초록 ▼

Additional thrust fuel efficiency is provided for a gas turbine system that includes a first member(s) (e.g., a support for a rotating main shaft) that is attached to a stationary casing. The rotating main shaft is attached to the first member through a bearing. A second member is associated with a

Additional thrust fuel efficiency is provided for a gas turbine system that includes a first member(s) (e.g., a support for a rotating main shaft) that is attached to a stationary casing. The rotating main shaft is attached to the first member through a bearing. A second member is associated with a rotating member, such as a motor or other rotating part of the main or other shaft. The first member has a flow path in it for the liquid (e.g. water and/or other volatile liquid) and has an opening (nozzle) for discharging the liquid. The second member has a liquid impinging member for generating a liquid spray, droplet, mist optimally, which vaporizes with hot combustion gases that flow exteriorly along the main shaft. In this form vaporization is quick and is less erosive. The volume of thrust gases is increased advantageously and likewise engine boost increases.

대표청구항 ▼

1. A gas turbine system including a casing outer part extending its length and containing a main shaft, compressor section, combustion section, a turbine section defined by a plurality of turbine blades, the system comprising: a first support structure that is stationary relative to the casing outer

1. A gas turbine system including a casing outer part extending its length and containing a main shaft, compressor section, combustion section, a turbine section defined by a plurality of turbine blades, the system comprising: a first support structure that is stationary relative to the casing outer part and extends toward the main shaft and supports the main shaft, the first support structure having a bearing associated therewith for holding the main shaft allowing for rotation of the main shaft, wherein the first support structure has at least one internal conduit formed therein for receiving a liquid and defining a flow path for the liquid through the first support structure to an exit opening formed along the first support structure, the exit opening being formed such that liquid discharged therefrom flows in a direction at least substantially parallel to the main shaft and contacts hot combustion gas that surrounds the first support structure and flows also in a direction parallel to the main shaft; anda liquid impinging member that is associated with the main shaft downstream of the exit opening, the liquid impinging member being disposed downstream of the turbine blades, the liquid impinging member rotating with and at a same speed as the main shaft, the liquid impinging member being configured and positioned to contact liquid discharged through the exit opening and cause formation of a liquid spray defined by liquid droplets of reduced size, wherein the spray travels along a swirling path, whereby the hot combustion gas created as a result of fuel burning interact with the liquid spray liquid formed by the liquid impinging member resulting in the liquid being converted into a gaseous phase as a result of consumption of heat energy thereby yielding thrust mechanical energy. 2. The system of claim 1, wherein the internal conduit of the first support structure includes a first section that is formed along a first axis that intersects a central axis about which the main shaft rotates and a second section that extends along a second axis that is parallel to the central axis. 3. The system of claim 2, wherein the exit opening is formed at an open end of the second section of the conduit and is formed along a trailing edge of the first support structure. 4. The system of claim 1, further including a spray nozzle in fluid communication with the exit opening and receiving liquid flowing through the internal conduit and discharging the liquid in spray form. 5. The system of claim 4, wherein the spray generated by the nozzle flows in a direction that is substantially parallel to a central axis about which the main shaft rotates and flows into contact with the liquid impinging member. 6. The system of claim 1, wherein the liquid impinging member comprises a protrusion that extends radially outward from the main shaft and is axially aligned with the exit opening such that the discharged liquid makes contact therewith. 7. The system of claim 6, wherein the protrusion comprises a cylindrical shaped pin. 8. The system of claim 1, wherein the liquid is selected from the group consisting of: water, a water-methanol mix, a water fuel mixture, and a volatile liquid. 9. The system of claim 1, wherein the main shaft includes a fixed annular ring that extends radially outward therefrom, the liquid impinging member extending radially outward from the fixed annular ring and having different dimensions relative to the annular ring. 10. A gas turbine system including a casing outer part extending its length and containing a main shaft, compressor section, combustion section, a turbine section defined by a plurality of turbine blades, the system comprising: a first support structure that is part of the casing outer part and extends inwardly toward the main shaft and supports the main shaft, the first support structure being disposed downstream of the combustion section of the gas turbine system, the first support structure having a bearing associated therewith for holding the main shaft allowing for rotation of the main shaft, wherein the first support structure has at least one internal conduit formed therein for receiving a liquid and defining a flow path for the liquid through the first support structure to an exit opening formed along a trailing edge of the first support structure, the exit opening being formed such that liquid discharged therefrom flows in a direction at least substantially parallel to the main shaft and contacts hot combustion gas that surrounds the first support structure and flows also in a direction parallel to the main shaft; anda liquid impinging member that is associated with the main shaft downstream of the exit opening, the liquid impinging member being a separate structure relative to the turbine blades and being spaced from the turbine blades and being located downstream of the turbine blades, the liquid impinging member rotating with the main shaft, the liquid impinging member being configured and positioned to contact liquid discharged through the exit opening and cause formation of a liquid spray defined by liquid droplets of reduced size, wherein the spray travels along a swirling path downstream of the turbine blades, whereby the hot combustion gas created as a result of fuel burning interact with the liquid spray liquid formed by the liquid impinging member resulting in the liquid being converted into a gaseous phase as a result of consumption of heat energy thereby yielding thrust mechanical energy;wherein the bearing is disposed between the exit opening and the main shaft. 11. The system of claim 10, further including a spray nozzle in fluid communication with the exit opening and receiving liquid flowing through the internal conduit and discharging the liquid. 12. The system of claim 11, wherein the liquid discharged by the nozzle flows in a direction that is substantially parallel to a central axis about which the main shaft rotates and flows into contact with the liquid impinging member. 13. The system of claim 11, wherein the spray nozzle and the liquid impinging member are oriented such that the discharged liquid flows directly toward and into contact with the liquid impinging member without obstruction since the spray nozzle directly faces the liquid impinging member without another element disposed therebetween. 14. A gas turbine system including a casing outer part extending its length and containing a main shaft, compressor section, combustion section, a turbine section defined by a plurality of turbine blades, the system comprising: a first support structure that is part of the casing outer part and extends inwardly toward the main shaft and supports the main shaft, the first support structure being disposed downstream of the combustion section of the gas turbine system, the first support structure having a bearing associated therewith for holding the main shaft allowing for rotation of the main shaft, wherein the first support structure has at least one internal conduit formed therein for receiving a liquid and defining a flow path for the liquid through the first support structure to an exit opening formed along a trailing edge of the first support structure, the exit opening being formed such that liquid discharged therefrom flows in a direction at least substantially parallel to the main shaft and contacts hot combustion gas that surrounds the first support structure and flows also in a direction parallel to the main shaft; anda liquid impinging member that is coupled to the main shaft downstream of the exit opening, the liquid impinging member being a separate structure relative to the turbine blades and being spaced and detached from the turbine blades, the liquid impinging member being disposed downstream of the turbine blades, the liquid impinging member rotating with the main shaft, the liquid impinging member being configured and positioned to contact liquid discharged through the exit opening and cause formation of a liquid spray defined by liquid droplets of reduced size, wherein the spray travels along a swirling path downstream of the turbine blades, whereby the hot combustion gas created as a result of fuel burning interact with the liquid spray liquid formed by the liquid impinging member resulting in the liquid being converted into a gaseous phase as a result of consumption of heat energy thereby yielding thrust mechanical energy;wherein the bearing is disposed between the exit opening and the main shaft.