IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0724863
(2010-03-16)
|
등록번호 |
US-8671696
(2014-03-18)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
18 |
초록
▼
A turbine arrangement is provided for use in a gas turbine engine that includes a combustion chamber and a nozzle. The turbine arrangement includes a source of liquid and a turbine blade assembly that is rotatable about a central shaft. The blade assembly further includes a plurality of turbine blad
A turbine arrangement is provided for use in a gas turbine engine that includes a combustion chamber and a nozzle. The turbine arrangement includes a source of liquid and a turbine blade assembly that is rotatable about a central shaft. The blade assembly further includes a plurality of turbine blades, the blade having a forward edge that faces the combustion chamber and an opposite rear edge. A hollow interior of at least one blade is in fluid communication with the source of liquid. The blade (e.g. a rear edge thereof) including a plurality of openings in communication with the hollow interior and sized to produce liquid droplets for discharge downstream of the turbine blade to generate a gas (e.g., steam) due to contact with hot gases generated by the combustion chamber. The rotation of the turbine blades and discharge of the liquid in droplet form causes the liquid droplets to travel in a non-linear pattern resulting in conversion of the liquid droplets to the gas and an increase in volume for the hot gases, thereby resulting in the hot gases leaving the nozzle with increased thrust.
대표청구항
▼
1. A turbine arrangement for use in a gas turbine engine that includes a combustion chamber comprising: a source of liquid; anda turbine blade assembly that is rotatable about a central shaft, the blade assembly including a plurality of turbine blades, each blade having a forward edge that faces the
1. A turbine arrangement for use in a gas turbine engine that includes a combustion chamber comprising: a source of liquid; anda turbine blade assembly that is rotatable about a central shaft, the blade assembly including a plurality of turbine blades, each blade having a forward edge that faces the combustion chamber and an opposite rear edge, wherein a hollow interior of at least one blade has a fluid conduit formed therein that is in fluid communication with the source of liquid to permit the liquid to flow along the fluid conduit within the blade, the blade including a plurality of openings in direct communication with the fluid conduit formed in the blade, the plurality of openings being open along an exterior surface of the blade and sized to produce liquid droplets as a result of the liquid being forced through the openings under pressure to create the liquid droplets for discharge downstream of the turbine blade to generate a gas due to contact with hot gases generated by the combustion chamber;wherein the rotation of the turbine blades and discharge of the liquid in droplet form from the rotating blades causes the liquid droplets to travel in a non-linear pattern resulting in conversion of the liquid droplets to a gas and an increase in volume for the hot gases, thereby resulting in the hot gases leaving an exhaust section with increased thrust. 2. The turbine arrangement of claim 1, wherein a size of the liquid droplet is approximately 10 microns. 3. The turbine arrangement of claim 1, wherein the liquid is selected from the group consisting of water, water-methanol mixture, hydrocarbon fuel, methanol and mixtures thereof. 4. The turbine arrangement of claim 1, wherein the gas turbine engine is part of a jet engine assembly. 5. The turbine arrangement of claim 1, wherein the liquid is delivered under pressure to the turbine blade. 6. The turbine arrangement of claim 1, wherein the exhaust section comprises a nozzle is operatively connected to an energy extraction or turbine device to produce increased efficient usage of the hot gases exhausted by the nozzle. 7. The turbine arrangement of claim 1, including a liquid inlet that is in fluid communication with the source of liquid, the liquid inlet being in fluid communication with a channel formed in the shaft that is also in fluid communication with the interior of the blade such that the liquid flows through the inlet, the channel in the shaft and into the blade before being discharged therefrom. 8. The turbine arrangement of claim 7, wherein the liquid inlet is sealingly coupled to the shaft. 9. A turbine arrangement for use in a gas turbine engine that includes a combustion chamber comprising: a source of liquid;a turbine blade assembly that is rotatable about a central shaft, the blade assembly including a plurality of turbine blades, each blade having a forward edge that faces the combustion chamber and an opposite rear edge, wherein a hollow interior of at least one blade is in fluid communication with the source of liquid, the blade including a plurality of openings in communication with the hollow interior and sized to produce liquid droplets for discharge downstream of the turbine blade to generate a gas due to contact with hot gases generated by the combustion chamber; andan impinging surface that is located downstream of where the liquid droplets are discharged to provide a surface that acts on the swirling droplets to cause the droplets to evaporate quicker;wherein the rotation of the turbine blades and discharge of the liquid in droplet form from the rotating blades causes the liquid droplets to travel in a non-linear pattern resulting in conversion of the liquid droplets to a gas and an increase in volume for the hot gases, thereby resulting in the hot gases leaving an exhaust section with increased thrust. 10. The turbine arrangement of claim 9, wherein the impinging surface is stationary relative to the rotating components of the turbine. 11. A turbine arrangement for use in a gas turbine engine that includes a combustion chamber comprising: a source of liquid;a rotatable shaft that is coupled to a turbine housing, the shaft being stationary relative to the housing, the shaft including a liquid inlet member that is in fluid communication with the source of liquid and a channel for routing the liquid within and along a length of the shaft;a bearing/seal assembly including a bearing that is in intimate contact with the shaft and includes an opening that is aligned with the shaft channel so that the liquid can flow therein from the shaft, the assembly further including a bushing that is in intimate contact with the bearing and includes an opening that is aligned with the opening of the bearing to allow the liquid to flow therein in a direction radially outward from the shaft;at least one rotatable member that is sealingly coupled to the bushing and includes a channel formed internally therein, the channel being fluidly connected to the opening in the bushing to allow the liquid flowing within the bushing to flow into the channel, the channel being in fluid communication with a plurality of outlet ports formed within the rotatable member, the outlet ports being sized to produce liquid droplets for discharge downstream of the rotatable member to generate gas due to contact with hot gases generated by the combustion chamber;wherein the rotation of the rotatable member and discharge of the liquid in droplet form causes the liquid droplets to travel in a non-linear, swirling pattern resulting in conversion of the liquid droplets to gas and an increase in volume for the hot gases, thereby resulting in the hot gases flowing downstream of the rotatable member with increased thrust. 12. The turbine arrangement of claim 11, wherein the discharge openings are formed to create approximately 10 micron sized liquid droplets. 13. The turbine arrangement of claim 11, wherein the discharge openings are formed along the trailing edge of the rotatable member. 14. The turbine arrangement of claim 11, further including: means for introducing air to support combustion, the air being delivered into the turbine arrangement to improve combustion by by-pass or other means. 15. The turbine arrangement of claim 11, wherein the liquid is selected from the group consisting of a heavy oil, a slurry of coal dust, water, methanol and a hydrocarbon in whole or part. 16. The turbine arrangement of claim 11, wherein the engine is of a by-pass air type where air flows around and beyond the turbine. 17. The turbine arrangement of claim 11, wherein the at least one rotatable member comprises a free wheeling structure that rotates due to impinging gas flow. 18. A turbine arrangement for use in a gas turbine engine that includes a combustion chamber and a nozzle comprising: a source of liquid;a liquid inlet member that is in fluid communication with the source of liquid; anda turbine blade assembly that is rotatable about a central shaft, wherein the liquid inlet member is sealingly coupled to the shaft, the blade assembly including a plurality of turbine blades, the blade having a forward edge that faces the combustion chamber and an opposite rear edge, wherein the central shaft includes at least one main channel that is in fluid communication with the liquid inlet member for receiving liquid therefrom, the central shaft further including a plurality of secondary channels each of which is in communication with the main channel and terminates in an opening formed at a rotating end of the central shaft, the opening being sized to produce liquid droplets for discharge downstream of the turbine blade to generate a gas due to contact with hot gases generated by the combustion chamber;wherein the rotation of the central shaft and discharge of the liquid in droplet form causes the liquid droplets to travel in a non-linear pattern resulting in conversion of the liquid droplets to gas and an increase in volume for the hot gases, thereby resulting in the hot gases leaving the nozzle with increased thrust. 19. A turbine arrangement for use in a gas turbine engine that includes a combustion chamber comprising: a source of liquid;a main turbine blade assembly that includes a first rotating shaft and a turbine blade section coupled to and rotating with the first rotating shaft;a second shaft assembly downstream of the main turbine blade assembly, the second shaft assembly including a second rotating shaft that is independent and spaced from the first rotating shaft, the second shaft assembly including a protrusion that extends radially outward from the second rotating shaft and rotates therewith, the protrusion having a forward edge that faces the combustion chamber and an opposite rear edge, wherein a hollow interior of the protrusion is in fluid communication with the source of liquid, the protrusion including a plurality of openings that are open along an exterior surface thereof and are in fluid communication with the hollow interior and sized to produce liquid droplets for discharge downstream of the protrusion to generate a gas due to contact with hot gases generated by the combustion chamber;a mechanical drive unit operatively coupled to the second rotating shaft for rotating the second rotating shaft;a liquid inlet that is in fluid communication with the source of liquid, the liquid inlet being in fluid communication with a channel formed in the second rotating shaft, the channel being in fluid communication with the interior of the protrusion such that the liquid flows through the inlet, through the channel in the second rotating shaft and into the hollow interior of the protrusion before being discharged through the openings formed in the protrusion;wherein rotation of the second rotating shaft and discharge of the liquid in droplet form from the protrusion, which rotates with the second rotating shaft, causes the liquid droplets to travel in a non-linear pattern resulting in conversion of the liquid droplets to a gas and an increase in volume for the hot gases, thereby resulting in the hot gases leaving an exhaust section with increased thrust. 20. The turbine arrangement of claim 19, wherein a housing of the mechanical drive unit is sealingly coupled to the second rotating shaft by means of a seal bearing unit. 21. The turbine arrangement of claim 19, wherein the liquid inlet includes a channel section formed in the mechanical drive unit, the channel section being in fluid communication with the channel in the second rotating shaft to allow fluid to flow through the mechanical drive unit into the second rotating shaft. 22. The turbine arrangement of claim 19, wherein the mechanical drive unit includes a gear that is operatively connected to the second rotating shaft to translate actuation of the mechanical drive unit into rotation of the second rotating shaft. 23. The turbine arrangement of claim 19, wherein the second rotating shaft is configured to be driven at least one of a different speed and a different direction relative to the first rotating shaft. 24. The turbine arrangement of claim 19, wherein the mechanical drive unit includes a motor for rotating the second rotating shaft. 25. The turbine arrangement of claim 19, wherein the protrusion comprises one of: (1) a plurality of blades that extend radially outward from the second rotating shaft, at least one blade having an internal channel that receives the liquid from the second rotating shaft, the at least one blade having a plurality of openings that are open along an exterior surface thereof and are in communication with the internal channel to allow discharge of the liquid; and (2) a nozzle having an opening for discharging the liquid. 26. A turbine arrangement for use in a gas turbine engine that includes a combustion chamber comprising: a source of liquid;a main turbine blade assembly that includes a first rotating shaft and a turbine blade section coupled to and rotating with the first rotating shaft;a second shaft assembly downstream of the main turbine blade assembly, the second shaft assembly including a second rotating shaft that is independent and spaced from the first rotating shaft, the second shaft assembly including a protrusion that extends radially outward from the second rotating shaft and rotates therewith, the protrusion having a hollow interior that is in fluid communication with the source of liquid, the protrusion having a plurality of openings formed therein that are open along an exterior surface thereof and are in fluid communication with the hollow interior and sized to produce liquid droplets for discharge downstream of the protrusion to generate a gas due to contact with hot gases generated by the combustion chamber;a housing at least partially surrounding the second rotating shaft, the housing being sealingly coupled to the second rotating shaft by means of a seal bearing unit to permit the second rotating shaft to rotate relative to the housing;a liquid inlet formed in the housing and in fluid communication with the source of liquid, the liquid inlet being in fluid communication with a channel formed in the second rotating shaft, the channel in the second rotating shaft being in fluid communication with the hollow interior of the protrusion such that the liquid flows through the inlet, through the channel in the second rotating shaft and into the hollow interior of the protrusion before being discharged through the openings formed in the protrusion;wherein rotation of the second rotating shaft and discharge of the liquid in droplet form from the protrusion, which rotates with the second rotating shaft, causes the liquid droplets to travel in a non-linear pattern resulting in conversion of the liquid droplets to a gas and an increase in volume for the hot gases, thereby resulting in the hot gases leaving an exhaust section with increased thrust. 27. The turbine arrangement of claim 26, wherein the protrusion comprises a plurality of blades that extend radially outward from the second rotating shaft, at least one blade having an internal channel that receives the liquid from the second rotating shaft, the at least one blade having a plurality of openings that are open along an exterior surface thereof and are in communication with the internal channel to allow discharge of the liquid, wherein the second shaft assembly including the plurality of blades is a free wheeling structure that rotates due to impinging gas flow. 28. The turbine arrangement of claim 26, wherein the protrusion comprises a nozzle piece that is rotated due to gas flow.
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