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2. SpaceX Raptor - Wikipedia

   en.wikipedia.org/wiki/SpaceX_Raptor

   The concept evolved from a family of Raptor-designated rocket engines (2012) [45] to focus on the full-size Raptor engine (2014). [46] In January 2016, the US Air Force awarded a US$33.6 million development contract to SpaceX to develop a prototype Raptor for use on the upper stage of Falcon 9 and Falcon Heavy. [47] [48]

3. Comparison of orbital rocket engines - Wikipedia

   en.wikipedia.org/wiki/Comparison_of_orbital...

   Engine Origin Designer Vehicle Status Use Propellant Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [b] Oxidiser: fuel ratio

4. SpaceX rocket engines - Wikipedia

   en.wikipedia.org/wiki/SpaceX_rocket_engines

   The booster would utilize multiple Raptor engines, similar to the use of nine Merlin 1s on each Falcon 9 booster core. [17] The following month, SpaceX confirmed that as of March 2014, all Raptor development work is exclusively on this single very large rocket engine, and that no smaller Raptor engines were in the current development mix. [14]

5. SpaceX Merlin - Wikipedia

   en.wikipedia.org/wiki/SpaceX_Merlin

   By October 2014, SpaceX announced that it had manufactured the 100th Merlin 1D engine and that engines were now being produced at a rate of four per week, soon to be increased to five. [ 51 ] [ 52 ] In February 2016, SpaceX indicated that the company will need to build hundreds of engines a year in order to support a Falcon 9/Falcon Heavy build ...

6. Pratt & Whitney F119 - Wikipedia

   en.wikipedia.org/wiki/Pratt_&_Whitney_F119

   The Pratt & Whitney F119, company designation PW5000, is an afterburning turbofan engine developed by Pratt & Whitney for the Advanced Tactical Fighter (ATF) program, which resulted in the Lockheed Martin F-22 Raptor.

7. RL10 - Wikipedia

   en.wikipedia.org/wiki/RL10

   The RL10 is a liquid-fuel cryogenic rocket engine built in the United States by Aerojet Rocketdyne that burns cryogenic liquid hydrogen and liquid oxygen propellants. Modern versions produce up to 110 kN (24,729 lb f) of thrust per engine in vacuum.