Patent Application
20140072401
The invention relates generally to gas turbines and, more specifically, to an axial diffuser in a gas turbine including a plasma controller to control air flow.
Conventional gas turbine combustion systems employ multiple combustion chamber assemblies to achieve reliable and efficient turbine operation. Each combustion chamber includes a cylindrical combustor, a fuel injection system, and a transition piece that guides the flow of the hot gas from the combustor to the inlet of the turbine. Generally, a portion of the compressor discharge air is introduced directly into the combustor reaction zone to be mixed with the fuel and burned. The balance of the airflow serves either to quench the flame prior to the combustor discharge entering the turbine, or to cool the wall of the combustor and, in some cases, the transition piece.
In systems incorporating impingement cooled transition pieces, a hollow sleeve surrounds the transition piece, and the sleeve wall is perforated so that compressor discharge air will flow through the cooling apertures in the sleeve wall and impinge upon (and thus cool) the transition piece.
Because the transition piece is a structural member, it is desirable to have lower temperatures where the stresses are highest. This has proven difficult to achieve, but an acceptable compromise is to have uniform temperatures (at which the stresses are within allowable limits) all along the length of the transition piece. Thus, uniform flow pressures along the impingement sleeve are desirable to achieve the desired uniform temperatures.
Substantially straight axial diffusers are typically utilized in gas turbines at the compressor discharge location.
A typical problem associated with existing diffuser configurations is flow separation. The flow gets detached from the surface creating losses and reducing pressure recovery. Efforts have been made to have an aggressive design of the diffuser for reducing its length of providing a steeper angle and by diverging the annulus in two stages. The steeper angle, however, creates more flow separation, thereby reducing the pressure recovery. Current methods of flow control are achieved by mechanical means, which are complicated, add weight, have volume and are sources of noise and vibration. Also, existing devices are typically composed of mechanical parts that wear away and that may break down.
It would be desirable to eliminate the problems with existing devices while effectively controlling the flow profile.
In an exemplary embodiment, an axial diffuser for a gas turbine includes diffuser walls that define diffuser channels receiving compressor discharge air. The diffuser walls diverge in a flow direction. A flow control device is disposed in the diffuser channels. The flow control device includes a plasma controller that serves to ionize airflow in the diffuser channels.
In another exemplary embodiment, a flow control device is cooperable with an axial diffuser in a gas turbine and includes the plasma controller that serves to ionize airflow through the axial diffuser.
In still another exemplary embodiment, a method of controlling flow in a gas turbine axial diffuser includes the steps of positioning a flow control device in diffuser channels of the axial diffuser, where the flow control device includes a plasma controller; and applying a current to the plasma controller to ionize airflow in the diffuser channels.
Generally, the combustion section 150 includes a plurality of combustion cans 155 (only one is illustrated), a plurality of fuel nozzles 160, and a plurality of transition sections 165 (only one is illustrated). The plurality of combustion cans 155 may be coupled to a fuel source (not illustrated). Within each combustion can 155, compressed air is received from the compressor section 105 and mixed with fuel received from the fuel source. The air and fuel mixture is ignited and creates a working fluid. The working fluid generally proceeds from the aft end of the plurality of fuel nozzles 160 downstream through the transition section 165 into the turbine section 180.
Generally, the turbine section 180 includes a plurality of rotating components 185, a plurality of stationary components 190, and a plurality of wheelspace areas 195. The turbine section 180 converts the working fluid to a mechanical torque.
Typically, during the operation of the gas turbine 100, a plurality of components experience high temperatures and may require cooling or purging. These components may include a portion of the compressor section 105, the marriage joint 135, and the plurality of wheelspace areas 195.
The extraction port 120 draws cooling fluid from the compressor section 105. The cooling fluid bypasses the combustion section 150, and flows through a cooling circuit 200 (illustrated in
An axial diffuser 12 is provided at the compressor discharge location to distribute compressor discharge air along the impingement sleeve surrounding the transition piece. The axial diffuser 12 includes diffuser walls that define diffuser channels 14 that receive the compressor discharge air. As shown, the diffuser walls diverge in a flow direction (shown by arrows in
In use, the fluid/air in the diffuser will get ionized, and in ambient air, an electric wind is created tangentially to the diffuser wall. The effect is used to reduce the flow separation, providing effective flow control and reduced pressure drop. As shown, the electrodes can be mounted to the inner surface of the axial diffuser casing.
The air flow direction can be altered in different channels based on the aerodynamic shape of the diffuser, hence making the airflow conform to the shape of the diffuser. Moreover, a decreased amount of air during reduced load on the turbine can be made to accelerate through the diffuser to thereby further control turbine performance. Additionally, redirecting the amount and the nature of the flow may serve to control the impingement of air on the combustion hardware.
An exemplary plasma controller 2 is illustrated in
When the current amplitude is large enough, the gas flow 19 ionizes in a region of largest electric potential forming the plasma 90. The plasma controller 2 produces an outer surface conforming plasma 90 which covers a substantial portion of the diffuser channels. The plasma 90 generally begins at an edge 102 of the first electrode 3, which is exposed to the gas flow 19, and spreads out over an area 104 projected by the second electrode 4, which is covered by the dielectric material 5. The plasma 90 in the presence of an electric field gradient produces a force on the gas flow 19 located between the diffuser surface and the plasma 90 inducing a virtual aerodynamic shape that causes a change in the pressure distribution over the diffuser surface.
The use of plasma flow control in an axial diffuser serves to reduce flow separation without complicated mechanical devices that add weight and can be sources of noise and vibration. Effective flow control and a reduced pressure drop can be advantageously achieved by the application of current between the plasma controller electrodes. The improved pressure recovery results in higher and more efficient power generation. Additionally, the device is suitable for retrofitting on existing turbines.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiments, it is to be understood that the invention is not to be limited to the disclosed embodiments, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
