Been reading about some designs for hydrolox engines that proposed running
very LOX-rich to get a better TWR at the expense of performance. To my
understanding this probably would have entailed extreme film
cooling/entraining excess LOX into the exhaust stream, injected somewhere
in the nozzle exit? because the metallurgy available back in the 70s-90s
just wouldn’t cut it.
Did anything like this ever make it to flight or bench testing? It seems
promising even in our domain, squeezing just a little more thrust out of
the early phase of flight and gearshifting to better performance at
altitude.
