A gas turbine apparatus may include one or more driving shafts; a compressor configured to receive power from the one or more driving shafts, suck air, and compress the sucked air at high pressure. The gas turbine may include a combustor configured to mix the compressed air with fuel, and combust th
A gas turbine apparatus may include one or more driving shafts; a compressor configured to receive power from the one or more driving shafts, suck air, and compress the sucked air at high pressure. The gas turbine may include a combustor configured to mix the compressed air with fuel, and combust the fuel mixture to generate combustion gas. A turbine is connected to the one or more driving shafts and is configured to rotate while the combustion gas passes through the turbine. The turbine may include one or more first turbine blades configured to rotate in a first direction and one or more second turbine blades configured to rotate in a second direction opposite to the first direction. The one or more first turbine blades and the one or more second turbine blades may be alternately arranged along an axial direction of the turbine.
대표청구항▼
1. A gas turbine apparatus comprising: a first driving shaft;a second driving shaft;a compressor configured to receive power from the first and second driving shafts, suck air, and compress the sucked air at high pressure;a combustor configured to mix the compressed air with fuel, and combust the fu
1. A gas turbine apparatus comprising: a first driving shaft;a second driving shaft;a compressor configured to receive power from the first and second driving shafts, suck air, and compress the sucked air at high pressure;a combustor configured to mix the compressed air with fuel, and combust the fuel mixture to generate combustion gas; anda turbine connected to the first and second driving shafts and configured to rotate while the combustion gas passes through the turbine,the turbine comprising one or more first turbine blades configured to rotate in a first direction and one or more second turbine blades configured to rotate in a second direction opposite to the first direction,the one or more first turbine blades and the one or more second turbine blades being alternately arranged along an axial direction of the turbine,the first driving shaft connected to each of the first turbine blades and the second driving shaft connected to each of the second turbine blades,the first turbine blade including a first blade part having a rear end,the second turbine blade including a second blade part having a front end, anda distance from a central-axis line of the first driving shaft to the rear end of the first blade part is substantially equal to a distance from the central-axis line of the first driving shaft to the front end of the second blade part. 2. The gas turbine apparatus according to claim 1, wherein no turbine vane is provided between the first turbine blade and the second turbine blade. 3. The gas turbine apparatus according to claim 1, wherein the first driving shaft is provided as an inner shaft, and the second driving shaft is provided as an outer shaft surrounding at least a portion of the inner shaft. 4. The gas turbine apparatus according to claim 3, wherein a rear end of the first turbine blade is fixed to the first driving shaft, and a front end of the first turbine blade protrudes toward the second driving shaft, anda rear end of the second turbine blade is fixed to the second driving shaft, and a front end of the second turbine blade protrudes toward the first driving shaft. 5. The gas turbine apparatus according to claim 4, wherein the first blade part is configured to contact the combustion gas while the combustion gas passes through the first blade part, andthe second turbine blade is configured to contact the combustion gas having passed through the first blade part while the combustion gas passes through the second blade part. 6. The gas turbine apparatus according to claim 4, wherein a distance from a central-axis line of the first driving shaft to the front end of the first blade part is substantially equal to a distance from the central-axis line of the first driving shaft to the rear end of the second blade part. 7. The gas turbine apparatus according to claim 3, wherein the compressor comprises one or more first compressor blades configured to rotate in the first direction and one or more second compressor blades configured to rotate in the second direction, andthe one or more first compressor blades and the one or more second compressor blades are alternately arranged in an axial direction of the compressor. 8. The gas turbine apparatus according to claim 7, wherein no vane is provided between the first compressor blade and the second compressor blade. 9. The gas turbine apparatus according to claim 7, wherein the first compressor blade is connected to the first driving shaft, and the second compressor blade is connected to the second driving shaft. 10. The gas turbine apparatus according to claim 7, wherein a rear end of the first compressor blade is fixed to the first driving shaft and a front end of the first compressor blade protrudes toward the second driving shaft, anda rear end of the second compressor blade is fixed to the second driving shaft and a front end of the second compressor blade protrudes toward the first driving shaft. 11. The gas turbine apparatus according to claim 1, further comprising: a blower fan disposed at the front end of the compressor. 12. The gas turbine apparatus according to claim 11, wherein the one or more first turbine blades comprise a plurality of first turbine blades;the one or more second turbine blades comprise a plurality of second turbine blades; andthe apparatus further comprises a third driving shaft connecting one of the plurality of second turbine blades to the blower fan. 13. The gas turbine apparatus according to claim 12, wherein the one of the plurality of second turbine blades is provided at the rearmost end in a flow direction of the combustion gas. 14. A gas turbine apparatus comprising: a first driving shaft;a compressor configured to be driven by the first driving shaft;a combustor configured to combust a fuel mixture of fuel and air compressed by the compressor;a plurality of first turbine blades configured to be driven by the first driving shaft and expanding combustion gas from the combustor;a plurality of second turbine blades configured to further expand combustion gas from the first turbine blades; anda second driving shaft supporting the second turbine blades, and configured to rotate in an opposite direction to rotation of the first driving shaft, and the second driving shaft having a space for receiving the first turbine blades therein,the first driving shaft connected to each of the first turbine blades and the second driving shaft connected to each of the second turbine blades,each of the first turbine blades including a first blade part having a rear end,each of the second turbine blades including a second blade part having a front end, anda distance from a central-axis line of the first driving shaft to the rear end of the first blade part is substantially equal to a distance from the central-axis line of the first driving shaft to the front end of the second blade part. 15. The gas turbine apparatus of claim 14, wherein the second driving shaft is concentrically disposed with the first driving shaft. 16. The gas turbine apparatus of claim 14, wherein the compressor includes: a plurality of first compressor blades configured to be driven by the first driving shaft; anda plurality of second compressor blades configured to further compress air from the first compressor blades and engage with the second driving shaft. 17. The gas turbine apparatus of claim 14, further comprising: a blower fan disposed at the front end of the compressor. 18. The gas turbine apparatus according to claim 17, further comprising: a third driving shaft connecting one of the plurality of second turbine blades to the blower fan. 19. The gas turbine apparatus according to claim 18, wherein the one of the plurality of second turbine blades is provided at the rearmost end in a flow direction of the combustion gas.
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이 특허에 인용된 특허 (4)
Gruner George P. (13 Bradley Rd. Andover MA 01810), Contra-rotating rotors with differential gearing.
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