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Pistonless Pump for Rockets full report and ppt
Post: #1

.doc  PistonlessPumpforRocket.doc.doc (Size: 320 KB / Downloads: 996)
.ppt  PISTON_LESS_PUMP_FOR_ROCKET.ppt (Size: 521 KB / Downloads: 1537)

Pistonless pump for rocket has been proved to be the most economical than piston pump or turbopump.
In pistonless pumps, piston is absent. It has very much less rotating parts than that of piston pumps or turbo pumps. So, it has less friction losses and there by it helps to improve the efficiency of the engine considerably.They can be easily installed in the rocket than turbopumps.Also,it reduces the weight of rocket.
This article discusses the working , advantages of pistonless pump over turbopump.
Pistonless pumps are 80-90% economical than that of piston pump or turbo pumps.Nasa has manufactured such kind of pump and tested it actually,and they found it works conveneiently.


NASA have developed a Low cost rocket fuel pump which has
Comparable performance to turbopump at 80-90% lower cost. Perhaps
the most difficult barrier to entry in the liquid rocket business is the
turbo pump. A turbo pump design requires a large engineering effort
and is expensive to mfg. and test. Starting a turbo pump fed rocket
engine is a complex process, requiring a careful of many valves and
subsystems.In fact ,Beal aerospace tried to avoid the issue entirely by
building a huge pressure feed booster. Their booster never flew, but the
engineering behind it was sound and ,if they had a low cost pump at
their disposal ,they might be competing against Boeing. This pump
saves up to 90% of the mass of the tanks as compared to a pressure
fed system. This pump has really proved to be a boon for rockets . By
this pump the rocket does not have to carry heavy load and can travel
with very high speed.


The turbo pumps used in rocket are very heavy,containing many
rotating parts by which there are more frictional losses which
more consumption of fuel there by decreasing the efficiency of
the engine .Also, the maintainanace of such pump is, very
important factor since the rocket has to remain stable in the
space, is difficult and require complex methods for it. If this
pump gets any fault then its repairance requires long time and also
it is avery hectic task.So, there must be such a device which
overcomes all the drawbacks of the turbopump as above. The
pistonless pump is the solution for the problems faced by using
turbopumps. They have only a drawback that they supply fuel
with less pressure as compared to turbopumps.


NASA has designed,built and tested a simple, light weight pump
(dual pistomless pump) for use in liquid propelled rocket where a
reliable pump with minimal moving parts is needed. This pump
has the potential to reduce the cost and increase the reliability of
rocket fuel pumps by a factor of 20 to 100.


Rocket engines requires a tremendous amount of fuel high
at high pressure .Often th pump costs more than the thrust
chamber.One way to supply fuel is to use the expensive
turbopump mentioned above,another way is to pressurize fuel
tank. Pressurizing a large fuel tank requires a heavy , expensive
tank. However suppose instead of pressurizing entire tank, the
main tank is drained into a small pump chamber which is then
pressurized. To achieve steady flow, the pump system consists of
two pump chambers such that each one supplies fuel for ½ of
each cycle. The pump is powered by pressurized gas which acts
directly on fluid. For each half of the pump system, a chamber is
filled from the main tank under low pressure and at a high flow
rate, then the chamber is pressurized, and then the fluid is
delivered to the engine at a moderate flow rate under high
pressure. The chamber is then vented and cycle repeats. The
system is designed so that the inlet flow rate is higher than the
outlet flow rate.This allows time for one chamber to be vented ,
refilled and pressurized while the other is being emptied.A bread
board pump has been tested and it works great .A high version
has been designed and built and is pumping at 20 gpm and 550psi.


As shown in the above diagram , two cylinders are there ,
filled with the fuel from the main tank. This main tank is
emptied in these two cylinders, these cylinders are
pressurized by the high pressure tank,as shown.The high
pressure tank pressurizes one cylinder of high pressure,as
shown,as soon as the cylinder is emptied , it is vented,
again it gets filled up from the main tank.The same cycle
reapeats for the second cylinder.the cycle is such that,
fuel is supplied by the cylinder one by each
cylinder supplies fuel for each half cycle.As one cylinder
supplies the fuel other has enough time to refill.


Nearly all of the hardware in this pump consists of pressure
vessels, so the weight is low.There are less than 10 moving parts ,
and no lubrication issues which might cause problems with other
pumps. The design and constr. Of this pump is st, forward and no
precision parts are required .This device has advantage over std.
turbopumps in that the wt. is about the same, the unit,engg.and test
costs are less and the chance for catastrophic failure is less.This
pump has the advantage over pressure fed designs in that the wt. of
the complete rocket is much less, and the rocket is much safer
because the tanks of rocket fuel do not need to be at high pressure.the
pump could be started after being stored for an extended period with
high reliability.It can be used to replace turbopumps for rocket
booster opn. or it can be used to replace high pressure tanks for deep
space propulsion.It can also be used for satellite orbit changes and
station keeping.


NASA has a need for high power propulsion to land and
spacecraft on the moons of Jupitor and beyond.this pump would
allow these missions to go forward due to lower weight of the fuel
tanks. For example, to land on Europa with a hydrazine
monopropellant rocket , pump fed design would save 80% of the
tank weight compared to a pump fed design.Further weight
savings could be achieved by heating the pressurant gas more,
because the pressurant would not be in contact with the propellant
for more than a few seconds . In addition ,the chamber could be
increased , saving engine weight and improving performance.


For X-prize competitors, a the fuel pump will reduce the cost
and increase the safety and reliability of their amateur manned
vehicles.Sitting on top of tons of rocket fuel is dangerous
enough,siiting on top if tons of rocket fuel at high pressure is
even more so. Many of the competitors plan to use Hydrogen
Peroxide(HTP) and jet fuel to power their rockets.When the
pump is used to pump HTP, it can decompose some of the fuel in
a gas generator to run the pump. This saves a considerable
amount of weight pressurant and main tankage.
In addition , the factor on the low pressure tanks will
be similar to the cost of the high pressure tanks alone.


A calculation of the weight of this type of pump shows that the
power to weight ratio would be dominated by the pressure chamber
and that it would be of the order of 8-12 hp per lb., for a 5 second
cycle using a composite chamber. This performance is similar to
state of the art gas-generator turbopump technology. (The F1
turbopump on the Saturn V put out 20 hp/lb) This pump could be
run until dry, so it would achieve better residual propellant
scavenging than a turbopump. This system would require a supply
of gaseous or liquid Helium which would be heated by a heat
exchanger mounted on the combustion chamber before it was used
to pressurize the fuel, as in the Ariane rocket.. The volume of
gas required would be equivalent to a standard pressure fed design,
with a small additional amount to account for ullage in the pump
chambers. The rocket engine itself could be a primarily ablative
design, as in the NASA Fastrac, scorpious rocket or in
recent rocket engine tests.

hi ,
there is lot of information about Pistonless Pump for Rockets available in following page with report and ppt
Post: #2
sir please send me the full seminar report and soon as possible.;)
Post: #3
To get more information about the topic "Pistonless Pump for Rockets full report " please refer the link below
Post: #4
Post: #5
to get information about the topic pistonless pump for rocket full report ,ppt and related topic refer the link bellow
Post: #6
I need ppt of pistonless pump..thank u Heart

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