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Published in Harish Kumar Banga, Rajesh Kumar, Parveen Kalra, Rajendra M. Belokar, Additive Manufacturing with Medical Applications, 2023
“NASA’s Rapid Analysis and Manufacturing Propulsion Technology project, or RAMPT, has recently used ‘blown powder directed energy deposition’ technique to 3D print a 40-inch diameter and 38-inch tall rocket engine nozzle with fully integrated cooling channels using lasers and metal powder. As a result, the most expensive and challenging rocket engine parts can now be produced at a lower cost than in the past (NASA, 2020) (see Figures 14.6 and 14.7). Overall, AM technology is a promising proposition for the aerospace industry in terms of hard benefits (Joshi & Sheikh, 2015).
Product Quality
Published in G.K. Awari, C.S. Thorat, Vishwjeet Ambade, D.P. Kothari, Additive Manufacturing and 3D Printing Technology, 2021
G.K. Awari, C.S. Thorat, Vishwjeet Ambade, D.P. Kothari
Proof testing is a way to subject a prototype part, a process qualification lot, or a random sample taken from a production lot, to a mockup testing of the part within an in-service environment. As an example, this is the testing stage where you fire up the rocket engine nozzle, take the car to the race track, or pressurize the storage vessel to see how well it works. Often the component is subjected to an extended range of standard operating conditions to prove functional performance beyond that typically seen in service. Elaborate machines to perform these tests have been used for years to evaluate test parts destined for manufacture. We have all seen the so-called shake, rattle, and roll systems where you bolt up the car and subject it to high cycle fatigue for tens of thousands of loading cycles and we all know the fate of the crash test dummies. It will probably not be too long before these machines and dummies feature 3D-printed parts.
Energetic Properties
Published in WeiQiang Pang, Luigi T. De Luca, XueZhong Fan, Oleg G. Glotov, FengQi Zhao, Boron-Based Fuel-Rich Propellant, 2019
WeiQiang Pang, Luigi T. De Luca, XueZhong Fan, Oleg G. Glotov, FengQi Zhao
Where Ve is regarded as the velocity of combustion products of the “mixed propellant” in the secondary combustion chamber at the outlet of the nozzle. The calculation method is the same as the flow velocity at the outlet of the ordinary rocket engine nozzle. Therefore, the flow rate of 1 kg “mixed propellant” at the exit of the engine (the same working environment of the combustion chamber) is calculated.
Comparative appraisal of nanofluid flows in a vertical channel with constant wall temperatures: an application to the rocket engine nozzle
Published in Waves in Random and Complex Media, 2022
Muhammad Ramzan, Nazia Shahmir, Hassan Ali S. Ghazwani, M. Y. Malik
The aforesaid literature analysis discloses that there are limited research articles on the cooling of rocket nozzles using transpiration mechanisms. It is also noted that studies on the transpiration of nanofluid in rocket engines for cooling purposes are examined when walls are stretchable [16,17]. However, in reality, the walls of the rocket engine are fixed. Keeping this veracity in mind, we, therefore, intend to analyze the cooling process of rocket nozzle walls using the fixed wall channel. So, in this article mixed convection nanofluid flow between two vertical porous plates with entropy generation is analyzed. The flow geometry design corresponds to the cooling channel of the rocket engine nozzle. Exponential space-dependent heat source, linear thermal radiation effects, and a thermal-dependent heat source are all employed in the temperature equation. However, no research has been conducted that included a combination of the aforementioned impacts. Table 1 compares the provided model to the existing literature to show its reliability.