Я не понимаю J
jd
From: arocket-bounce@xxxxxxxxxxxxx [mailto:arocket-bounce@xxxxxxxxxxxxx] On
Behalf Of Alexander Ponomarenko
Sent: dinsdag 14 juli 2015 14:53
To: arocket
Subject: [AR] Re: Arocket Pump Progress
You can catch the answers to all questions from this image (though it is not
the best available quality):
http://s012.radikal.ru/i321/1011/1f/09bd664d3736.jpg
"Monroe L. King Jr." < <mailto:monroe@xxxxxxxxxxxxxxxxxx>
monroe@xxxxxxxxxxxxxxxxxx> hat am 14. Juli 2015 um 12:48 geschrieben:
Looking at the densities of the propellants, that SA-2 engine is very
close to what we are working on. Reverse engineering that pump would
actually probably work with some slight changes to handle our
propellants.
What was used to power the turbine?
Are there inducers on the pumps?
Are the impellers open or shrouded?
What kind of seals are they using?
Just some of the basic questions I'd ask. Depending on the answers to
those questions I could be more specific with follow up questions.
At this point I'd be willing to travel to get a really good look at one
of these. If I could really examine it good.
Today we can even make 3D scans and save a lot of time and effort.
-------- Original Message --------
Subject: [AR] Re: Arocket Pump Progress
From: "Monroe L. King Jr." < <mailto:monroe@xxxxxxxxxxxxxxxxxx>
monroe@xxxxxxxxxxxxxxxxxx>
Date: Tue, July 14, 2015 2:34 am
To: <mailto:arocket@xxxxxxxxxxxxx> arocket@xxxxxxxxxxxxx
Anthony
Worth your time to dissemble that pump and let us have a good look at
the housings and turbine? Or just take that turbine off and send it to
me to examine? lol
Again being funny but kinda serious at the same time.
That would be a great pump to examine about right now.
-------- Original Message --------
Subject: [AR] Re: Arocket Pump Progress
From: "Anthony Cesaroni" < <mailto:acesaroni@xxxxxxxxxxx>
acesaroni@xxxxxxxxxxx>
Date: Mon, July 13, 2015 2:54 pm
To: < <mailto:arocket@xxxxxxxxxxxxx> arocket@xxxxxxxxxxxxx>
The SA-2 sustainer has the axial turbine in the middle with the hypergolic
propellant pumps on each end. One of the last unfired version sits in my
board room at the SRQ facility. ~200 shp. Pc is around 900 psi IIRC. A very
famous LR-101 known as “7-UP” is on the right.
Best.
Anthony J. Cesaroni
President/CEO
Cesaroni Technology/Cesaroni Aerospace
<http://www.cesaronitech.com/> http://www.cesaronitech.com/
(941) 360-3100 x101 Sarasota
(905) 887-2370 x222 Toronto
-----Original Message-----
From: <mailto:arocket-bounce@xxxxxxxxxxxxx> arocket-bounce@xxxxxxxxxxxxx [
<mailto:arocket-bounce@xxxxxxxxxxxxx> mailto:arocket-bounce@xxxxxxxxxxxxx]
On Behalf Of Alexander Ponomarenko
Sent: Monday, July 13, 2015 5:04 PM
To: <mailto:arocket@xxxxxxxxxxxxx> arocket@xxxxxxxxxxxxx
Subject: [AR] Re: Arocket Pump Progress
In case of closed impeller design, the distance between impeller and
housing should be rather large to minimize the friction losses. The
hydraulic losses as well as axial thrust are typically controlled by
diameter of and clearance between wearing or floating rings on both sides
of the impeller.
In case of open design, the mentioned is applicable to the back
("closed") side of the impeller only, whereas the clearance between open
blades and pump housing should be as small as possible. This makes crucial
both the assembly precision and the balancing of the axial thrust.
The usage of double-suction impellers may indeed compensate the axial
thrust, but such design is impractical in case of small pumps because of
too small height of blades. Better to design the bi-prop single-shaft
turbopump with such location of the impellers that their axial thrusts
compensate each other - at least partially. Of course, this is applicable
for bi-prop only.
Regards,
Alexander
On 07/12/2015 02:43 PM, Monroe L. King Jr. wrote:
I'd like to propose a question about the distance of the backside of
the impeller from the housing.
Is there an ideal distance on the backside of the impeller and should
that surface be smooth or ribbed?
Peter H. would you be interested in running CFD on this impeller
design? Also looking for FEA analysis if anyone's interested.
