Performance Trends for a Product Scale Pulse Detonation Engine

Anderson, Steve; Tonouchi, J. H.; Lidstone, Gary L.; Lupkes, K. R.; Alfonso, F. J.

doi:10.2514/6.2004-3402

Cited by 7 publications

(4 citation statements)

References 6 publications

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“…Previous studies mainly focused on the application of pulse detonation technology in main combustors for pulse detonation engines. There are two forms of PDE: pulse detonation rocket engine and airbreathing pulse detonation engine, and the five-tube airbreathing pulse detonation engine ITR-2 which was developed for the supersonic missile by Pratt & Whitney and Boeing [42], the fourtube pulse detonation rocket engine Todoroki II [38], and the pulse detonation turbine engine developed by Northwestern Polytechnical University [43] are the representative configurations of the PDEs. Based on these prototypes, the technical feasibility and performance superiority of various types of PDE have been preliminarily verified.…”

Section: System Configuration and Component Matchingmentioning

confidence: 99%

Review on the Rotating Detonation Engine and It’s Typical Problems

Xie

Wen

et al. 2020

Transactions on Aerospace Research

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Detonation is a promising combustion mode to improve engine performance, increase combustion efficiency, reduce emissions, and enhance thermal cycle efficiency. Over the last decade, significant progress has been made towards the applications of detonation mode in engines, such as standing detonation engine (SDE), Pulse detonation engine (PDE) and rotating detonation engine (RDE), and the understanding of the fundamental chemistry and physics processes in detonation engines via experimental and numerical studies. This article is to provide a comprehensive overview of the progress in the knowledge of rotating detonation engine from the different countries. New observations of injection, ignition, and geometry of combustor, pressure feedback, and combustion modes of RDE have been reported. These findings and advances have provided new opportunities in the development of rotating detonation for practical applications. Finally, we point out the current gaps in knowledge to indicate which areas future research should be directed at.

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Section: System Configuration and Component Matchingmentioning

confidence: 99%

Review on the Rotating Detonation Engine and It’s Typical Problems

Xie

Wen

et al. 2020

Transactions on Aerospace Research

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“…Pratt & Whitney Group developed a full size rotary valve PDE validation prototype with five tubes at flight inlet condition. 16 Propane gas was used as fuel. The inner diameter of detonation tube was 101.6 mm, and the length of detonation tube was 762 mm.…”

Section: Introductionmentioning

confidence: 99%

Direct-connected experimental investigation on a pulse detonation engine

Wang

Liang

Zhang

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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A pulse detonation engine with the inner diameter of 50 mm and total length of 1500 mm was designed. Gasoline was used as the fuel and air as the oxidizer. The Shchelkin spiral was used as the deflagration to detonation transition accelerator. The direct-connected test of the pulse detonation engine was conducted to find out the detonation initiation and propulsion performance at several different operating frequencies. The experimental results indicated that detonation waves were fully initiated in the pulse detonation engine at the operating frequency range of 1–35 Hz. As the operating frequency increased, the pulse detonation engine average thrust increased nearly linearly, while the optimum equivalence ratio decreased gradually. The volume-specific impulse and mixture-specific impulse had the similar increasing trend at the increased operating frequency. As the operating frequency increased from 0 to 25 Hz, the fuel-specific impulse increased dramatically while the specific fuel consumption decreased quickly. The fuel-specific impulse and specific fuel consumption changed slightly when the operating frequency exceeded 25 Hz. In addition, two groups of computational value of mixture-specific impulse and fuel-specific impulse were obtained by Winternberger model and Yan model considering the two-phase effect. Compared with the experimental results, similar variation trends relative to the operating frequency were achieved by the two computational models. However, the computational values of mixture-specific impulse and fuel-specific impulse by Winternberger model were much higher than that of experimental values. When two-phase effect was considered, the computational values of mixture-specific impulse and fuel-specific impulse were close to that of experimental values.

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“…Multiple studies 34,35 (Figure 2.13). In addition, the use of multiple detonation tubes in concert with a common nozzle has been shown to increase backpressure wherein a common choke point can be achieved 8,36 . This configuration has also been tested on the ITR-2 PDE (Figure 2.14).…”

Section: Filling Velocitymentioning

confidence: 99%

“…The incorporation of nozzles or ejectors are required in order to capture the energy contained within the detonation shock wave as it exits the tube 25 , however, the unsteady nature of PDE operation make nozzle optimization anything but straightforward. Ideal nozzle operation would require a variable nozzle capable of continuously varying its geometry throughout the detonation cycle 8 .…”

Section: Nozzles and Ejectorsmentioning

confidence: 99%

Intake Flow Analysis of a Pulsed Detonation Engine

Strafaccia

2016

Journal of Engineering for Gas Turbines and Power

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A CFD program is converted and modified to explore unsteady flow within the intake system of a pulse detonation engine (PDE). Using a quasi-one-dimensional approach the program provides insight into the unsteady nature of localized equivalence ratios to include their effects on PDE performance. The original FORTRAN program is converted into the MATLAB architecture, taking full advantage of user availability and post processing convenience. The converted program was validated against the original program and modified to include a primitive intake manifold system with a single fuel injector located approximately 10 feet upstream of the primary intake valve. Constant fuel mass flow rate at the injector end creates local variations in equivalence ratio throughout the PDE that may have significant impact on overall engine performance. The results of the current thesis research suggest that performance effects of up to 21% can be attributed to non-uniform fuel distribution throughout the detonation process and are most prevalent at lower frequencies and fill ratios.iii DEDICATION This thesis is dedicated to my family. In particular, to my wife and daughter who endured the many late nights and long hours needed to fulfill this lifelong academic goal and to my parents who taught me the meaning of hard work, commitment and sacrifice.iv

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Performance Trends for a Product Scale Pulse Detonation Engine

Cited by 7 publications

References 6 publications

Review on the Rotating Detonation Engine and It’s Typical Problems

Review on the Rotating Detonation Engine and It’s Typical Problems

Direct-connected experimental investigation on a pulse detonation engine

Intake Flow Analysis of a Pulsed Detonation Engine

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