Expander cycle

This operational cycle is a modification of the traditional expander cycle. In the bleed (or open) cycle, instead of routing all of the heated propellant through the turbine and sending it back to be combusted, only a small portion of the heated propellant is used to drive the turbine and is then bled off, being vented overboard without going through the combustion chamber. The other portion is injected into the combustion chamber. Bleeding off the turbine exhaust allows for a higher turbopump efficiency by decreasing backpressure and maximizing the pressure drop through the turbine. Compared with a standard expander cycle, this allows higher engine thrust at the cost of efficiency by dumping the turbine exhaust. The Mitsubishi LE-9 is the world's first first stage expander bleed cycle engine. Blue Origin chose the expander bleed cycle for the BE-3U engine used on the upper stage of its New Glenn launch vehicle. == Dual expander ==

In a similar way that the staged combustion can be implemented separately on the oxidizer and fuel on the full flow cycle, the expander cycle can be implemented on two separate paths as the dual expander cycle. The use of hot gases of the same chemistry as the liquid for the turbine and pump side of the turbopumps eliminates the need for purges and some failure modes. Additionally, when the density of the fuel and oxidizer is significantly different, as it is in the H2/LOX case, the optimal turbopump speeds differ so much that they need a gearbox between the fuel and oxidizer pumps. The use of dual expander cycle, with separate turbines, eliminates this failure-prone piece of equipment. Dual expander cycle can be implemented by either using separated sections on the regenerative cooling system for the fuel and the oxidizer, or by using a single fluid for cooling and a heat exchanger to boil the second fluid. In the first case, for example, you could use the fuel to cool the combustion chamber, and the oxidizer to cool the nozzle. In the second case, you could use the fuel to cool the whole engine and a heat exchanger to boil the oxidizer. == Advantages ==

The expander cycle has a number of advantages over other designs: ;Low temperature:After they have turned gaseous, the propellants are usually near room temperature, and do very little or no damage to the turbine, allowing the engine to be reusable. In contrast gas-generator or staged combustion engines operate their turbines at high temperature. ;Tolerance: During the development of the RL10 engineers were worried that insulation foam mounted on the inside of the tank might break off and damage the engine. They tested this by putting loose foam in a fuel tank and running it through the engine. The RL10 chewed it up without problems or noticeable degradation in performance. Conventional gas-generators are in practice miniature rocket engines, with all the complexity that implies. Blocking even a small part of a gas generator can lead to a hot spot, which can cause violent loss of the engine. Using the engine bell as a 'gas generator' also makes it very tolerant of fuel contamination because of the wider fuel flow channels used. ;Inherent safety: Because a bell-type expander-cycle engine is thrust limited, it can easily be designed to withstand its maximum thrust conditions. In other engine types, a stuck fuel valve or similar problem can lead to engine thrust spiraling out of control due to unintended feedback systems. Other engine types require complex mechanical or electronic controllers to ensure this does not happen. Expander cycles are by design incapable of malfunctioning that way. ;Higher vacuum performance: Compared to a pressure-fed engine, pump-fed engines and hence, expander cycle engines have higher combustion chamber pressures. Increased combustion chamber pressures allow for a reduced throat area Ath, and therefore, leads to a larger expansion ratio, e = Ae/Ath for an identical nozzle exit area Ae, which ultimately leads to higher vacuum performance. == Usage ==

Expander cycle engines include the following: • Aerojet Rocketdyne RL10 • Pratt & Whitney RL60 • ArianeGroup Vinci • CADB & Pratt & Whitney RD-0146 • Chinese YF-75D • Mitsubishi Heavy Industries LE-5A / 5B • Mitsubishi Heavy Industries LE-9 • Aerojet Rocketdyne & MHI MARC-60 (MB-60) • Blue Origin BE-3U and BE-7 • Avio M10 • Demonstration Rocket for Agile Cislunar Operations (DRACO) nuclear thermal engine == Comparison of upper-stage expander-cycle engines ==