first compressor disk together form a counter-rotating compressor stage; and excluding all mechanical components in a space in said core engine flow passage between said fan and said first compressor disk.
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이 특허에 인용된 특허 (1)
Adamson Arthur P. (Cincinnati OH) Butler Lawrence (Cincinnati OH) Wall Robert A. (Wyoming OH), Geared counterrotating turbine/fan propulsion system.
Merry, Brian D.; Suciu, Gabriel L.; Brilliant, Lisa I.; Rose, Becky E.; Dong, Yuan; Balamucki, Stanley J., LPC flowpath shape with gas turbine engine shaft bearing configuration.
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