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| 1 | Role of electrodes in ambient electrolytic decomposition of hydroxylammonium nitrate (HAN) solutions显示文摘Decomposition of hydroxylammonium nitrate (HAN) solution with electrolytic decomposition method has attracted much attention in recent years due to its efficiencies and practicability.However,the phenomenon has not been well-studied till now. By utilizing mathematical model currently available,the effect of water content and power used for decomposition was studied. Experiment data shows that sacrificial material such as copper or aluminum outperforms inert electrodes in the decomposition of HAN solution. In the case of using copper wire to electrolyse HAN solutions, approximately 10 seconds is required to reach 100℃ regardless of concentration of HAN. In tem of power consumption,100W-300W was found to be the range in which decomposition could be triggered effectively using copper wire as electrodes. | Kai SengKoh Jitkai Chin Tengku F.Wahida Ku Chik | 2013 | Propulsion and Power Research2013，2，3： | 12 |
| 2 | Turbine blade temperature calculation and life estimation-a sensitivity analysis显示文摘The overall operating cost of the modern gas turbines is greatly influenced by thedurability of hot section components operating at high temperatures.In turbine operatingconditions,some defects may occur which can decrease hot section life.In the present paper,methods used for calculating blade temperature and life are demonstrated and validated.Usingthese methods,a set of sensitivity analyses on the parameters affecting temperature and life ofa high pressure,high temperature turbine first stage blade is carried out.Investigateduncertainties are:(1)blade coating thickness,(2)coolant inlet pressure and temperature(asa result of secondary air system),and(3)gas turbine load variation.Results show thatincreasing thermal bamier coating thickness by 3 times,leads to rise in the blade life by 9times.In addition,considering inlet cooling temperature and pressure,deviation in temperaturehas greater effect on blade life.One of the interesting points that can be realized from theresults is that 300 hours operation at 70%load can be equal to one hour operation atbase load. | Majid Rezazadeh Reyhani Mohammad Alizadeh Alireza Fathi Hiwa Khaledid | 2013 | Propulsion and Power Research2013，2，2： | 9 |
| 3 | Effect of surface roughness on the aerodynamic performance of turbine blade cascade显示文摘The effect of surface roughness on the boundary development and loss behavior of turbine blades is investigated with different Reynolds numbers in this paper.The result shows that the velocity profile in boundary layer is plumper on rough surface than on smooth blade.The aerodynamic loss is lowered at low Reynolds number,but becomes significantly large at high Reynolds number.The total pressure loss coefficient of cascade can reach a top increase of 129%for rougher blades comparing with smooth blades at Re=300000. | Tao Bain Jingyuan Liu Weihao Zhang Zhengping Zou | 2014 | Propulsion and Power Research2014，3，2： | 9 |
| 4 | Light-weighting in aerospace component and system design显示文摘Light-weighting involves the use of advanced materials and engineering methods to enable structural elements to deliver the same,or enhanced,technical performance while using less material.The concept has been extensively explored and utilised in many industries from automotive applications to fashion and packaging and offers significant potential in the aviation sector.Typical implementations of light-weighting have involved use of high performance materials such as composites and optimisation of structures using computational aided engineering approaches with production enabled by advanced manufacturing methods such as additive manufacture,foam metals and hot forming.This paper reviews the principal approaches used in light-weighting,along with the scope for application of light-weighting in aviation applications from power-plants to airframe components.A particular area identified as warranting attention and amenable to the use of lightweighting approaches is the design of solar powered aircraft wings.The high aspect ratio typically used for these can be associated with insufficient stiffness,giving rise to non-linear deformation,aileron reversal,flutter and rigid-elastic coupling.Additional applications considered include ultralight aviation components and sub-systems,UAVs,and rockets.Advanced optimisation approaches can be applied to optimise the layout of structural elements,as well as geometrical parameters in order to maximise structural stiffness,minimise mass and enable incorporation of energy storage features.The use of additive manufacturing technologies,some capable of producing composite or multi-material components is an enabler for light-weighting,as features formally associated with one principal function can be designed to fulfil multiple functionalities。 | L.Zhu N.Li P.R.N.Childs | 2018 | Propulsion and Power Research2018，7，2： | 8 |
| 5 | Study on motion of rigid rod on a circular surface using MHPM显示文摘In this paper motion of rigid rod on a circular surface is studied analytically.A new analytical method called modified homotopy perturbation method(MHPM)is applied for solving this problem in different initial conditions to show capability of this method.The goveming equation for motion of a nigid rod on the circular surface without slipping have been solved using MHPM.The efficacy of MHPM for handling nonlinear oscillation systems with various small and large oscillation amplitudes are presented in comparison with numerical benchmarks.Outcomes reveal that MHPM has an excellent agreement with numerical solution.The results show that by decreasing the oscillation amplitude,the velocity of rigid rod decreases and for A=w3 the velocity profile is maximum. | Seiyed E.Ghasemi Ali Zolfagharian D.D.Ganji | 2014 | Propulsion and Power Research2014，3，3： | 7 |
| 6 | Review on film coolingofliquidrocketengines显示文摘Film cooling in combination with regenerative cooling is presently considered as an efficient method to guarantee safe operation of liquid rocket engines having higher heat flux densities for long duration.This paper aims to bring all the research carried out in the field of liquid rocket engine film cooling since 1950.The analytical and numerical procedure followed,experimental facilities and measurements made and major inferences drawn are reviewed in detail,and compared where ever possible.Review has been made through a discussion of the analyses methodologies and the factors that influence film cooling performance.An effort has also been made to determine the status of the research,pointing out critical gaps,which are still to be explained and addressed by future generations. | S.R.Shine S.Shri Nidhi | 2018 | Propulsion and Power Research2018，7，1： | 7 |
| 7 | Comparative performance analysis of combinedcycle pulse detonation turbofan engines (PDTEs)显示文摘Combined-cycle pulse detonation engines are promising contenders for hypersonic propulsion systems.In the present study,design and propulsive performance analysis of combined-cycle pulse detonation turbofan engines(PDTEs)is presented.Analysis is done with respect to Mach number at two consecutive modes of operation:(1)Combined-cycle PDTE using a pulse detonation afterburner mode(PDA-mode)and(2)combined-cycle PDTE in pulse detonation ramjet engine mode(PDRE-mode).The performance of combined-cycle PDTEs is compared with baseline afterbuming turbofan and ramjet engines.The comparison of afterburning modes is done for Mach numbers from 0 to 3 at 15.24 km altitude conditions,while that of pulse detonation ramjet engine(PDRE)is done for Mach 1.5 to Mach 6 at 18.3 km altitude conditions.The analysis shows that the propulsive performance of a tubine engine can be greatly improved by replacing the conventional afterbumer with a pulse detonation afterburner(PDA).The PDRE also outperforms its ramjet counterpart at all flight conditions considered herein.The gains obtained are outstanding for both the combined-cycle PDTE modes compared to baseline turbofan and ramjet engines. | Sudip Bhattrai Hao Tangn | 2013 | Propulsion and Power Research2013，2，3： | 7 |
| 8 | Ultrasonic fatigue tests at high temperature on an austenitic steel显示文摘The objective of this paper is to study the gigacycle fatigue behavior of an austenitic steel at temperatures of 6001C and 700℃under fully reverse loading(R=-1).Numerical simulation by finite element method(FEM)was used to design the specimens and to analyze the effects of the variation in the dynamic Young modulus with temperature from measurements of the ultrasonic resonance frequency.Finally,new stress-life curves for this material are presented for a lifetime range from 10^(5)to 10^(9)cycles at room temperature,600℃and 700℃. | D.Wagner F.J.Cavalieri C.Bathias N.Ranc | 2012 | Propulsion and Power Research2012，1，1： | 6 |
| 9 | Investigation of flow resistance characteristics of endothermic hydrocarbon fuel under supercritical pressures显示文摘The characteristics of flow resistance of a typical hydrocarbon fuel(RP-3)flowthrough adiabatic horizontal miniature tubes at supercritical pressures are experimentallyinvestigated for both laminar and turbulent flow.The experiments are conducted by using along tube measuring section and a short tube measuring section simultaneously in order toeliminate the effect of local pressure drop.In these experiments,the temperature of RP-3changes from(295 to 789)K and the reduced pressure(P/Pc,Pc=2.33 MPa)ranges from 1 to2.58,the mass flux is up to 1572.7 kg/(m^(2).s).Test results indicate that frictional pressuredrops for various supercritical pressures at the same mass flux can be considered as equalwith each other when the reduced temperature Tb/Tpc<0.95.When Tb/Tpc>0.95,differenceappears and increases with the increase of Tb/Tpc.Additionally,the friction factor(f)of thesupercritical fluid for turbulent flow has a critical value at Tb/Tpc=1,the values of f at thispoint for all pressures and mass fluxes are equal with each other.Moreover,at the same massflux,there are two comresponding friction factors for the same Re,one is in the region of Tb/Tpc<1,the other is in the region of Tb/Tpc> 1.Finally, classical conelations of frictionfactor is inapplicable when Tb/Tpc>0.95 at supercritical pressure and a new coelation hasbeen obtained based on the experimental data. | Chunben Zhang Guoqiang Xu Hongwu Deng Kun Zhu | 2013 | Propulsion and Power Research2013，2，2： | 6 |
| 10 | Buoyancy effect on heat transfer in rotating smooth square U-duct at high rotation number显示文摘The buoyancy effect on heat transfer in a rotating,two-pass,square channel is experimentally investigated in curent work.The classical copper plate technique is performed to measure the regional averaged heat transfer cofficients.In order to perform a fundamental research,all turbulators are removed away.Two approaches of altering Buoyancy numbers are selected:varying rotation number from 0 to 2.08 at Reynolds number ranges of 10000 to 70000,and varying inlet density ratio from 0.07 to 0.16 at Reynolds number of 10000.And thus,Buoyancy numbers range from 0 to 12.9 for both cases.According to the experimental results,the relationships between heat transfer and Buoyancy numbers are in accord with those obtained under different rotation numbers.For both leading and trailing surface,a critical Buoyancy number exists for each X/D location.Before the critical point,the effect of Buoyancy number on heat transfer is limited;but after that,the Nusselt number ratios show different increase rate.Given the same rotation number,higher wall temperature ratios with its corresponding higher Buoyancy numbers substantially enhance heat transfer on both passages.And the critical exceed-point that heat transfer from trailing surface higher than leading surface happens at the same Buoyancy number for different wall temperature ratios in the second passage.Thus,the stronger buoyancy effect promotes heat transfer enhancement at high rotation number condition. | Yang Li Guoqiang Xu Hongwu Deng Shuqing Tian | 2014 | Propulsion and Power Research2014，3，3： | 6 |
| 11 | Experimental and numerical investigation of design optimization of a partial admitted supersonic turbine显示文摘To obtain a high specific work output,the large pressure ratios across the turbine are required.This can be achieved using a supersonic turbine.When the fluid mass flow is low,the impulse kind of one or two stages supersonic turbine is employed.To prevent losses due to low blade aspect ratio and issues related to manufacturing and industrial problems,the turbine is used in partial admission conditions.Studies show that the turbine efficiency is highly dependent on the amount of partial admission coefficient.The turbine efficiency in full admission is high,but the use of partial admission lowers the additional losses.Therefore,there will be a degree of partial admission in which the turbine will have the highest efficiency.The aim of this work is to achieve the optimum partial admission for a special impulse turbine as a case study.Therefore,in the beginning,an appropriate model of losses is presented.Then,using a nonlinear design optimization code,the partial admission of an impulse supersonic turbine is optimized.This code is written using a genetic algorithm.Then,using three-dimensional numerical analysis,the optimal model will be selected.In the optimization problem,the turbine efficiency is the objective function.The amount of design parameters and constraints used in this process are ten and eight,respectively.After the optimization process,prototypes of designed and modified turbines are made and tested.Test results were compared and analyzed.The results showed that the turbine efficiency is improved between 2.5%and 3%depending on various operation conditions. | Reza Aghaei tog Abolghasem M.Tousin | 2013 | Propulsion and Power Research2013，2，1： | 5 |
| 12 | Flow and heat transfer of nanofluids over a rotating disk with uniform stretching rate in the radial direction显示文摘This paper studies flow and heat transfer of nanofluids over a rotating disk with uniform stretching rate.Three types of nanopaiticles-Cu,Al_(2)O_(3) and CuO-with water-based nanofluids are considered.The governing equations are reduced by Von Karman transformation and then solved by the homotopy analysis method(HAM),which is in close agreement with numerical results.Results indicate that with increasing in stretching strength parameter,the skin friction and the local Nusselt number,the velocity in radial and axial directions increase,whereas the velocity in tangential direction and the thermal boundary'layer thickness decrease,respectively.Moreover,the effects of volume fraction and types of nanofluids on velocity and temperature fields are also analyzed. | Chenguang Yin Liancun Zheng Chaoli Zhang Xinxin Zhang | 2017 | Propulsion and Power Research2017，6，1： | 5 |
| 13 | Development of high intensity low emission combustor for achieving flameless combustion ofliquid fuels显示文摘This paper presents the experimental and numerical results for a two stagecombustor capable of achieving flameless combustion with liquid fuels for different thermalheat inputs of 20,30,40 and 60 kW and heat release density of 5-15 MW/m^(3).Combustioncharacteristics and pollutant emissions are studied for three different fuels,kerosene,diesel andgasoline.The influence of droplet diameter on pollutant emissions at all conditions is studied.The fuel and oxidizer are supplied at ambient conditions.The concept of high swirl flows hasbeen adopted to achieve high intemal recirculation rates,residence time and increased dilutionof the fresh reactants in the primary combustion zone,resulting in flameless combustion mode.Air is injected through four tangential injection ports located near the bottom of the combustorand liquid fuel is injected through a centrally mounted pressure swirl injector.Computationalanalysis of the flow features shows that decrease in the exit port diameter of the primarychamber increases the recirculation rate of combustion products and helps in achieving theflameless combustion mode.Based on preliminary computational studies,a 30 mm primarychamber exit pont diameter is chosen for experimental studies.Detailed experimentalinvestigations show that flameless combustion mode was achieved with evenly distributedcombustion reaction zone and unifom temperature distribution in the combustor.Pollutant emissions of CO, NO_(x),C_(x)H_(y) are measured and compared for all operating conditions ofdifferent fuels and different thermal inputs. The acoustic emission levels are reduced by6-8 dB as combustion mode shifts from conventional mode to flameless combustion mode. | V.Mahendra Reddy Sudarshan Kumarn | 2013 | Propulsion and Power Research2013，2，2： | 5 |
| 14 | Thermo-diffusion effects on MHD stagnation point flow towards a stretching sheet in a nanofuid显示文摘Thermodiffusion effects on stagnation point flow of a nanofuid towards a stretching surface with applied magnetic field is presented.Similarity transforms are applied to reduce the equations that govem the flow to a system of nonlinear ordinary differential equations.Runge-K utta-Fehlberg method is applied to solve the sy stem.Results are compared with existing solutions that are special cases to our problem.Concrete graphical analysis is carried out to study the effects of different emerging parameters such as stretching ratio A,mag netic infuence parameter M,Prandtl number Pr,Lewis number Le,Brownian motion parameter Nb,thermophoresis parameter Nr,nanofluid Lewis number Ln,modified Dufour parameter Nd and Dufour solutal number Ld coupled with comprehensive discussions.Numerical effects of local Nusselt number,local Sherwood number and nanofluid Sherwood number are also discussed. | Umar Khan Naveed Ahmed Sheikh Irfan Ullah Khan Syed Taluseef Mohyud-din | 2014 | Propulsion and Power Research2014，3，3： | 5 |
| 15 | Numerical study of operational processes in a GOx-kerosene rocket engine with liquid film cooling显示文摘Combustion process inside kerosene-GOx rocket combustor with kerosene Alm cooling is studied,and a modeling approach is proposed.The paper suggests to use the Lagrangian particle tracking technique to model fuel film behavior while the continuous fluid is simulated via the Navier-Stokes system of Favre-averaged equations.The approach is validated over the 12 experimental regimes by the criterions of characteristic velocity and pressure,ence on the adiabatic wall temperatures and relatively low impact on the pressure.In general,phenomena,the calculation of operational processes becomes fast and robust yet precise en-the design process. | Evgenij A.Strokach Igor N.Borovik Vladimir G.Bazarov Oscar J.Haidn | 2020 | Propulsion and Power Research2020，9，2： | 5 |
| 16 | An experimental investigation on the trailing edge cooling of turbine blades显示文摘An experimental study was conducted to quantify the flow characteristics of the wall jets pertinent to trailing edge cooling of turbine blades.A high-resolution stereoscopic particle image velocimetry(PIV)system was used to conduct detailed flow field measurements to quantitatively visualize the evolution of the unsteady vortices and turbulent flow structures in the cooling wall jet streams and to quantify the dynamic mixing process between the cooling jet stream and the mainstream flows.The detailed flow field measurements were correlated with the adiabatic cooling effectiveness maps measured by using pressure sensitive paint(PSP)technique to elucidate underlying physics in order to explore/optimize design paradigms for improved cooling effectiveness to protect the critical portions of turbine blades from harsh environments. | Zifeng Yang Hui Hun | 2012 | Propulsion and Power Research2012，1，1： | 5 |
| 17 | Unsteady flow characteristic analysis of turbine based combined cycle(TBCC)inlet mode transition10.1016/j.jppr.2015.07.006显示文摘A turbine based combined cycle(TBCC)propulsion system uses a turbine-based engine to accelerate the vehicle from takeoff to the mode transition flight condition,at which point,the propulsion system performs a“mode transition”from the turbine to ramjet engine.Smooth inlet mode transition is accomplished when flow is diverted from one flowpath to the other,without experiencing unstart or buzz.The smooth inlet mode transition is a complex unsteady process and it is one of the enabling technologies for combined cycle engine to become a functional reality.In order to unveil the unsteady process of inlet mode transition,the research of over/under TBCC inlet mode transition was conducted through a numerical simulation.It shows that during the mode transition the terminal shock oscillates in the inlet.During the process of inlet mode transition mass flow rate and Mach number of turbojet flowpath reduce with oscillation.While in ramjet flowpath the flow field is non-uniform at the beginning of inlet mode transition.The speed of mode transition and the operation states of the turbojet and ramjet engines will affect the motion of terminal shock.The result obtained in present paper can help us realize the unsteady flow characteristic during the mode transition and provide some suggestions for TBCC inlet mode transition based on the smooth transition of thrust. | Jun Liu Huacheng Yuan Rongwei Guo | 2015 | Propulsion and Power Research2015，4，3： | 4 |
| 18 | The zero-dimensional model of the scavenging process in the opposed-piston two-stroke aircraft diesel engine显示文摘The analysis of the scavenging process in two-stroke engines is important in terms of achieved performance and emission of toxic substances.The amount of mass of air used for the scavenging process and the amount mass of gas retained in the cylinder affect engine effi-ciency.When designing two-stroke engines,the most efficient charge exchange process defined by the scavenging efficiency parameter is desirable.The process of charge exchange in a twostroke opposed-piston aircraft diesel engine based on the assumed scavenging model was analyzed in this work.The charge exchange process was performed by a mechanical centrifugal compressor.A zero-dimensional engine model created in the AVL BOOST program was used for the research.The simulation tests were performed for the selected operating conditions,i.e.maximum continuous power.The analysis of the charge exchange process was accompanied by obtaining the basic engine operating parameters from the simulation calculations. | Ł.Grabowski K.Pietrykowski P.Karpinski | 2019 | Propulsion and Power Research2019，8，4： | 4 |
| 19 | Optimization of gas turbines for sustainable turbojet propulsion显示文摘Gas-turbines are widely used to power aero planes because they are light,compact with a high power-to-weight ratio.In the turbo jet engine,the main operating variables are:compressor pressure ratio rp and turbine inlet temperature(TIT).These variables affect the specific thrust and specific fuel consumption(SFC),which represent the main performance parameters.In addition to the analytical work,a computer program of the General Algebraic Modeling System(GAMS)was used for analysis and optimization.The analysis shows that the specific thrust strongly depends on turbine inlet temperature(TIT),where a 10%decrease in TIT results in 6.7%decrease in specific thrust and 6.8%decrease in SFC.Furthermore,the value of optimum pressure ratio rf for maximum specific thrust increases with TIT.A 10%decrease from design TIT results in 11.43%decrease in rf.The value of optimum pressure ratio for the turbojet engine operating at Ma=0.8 and altitude Alt=13000 m,and TIT=1700 K was found to be 14.&2015 National Laboratory for Aeronautics and Astronautics.Production and hosting by Elsevier B.V. | Yousef S.H.Najjar Ibrahim A.I.Balawneh | 2015 | Propulsion and Power Research2015，4，2： | 4 |
| 20 | Effects of variable permeability and radiation absorption on magnetohydrodynamic(MHD)mixed convective flow in a vertical wavy channel with traveling thermal waves显示文摘An analysis has been carried out to study the effects of radiation absorption and firstorder chemical reaction on unsteady mixed convective flow of a viscous incompressible electrically conducting fluid through a porous medium of variable permeability between two long vertical non conducting wavy channels in the presence of heat generation.The unsteadiness in the flow is due to traveling thermal wave imposed on the walls.The governing equations are solved subject to the relevant boundary conditions with the assumption that the solution consists of a mean part and a perturbed part.The zeroth-order,the first order and the total solution of the problem are numerically evaluated and displayed graphically for pertinent parameters.This model finds applications in studying fixed-bed catalytic reactors and packed bed heat exchangers. | P.V.Satya Narayana | 2015 | Propulsion and Power Research2015，4，3： | 4 |
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