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Transient Side Load Analysis of Out-of-Round Film-Cooled Nozzle Extensions
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Author and Affiliation:
Wang, Ten-See(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Lin, Jeff(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Ruf, Joe(NASA Marshall Space Flight Center, Huntsville, AL, United States);
Guidos, Mike(NASA Marshall Space Flight Center, Huntsville, AL, United States)
Abstract: There was interest in understanding the impact of out-of-round nozzle extension on the nozzle side load during transient startup operations. The out-of-round nozzle extension could be the result of asymmetric internal stresses, deformation induced by previous tests, and asymmetric loads induced by hardware attached to the nozzle. The objective of this study was therefore to computationally investigate the effect of out-of-round nozzle extension on the nozzle side loads during an engine startup transient. The rocket engine studied encompasses a regeneratively cooled chamber and nozzle, along with a film cooled nozzle extension. The computational methodology is based on an unstructured-grid, pressure-based computational fluid dynamics formulation, and transient inlet boundary flow properties derived from an engine system simulation. Six three-dimensional cases were performed with the out-of-roundness achieved by three different degrees of ovalization, elongated on lateral y and z axes: one slightly out-of-round, one more out-of-round, and one significantly out-of-round. The results show that the separation line jump was the primary source of the peak side loads. Comparing to the peak side load of the perfectly round nozzle, the peak side loads increased for the slightly and more ovalized nozzle extensions, and either increased or decreased for the two significantly ovalized nozzle extensions. A theory based on the counteraction of the flow destabilizing effect of an exacerbated asymmetrical flow caused by a lower degree of ovalization, and the flow stabilizing effect of a more symmetrical flow, created also by ovalization, is presented to explain the observations obtained in this effort.
Publication Date: Jul 30, 2012
Document ID:
20120015655
(Acquired Nov 14, 2012)
Subject Category: FLUID MECHANICS AND THERMODYNAMICS
Report/Patent Number: M11-1336, M12-1855, M12-1962
Document Type: Conference Paper
Meeting Information: 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; 30 Jul. 2012 - 1 Aug. 2012; Atlanta, GA; United States
Meeting Sponsor: American Inst. of Aeronautics and Astronautics; Washington, DC, United States
American Society of Mechanical Engineers; Washington, DC, United States
Society of Automotive Engineers, Inc.; Warrendale, PA, United States
American Society for Electrical Engineers; United States
Financial Sponsor: NASA Marshall Space Flight Center; Huntsville, AL, United States
Organization Source: NASA Marshall Space Flight Center; Huntsville, AL, United States
Description: 29p; In English; Original contains color and black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: ROCKET NOZZLES; COMPUTATIONAL FLUID DYNAMICS; LOADS (FORCES); FLOW CHARACTERISTICS; ELLIPTICITY; DEFORMATION; INLET FLOW; REGENERATIVE COOLING; ROCKET ENGINES; THREE DIMENSIONAL MODELS; NOZZLE DESIGN; UNSTRUCTURED GRIDS (MATHEMATICS); THRUST CHAMBERS; DIMENSIONAL ANALYSIS; UNSTEADY FLOW; TRANSIENT LOADS
Miscellaneous Notes: PDF includes Conference paper and oral/visual presentation
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