Hypersonic wavecatcher intakes and variable-geometry turbine based combined cycle engines

Zuo, Feng-Yuan; Mölder, Sannu

doi:10.1016/j.paerosci.2019.03.001

Cited by 62 publications

(10 citation statements)

References 112 publications

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“…Inward-turning intakes have received considerable attention because of their advantages of high compression ratio, high mass capture rate, small wetted area, etc. (Smart 1999;Zuo & Mölder 2019;Zuo et al 2019). However, due to the three-dimensional converging geometry of this type of intake, a clear characterization seems to be very challenging; therefore, it is helpful to use simplified models to explore the basic characteristics and mechanisms of the flow.…”

Section: Introductionmentioning

confidence: 99%

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Converging near-elliptic shock waves

Zhang

et al. 2020

J. Fluid Mech.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Converging near-elliptic shock waves

Zhang

et al. 2020

J. Fluid Mech.

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“…Intakes that work based on such a flowfield, called wave-catcher intakes, are currently under the focus of researchers in the field of propulsion due to higher performance and pressure recovery in supersonic and hypersonic entering flow in airbreathing engines, 19 different aerodynamic conditions, 20 and combined cycle propulsions. 21 In the Busemann intake, shockwaves to redirect the flow are weak and the flow direction is not highly changed from the streamline, and then it does not need a strong shockwave to return to the mainstream direction. Consequently, the process can reasonably be considered isentropic.…”

Section: Designmentioning

confidence: 99%

“…DEA number is calculated by numerical solving of equation (21), and the result should be rounded and reset according to the design requirements. As a result, C 2 can be recalculated by equation (21), and then R is calculated by C 2 . Knowing r and R, the effective area of each tube is calculated as follows (Figure 10)…”

Section: Compressormentioning

confidence: 99%

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

Aryana¹

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This two-part article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part A of this article explains the design process comprising intake, compressor, detonation process, diffuser, axial turbine, and the exit nozzle. The main target is to design a high-performance low emission propulsion system capable of serving in a wide range of altitudes and flight Mach numbers that covers altitudes up to 20,000 m and flight Mach number up to the hypersonic edge. Designing the propulsion set, the design point is considered at the static condition in the sea level. Design results show the propulsion set can satisfy all requirements necessary for its mission.

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“…Internal conical flow, which usually serves as a basic model for internal compression systems including the inward-turning inlet (You 2011; Zuo & Mölder 2019), has received extensive attention. Owing to the specific constraint of internal contraction, some effects, such as the shock convergence, may result in serious total pressure loss and poor performance of the internal flow.…”

Section: Introductionmentioning

confidence: 99%

Intensification of non-uniformity in convergent near-conical hypersonic flow

Zhang

et al. 2021

J. Fluid Mech.

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The inevitable formation of a Mach disk at the central axis of a convergent conical shock wave may suffer from fundamental changes when the flow deviates from the axisymmetric condition. In this paper, the behaviours of near-conical shocks, which are generated by a circular ring wedge of $10^{\circ }$ at typical angles of attack (AoAs), are investigated at a free stream Mach number of 6 in a shock tunnel. To reveal the characteristics and mechanism of the flow, numerical analyses are carried out under the same conditions. The results indicate that when the flow deviates from axial symmetry, the circumferential non-uniformity is remarkably intensified as the shock converges downstream. The converging centre shifts against the inclination of the incoming flow and moves to the leeward side. For a sufficiently small AoA, the formation of a Mach disk remains similar to that in the axisymmetric case, although the Mach disk shrinks in size and is slightly flattened. As the circumferential non-uniformity of the shock increases at an AoA of approximately $3^{\circ }$ , a pair of kinks separate the shock surface into two discontinuous segments with the stronger shock segment on the windward side and the weaker shock segment on the leeward side. When the AoA increases further, the shrinkage of the Mach disk continuously occurs, and the Mach disk is eventually replaced by a regular reflection. The discontinuity of a convergent shock with flattening on the separated shock segments and the insufficient strength increase during the subsequent convergence are responsible for the appearance of regular reflection.

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Hypersonic wavecatcher intakes and variable-geometry turbine based combined cycle engines

Cited by 62 publications

References 112 publications

Converging near-elliptic shock waves

Converging near-elliptic shock waves

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

Intensification of non-uniformity in convergent near-conical hypersonic flow

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