Was that from the TRW demo engine we used in the head end of MVAD?
Anthony J. Cesaroni
President/CEO
Cesaroni Technology/Cesaroni Aerospace
http://www.cesaronitech.com/
(941) 360-3100 x1004 Sarasota
(905) 887-2370 x222 Toronto
From: arocket-bounce@xxxxxxxxxxxxx <arocket-bounce@xxxxxxxxxxxxx> On Behalf Of
roxanna Mason
Sent: Monday, October 11, 2021 3:35 PM
To: arocket@xxxxxxxxxxxxx
Subject: [AR] Re: Air breathing engines. (nothing to do with rockets)
Circa 2003 near North Edwards,CA, for a 6 month period, I leased Tom Muller an
aluminum 75K LOx/Kero pintle injector to show his peers in an attempt to
convince them to go with a pintle in their new ablative Falcon rocket.
The rest is history.
Ken
On Mon, Oct 11, 2021 at 12:20 PM Doug Jones
<rocketplumber@xxxxxxxxx<mailto:rocketplumber@xxxxxxxxx>> wrote:
I stand corrected, Tom Mueller and I being the exceptions since 1999.
On Mon, Oct 11, 2021 at 3:11 PM roxanna Mason
<rocketmaster.ken@xxxxxxxxx<mailto:rocketmaster.ken@xxxxxxxxx>> wrote:
Conversly why the TRW pintle is so stable, got the US on the moon and SpaceX
flying.
Ken
On Mon, Oct 11, 2021 at 12:04 PM Doug Jones
<rocketplumber@xxxxxxxxx<mailto:rocketplumber@xxxxxxxxx>> wrote:
NASA SP-194 LIQUID PROPELLANT ROCKET COMBUSTION INSTABILITY, particularly
section 7.2.5. If you populate the entire injector face with elements, you're
gonna have a bad time. But it's what everyone seems to have done ever since the
F-1, and none of them ever read the goddamn book. It's cringeworthy.
On Mon, Oct 11, 2021 at 11:03 AM Ismail Hozain
<ismailhozain@xxxxxxxxx<mailto:ismailhozain@xxxxxxxxx>> wrote:
Doug can you please elaborate on the design rules you applied?
Thanks,
Ismail
On Mon, Oct 11, 2021 at 9:16 AM Doug Jones
<rocketplumber@xxxxxxxxx<mailto:rocketplumber@xxxxxxxxx>> wrote:
We never used film cooling at XCOR, and had 97% or more cstar with LOX-kerosene
at 2.6 O:F, no mixture ratio compromises. I've never understood why everyone
else seems to struggle with efficiency vs stability vs cooling- they all pull
together in unison. I just applied design rules published fifty years ago.
On Mon, Oct 11, 2021, 3:20 AM roxanna Mason
<rocketmaster.ken@xxxxxxxxx<mailto:rocketmaster.ken@xxxxxxxxx>> wrote:
No, it's not that difficult to build high reliability long lived biprops, the
trick is to do it with high efficiency, c* that is, not off ratio and/or lots
of film cooling as was done with that Spectre RATO engine which BTW was derived
from an earlier Aerojet RATO rocket system using nitric acid oxidizer with
variations of fuels.
Thanks Henry for mentioning Bruno, I lost all my data earlier this year to a
hard drive crash and Bruno's info was one of the casualties. I had ~ 40 pics of
that Spectre system with subassemblIes of the TCA showing the cooling jacket
construction which was simple enough for amature use.
If anybody has that link of Bruno's I'd love to get it back into my archives.
Thanks,
Ken
On Sun, Oct 10, 2021 at 9:22 PM Henry Spencer
<hspencer@xxxxxxxxxxxxx<mailto:hspencer@xxxxxxxxxxxxx>> wrote:
On Sun, 10 Oct 2021, roxanna Mason wrote:
you get something as flaky and short-lived as a typical rocket engine
Enter SpaceX, particularly their Raptor which is claiming 100 flights.