A Numerical Model for Nozzle Flow Application under LOX/CH4 Hot Flow Conditions

Schneider, Dirk; Génin, Chloe; Karl, Sebastian; Hannemann, Volker

doi:10.2514/6.2016-4671

Cited by 2 publications

(1 citation statement)

References 22 publications

(26 reference statements)

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“…Previous investigations revealed that flow separation transition can be influenced not only by the variation of total propellant mass-flow rate but by a variation of the propellant mixture ratio r of as well. While its increase yielded in a reduction of the transition pressure ratio, lowering of r of produces an opposite result [59,60]. However, these effects are accompanied by a reduction of the width of the hysteresis, the pressure ratio gap between transition and re-transition occurs.…”

Section: Dual Bell Nozzlementioning

confidence: 98%

Collaborative Research for Future Space Transportation Systems

Haidn

Adams

Radespiel

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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This chapter book summarizes the major achievements of the five topical focus areas, Structural Cooling, Aft-Body Flows, Combustion Chamber, Thrust Nozzle, and Thrust-Chamber Assembly of the Collaborative Research Center (Sonderforschungsbereich) Transregio 40. Obviously, only sample highlights of each of the more than twenty individual projects can be given here and thus the interested reader is invited to read their reports which again are only a summary of the entire achievements and much more information can be found in the referenced publications. The structural cooling focus area included results from experimental as well as numerical research on transpiration cooling of thrust chamber structures as well as film cooling supersonic nozzles. The topics of the aft-body flow group reached from studies of classical flow separation to interaction of rocket plumes with nozzle structures for sub-, trans-, and supersonic conditions both experimentally and numerically. Combustion instabilities, boundary layer heat transfer, injection, mixing and combustion under real gas conditions and in particular the investigation of the impact of trans-critical conditions on propellant jet disintegration and the behavior under trans-critical conditions were the subjects dealt with in the combustion chamber focus area. The thrust nozzle group worked on thermal barrier coatings and life prediction methods, investigated cooling channel flows and paid special attention to the clarification and description of fluid-structure-interaction phenomena I nozzle flows. The main emphasis of the focal area thrust-chamber assembly was combustion and heat transfer investigated in various model combustors, on dual-bell nozzle phenomena and on the definition and design of three demonstrations for which the individual projects have contributed according to their research field.

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Section: Dual Bell Nozzlementioning

confidence: 98%