This is @blueorigin’s BE-7 engine for the #bluemoon lunar lander up close and personal!
Re-posting in this thread for ease of reference:https://twitter.com/erdayastronaut/status/1126594675048157185QuoteThis is @blueorigin’s BE-7 engine for the #bluemoon lunar lander up close and personal!
Quote from: FutureSpaceTourist on 05/10/2019 08:35 amRe-posting in this thread for ease of reference:https://twitter.com/erdayastronaut/status/1126594675048157185QuoteThis is @blueorigin’s BE-7 engine for the #bluemoon lunar lander up close and personal!Following up on Tonya's comment, note how the pipes are color coded depending on whether they carry hydrogen or oxygen.Also, this is a good opportunity to link to this nice educational article about expander cycle engines:https://blogs.nasa.gov/J2X/2014/03/24/inside-the-leo-doghouse-the-art-of-expander-cycle-engines/And attached, a diagram of the dual expander cycle:
AFAIK the BE-7 uses the most complex expander-cycle option; the dual expander cycle. The most simple is expander bleed; aka evaporating some of the fuel or oxidizer to drive the turbopump(s). The evaporated gas is dumped in the trust direction, but not used inside the combustion chamber.The next level in complexity is a standard expander cycle, the fuel or the oxidizer is evaporated, drives the turbopump(s) and is injected into the combustion chamber. The most complex is dual expander, both the fuel and oxidizer are expanded, they drive a fuel and oxidizer turbopump and the gasses are injected into the combustion chamber, reaching the high ISP of the GOxGH2 fuel combo. (RL-10 has a geared GH2(G) turbine driving a LH2 turbopump connected with a gear to the LO2 turbopump.Vince has a LOx and a LH2 turbopump both driven by a GH2 turbine. With a proportional valve the GH2 flow is regulated between the two turbopumps. Now in Europe the ETID is being developed under the ESA FLPP program, it uses another version of the single expander cycle (afaik). Have others envisioned the use of BE-7 as upper-stage engine for a New Shepard sized and derived small launcher? AKA ~1000-2000lb (0.5-1mT) to 800km SSO. Is this possible?Edit to add: Blue Origin what is the thust level of BE-7. 10k lbf (44 482 N) or 40kN (8992 lbf)? The current numbers are a mess. If its 10k lbf state its 44,5kN please.Note that BE-- is a very small low thrust engine. RL-10 is 15k - 25k lbf (~65-110kN), and Vince is 180kN (~40 500 lbf). And the Ariane 5 ECA HM7B gasgenerator engines provide ~64kN (14.3k lbf) so BE-7 is less powerful.What I find funny is the fact that the Callisto demonstrator (Europa and Japan reusable suborbital stage demonstrator) will use re-ignitable 40kN LOxLH2 engine. Details about this engine are vague. edit2: the engine shown on the right side if the Scott Manley Expander Cycle video, is NOT Vince. Its ID#1 the thust chamber test article from the EDIT FLPP project.
I think the mock-up of BE-7 misses the sensor and electronic cables and the LOx and LH2 infeeds. The mockup only only shows: four sections of the combustion chamber assembly; the GOx and GH2 lines and regulator valves.The engine for Callisto must be able to throttle down 40% or to 40% (40kN max => 24kN or 16kN |10k lbf => 6k or 4k lbf) @russianhelo117 can you explain the difference between DEC and CDSEC? What is de spilt meaning?The BE-7 definitely looks like a closed cycle engine.