An Experimental Study on Characteristics of Small-scale PDE under Low-frequency Operating Conditions

Han, Hyun-Sik; Kim, Jungmin; Oh, Se-Joon; Choi, Jeong-Yeol

doi:10.6108/kspe.2018.22.3.081

Cited by 8 publications

(4 citation statements)

References 11 publications

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“…Geometric features of converging section of the nozzle (dimensions in mm). A combustion wave ignitor (CWI) was used to ignite the VAH, which was based on the model designed by Han et al [23]. The CWI was installed at the chamber wall 50 mm from the VAH head, as shown in Figure 5.…”

Section: Vitiation-air-heater Experimental Modelmentioning

confidence: 99%

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

Lee

Han

et al. 2023

Aerospace

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Vitiation air heater (VAH) combustion characteristics for a direct-connect scramjet combustor (DCSC) were experimentally studied. The VAH consists of a head, modular chamber, and circular-to-rectangular shape transition (CRST) nozzle. The CRST nozzle transforms the circular cross-sectioned rocket-type VAH into a rectangular cross-sectioned scramjet combustor. The CRST nozzle exit Mach numbers at the top, middle, and bottom were measured using a tungsten wedge. The oblique shock formed by the wedge was captured using Schlieren visualization and recorded with a high-speed camera. The θ-β-M relation showed that the exit Mach number was 2.04 ± 0.04 with a chamber pressure of 1.685 ± 0.07 MPa. With the VAH design point verified, preliminary scramjet combustor ignition tests were conducted. As the fuel was not auto-ignited by the vitiated air, the forced ignition method, in which VAH ignition flame ignites the scramjet fuel, was used. The Schlieren images showed that a cavity shear layer combustion mode was formed and also showed that the forced ignition method could be used as a reference model for the ignitor-ignition method.

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Section: Vitiation-air-heater Experimental Modelmentioning

confidence: 99%

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

Lee

Han

et al. 2023

Aerospace

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“…It was designed with an inner diameter of 4.22 mm and a length of 110 mm. The PDT length was sufficient for DDT with a 4.22 mm inner diameter based on previous research results [33]. To generate a single detonation wave, the PDT was installed tangentially to the RDE combustion channel [34].…”

Section: Rde Modelmentioning

confidence: 99%

Effects of Injector Configuration on the Detonation Characteristics and Propulsion Performance of Rotating Detonation Engine (RDE)

Koo,

Lee,

Kim

et al. 2023

Aerospace

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Fuel injection and mixing affect the characteristics of detonation initiation and propagation, as well as the propulsion performance of rotating detonation engine (RDE). A study on the injector is carried out in the present investigation. A rectangular-shaped hole-type fuel injector (RHFI) and slit-type fuel injector (SFI) were designed and compared experimentally at equivalent conditions. The investigation of the detonation propagation modes and the analysis of propulsion performance were carried out using fast Fourier transform (FFT), short-time Fourier transform (STFT), and unwrapped image post-processing. Under 50, 75, and 100 g/s flow rate conditions at an equivalence ratio of 1.0 ± 0.05, the RHFI has relatively stable detonation propagation characteristics, higher thrust, and specific impulse performance. Additionally, the results of the experiment indicate that the number of detonation waves affects performance.

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“…The conical center body of 30.0 • is optionally attachable at the exit of the combustor, enabling a performance comparison between the buff exit and conical center body. A small single-tube PDE [8] using the same fuel and oxidizer is installed tangentially at the combustor channel as a pre-detonator for detonation initiation in the RDE. The inner diameter and length of the pre-detonator tube are 4.0 mm and 150.0 mm, respectively.…”

Section: Rde Model Configurationmentioning

confidence: 99%

“…In 2011, General Electric conducted a performance test of a gas turbine system based on a pulse detonation combustor [4]. Currently, given the physical and performance limitations of low-frequency pulsed operations, PDEs are used in applied areas or propulsion subsystems such as thermal sprays [5], reaction control systems [6,7] and combustion wave igniters [8,9], rather than as the main propulsion systems. However, they continue to be used for the study of detonation physics.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant

2021

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A small rotating detonation engine (RDE) model and the corresponding experimental setup were constructed for the experimental investigation of the detonation propagation characteristics and thrust performance of a circular RDE. Experiments were conducted at a range of 0.3–2.5 equivalence ratio with a total mass flow rate of less than 180.0 g/s using a C2H4/O2 mixture. Irregularly unstable detonative combustion occurs immediately after the detonation initiation, which includes initiation, propagation, decaying, and the merging of detonation waves. Following this, periodically unsteady detonative combustion occurs in the circular channel, resulting in the stable operation of the RDE. During stable operation, two detonation waves are predominant, rotating along the wall at a speed lower than the Chapman–Jouguet (CJ) detonation speed. The characteristic velocity efficiency is approximately 73% on average. The low characteristic velocity efficiency is presumed to be caused by the unoptimized combustion channel and the poor mixing efficiency owing to the two-dimensional injector configuration. The effect of the RDE component design and the RDE flow field characteristics need to be further investigated for improving the performance of the RDE.

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An Experimental Study on Characteristics of Small-scale PDE under Low-frequency Operating Conditions

Cited by 8 publications

References 11 publications

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

Effects of Injector Configuration on the Detonation Characteristics and Propulsion Performance of Rotating Detonation Engine (RDE)

Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant

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