Experimental Validation of Expanded Centerbodiless RDE Design

Stoddard, William; George, Andrew C. St.; Driscoll, Robert B.; Anand, Vijay; Gutmark, Ephraim

doi:10.2514/6.2016-0128

Cited by 19 publications

(11 citation statements)

References 7 publications

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“…As will be discussed in Section 4.4, the number of alternative designs to the annulus is limited. An exception is the hollow cylinder model to determine the effects of having no inner wall on the detonation wave as well as the practical feasibility [50].…”

Section: Existing Rde Designsmentioning

confidence: 99%

“…Hollow RDEs, dubbed "centrebodiless" designs, have been tested with two different designs [50,61]. One design was identical to a conventional RDE 100 mm across, but the inner cylinder terminated parallel to the fuel/oxidiser injectors [61].…”

mentioning

confidence: 99%

“…However, when the same geometry was tested with 253.3 g s À1 of CH 4 /O 2 at an equivalence ratio of 0.665, the mixture became sufficiently mixed to sustain a stable four-wave detonation structure [61]. Another design was completely hollow, allowing oxygen-enriched air to be pumped through the centre of the chamber, and fuel was supplied around the edge [50]. In this design, stable detonations, operating at $8000 Hz were achieved at an equivalence ratio of $0.4 [5-].…”

mentioning

confidence: 99%

“…Example of an aerospike nozzle configuration [52]. standard air-led to the RDE self-extinguishing [50]. Nevertheless, the need for oxygen enrichment introduces additional cost and challenges for practical RDEs in propulsion applications.…”

mentioning

confidence: 99%

“…Nevertheless, the need for oxygen enrichment introduces additional cost and challenges for practical RDEs in propulsion applications. It was also noted that the oxidant flow provides an outward pressure that acts like a wall but carries no extra weight, and even adds a small amount of thrust as the air is expelled [50]. Both designs can be looked at as successful proofs of concepts, and potential first steps in simplifying the geometry of an RDE, with the latter being potentially useful in applications such as afterburners [50,61].…”

mentioning

confidence: 99%

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Rotating detonation engines are a novel device for generating thrust from combustion, in a highly efficient, yet mechanically simple form. This chapter presents a detailed literature review of rotating detonation engines. Particular focus is placed on the theoretical aspects and the fundamental operating principles of these engines. The review covers both experimental and computational studies, in order to identify gaps in current understanding. This will allow the identification of future work that is required to further develop rotating detonation engines.

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Section: Existing Rde Designsmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Design, Optimization, and Analysis of Supersonic Radial Turbines

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New compact engine architectures such as pressure gain combustion require ad hoc turbomachinery to ensure an adequate range of operation with high performance. A critical factor for supersonic turbines is to ensure the starting of the flow passages, which limits the flow turning and airfoil thickness. Radial outflow turbines inherently increase the cross section along the flow path, which holds great potential for high turning of supersonic flow with a low stage number and guarantees a compact design. First, the preliminary design space is described. Afterward a differential evolution multi-objective optimization with 12 geometrical design parameters is deducted. With the design tool autoblade 10.1, 768 geometries were generated and hub, shroud, and blade camber line were designed by means of Bezier curves. Outlet radius, passage height, and axial location of the outlet were design variables as well. Structured meshes with around 3.7 × 106 cells per passage were generated. Steady three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) simulations, enclosed by the k-omega shear stress transport turbulence model were solved by the commercial solver CFD++. The geometry was optimized toward low entropy and high-power output. To prove the functionality of the new turbine concept and optimization, a full wheel unsteady RANS simulation of the optimized geometry exposed to a nozzled rotating detonation combustor (RDC) has been performed and the advantageous flow patterns of the optimization were also observed during transient operation.

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Experimental Validation of Expanded Centerbodiless RDE Design

Cited by 19 publications

References 7 publications

A Theoretical Review of Rotating Detonation Engines

A Theoretical Review of Rotating Detonation Engines

Rotating Detonation Combustor Research at the University of Cincinnati

Design, Optimization, and Analysis of Supersonic Radial Turbines

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