Analysis on impulse characteristics of pulse detonation engine with nozzles
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Xiao-long Huang
,
Yang Kang
Abstract
In order to study the influence of different nozzle configurations on the gas–liquid two-phase pulse detonation engine (PDE) propulsion performance, the measurement system based on the tunable diode laser absorption spectroscopy (TDLAS) technology is built to measure the velocity and the temperature, while the high frequency dynamic pressure sensor is used to measure the nozzle gas pressure. Based on the momentum principle, the contribution mechanism of unsteady gas jet on thrust is obtained indirectly by TDLAS data. The results show that the impulses of PDE with non-nozzle, convergent nozzle, divergent nozzle and convergent–divergent nozzle are 1.95, 2.08, 1.85 and 2.16 N∙s within 20 ms of the exhaust period, respectively. The analysis reveals that the impulses of PDE with convergent and convergent–divergent nozzles are larger than that with non-nozzle, while the impulse of PDE with divergent nozzle is smaller than that with non-nozzle. The research results in this paper can provide reference for the design of nozzles for PDE.
Funding source: China Scholarship Council
Award Identifier / Grant number: 201906845059
Funding source: Natural Science Foundation of Jiangsu Province
Award Identifier / Grant number: BK20190439
Funding source: National Key Laboratory of Transient Physics
Award Identifier / Grant number: 6142604200202
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 11902143
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This work is supported by the China Scholarship Council (contract 201906845059), the Young Scientists Fund of the Natural Science Foundation of Jiangsu Province (No. BK20190439), the Fundamental Research Funds of National Key Laboratory of Transient Physics (No. 6142604200202), the National Natural Science Foundation of China (No. 11902143).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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- Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
- Predicting remaining useful life of turbofan engines using degradation signal based echo state network
- Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
- Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
- Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
- Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
- Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
- Performance enhancement and flow separation control in an S-duct by air injection
- Gas dynamic analysis of the modern single shaft gas turbine engine flow path
- Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
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