(design meeting notes)
first nozzle stage: should be an impulse stage. flow goes to sonic velocity, choke flow regime, pressure drop is significant. The blades are impulse blades, and pressure drop will be very low. The air will cool, across the nozzle.
gives you a way to control mass flow
the air that strikes the blades will be much cooler because of expansion to high velocity (20% temp drop)
How many rows of blades do we need, to get expansion ratio of about 4?
may be difficult to also get it in choked flow. so we have to choose between first or second stage being in chocked flow.
inlet manifold and nozzle must have about double the flow area, compared to those of the first stage
challenge: peak temperature is on the second stage, rather than the first stage. does this mean that impulse blades should be used here, rather than reactive blades?
Constant air mass flow
power varies by varying turbine inlet temperature. so when running at part load, these types of turbines will be inefficient.
Turbine casing width must stay below 3.5 m, to remain rail-transportable, excluding the external combustor, which connects via a flange
Combutor cooling flow:
420+1300 -> 670
torrous: you want to keep the velocity constant, so that you don’t have to accelerate and decelerate, and you get constant pressure
applies to inlet plenum upstream of each of the two turbine nozzles. also applies to the outlet plenum on the reactor vessel.
Cold Air Line
what is the design assumption on the diameter of the cold air pipe? also, need to transition to higher diameter, because we shift to insulated piping
need to rotate around so it comes off the bottom
Hot Air Line
add the extension
- adding notes in wordpress
- design of torrous
- posting edrawing of latest design