航空发动机燃烧室燃烧过程与排放物生成的反应动力学数值模拟

选用正癸烷作为航空煤油的替代燃料,建立了正癸烷的化学反应详细机理与简化机理(包括50种组分,118个基元反应).分别采用详细机理与简化机理对正癸烷在激波管中的着火延迟时间、在预混燃烧炉内的燃烧过程进行了数值计算,并与实验结果进行了对比分析.同时,耦合该简化机理与CFD计算软件Fluent,对某型航空发动机环管形燃烧室中单个火焰筒内流动特性与燃烧过程、排放物及活性中间组分生成的反应动力学特性进行了详细分析,并与采用C₁₂H₂₃为燃料的单步反应机理的计算结果进行了对比分析.结果表明:采用简化机理计算得到的着火延迟时间、反应物与各主要生成物摩尔分数的整体变化趋势与实验数据吻合较好;与采用C₁₂H₂₃为燃料的单步反应机理相比,采用正癸烷为替代燃料的简化反应机理计算得到的温度场分布更符合实际,其出口平均温度亦更为接近燃烧室出口设计温度;同时,能更为详细了解燃料低温裂解过程及裂解产物、中间产物及主要排放物的生成规律.      

Assessment of gas temperature fluctuations in the GTE combustion chamber exit section at generalizing experimental data on fuel combustion efficiency

It is suggested that gas composition at every point of the combustion chamber exit section be characterized by the temperature values T _i (“ideal” temperature) corresponding to the local values of the air-to-fuel coefficient α _i under complete fuel combustion (ν _comb ≈ 1). It is assumed that the values of T _i are distributed over the exit section area (gas mass) linearly and the values of T _imax and T _imin can be determined by the experimental data on the gas temperature fields in the combustion chambers. The distribution of temperatures T _i is used when it is necessary to generalize the experimental data on fuel combustion efficiency in GTE combustion chambers.     

等离子体助燃对燃烧产物影响的实验

采用介质阻挡放电在燃烧实验段中产生等离子体,进行了等离子体助燃条件下丙烷/空气混合气燃烧过程影响因素及其规律的实验研究.测量了空气、丙烷/空气混合气介质阻挡放电的光谱特性,通过烟气分析仪测量燃烧产物成份,得到了燃烧产物中O₂,CO体积分数随时间的变化,研究了激励器放电电压、空气流量、丙烷流量对燃烧产物的影响.实验结果表明:等离子体助燃时,O₂和CO体积分数变化速率增大;稳定燃烧后O₂和CO体积分数小于常规燃烧的,燃烧效率提高;减小放电电压,增大空气、丙烷流量,等离子体助燃的效果减弱.      

Electric currents and voltage drops along auroral field lines

The current state of knowledge concerning Birkeland currents (j _∥) and parallel electric field (E _∥) is briefly reviewed. Four types of j _∥ are discussed-the primary ‘region 1’ sheets, the ‘region 2’ sheets which parallel them and which seem to close in the partial ring current, the cusp currents which appear to correlate with interplanetary B _y, and the ‘Harang filament’. The energy required by E _∥ and by the associated particle acceleration processes seems to be derived from j _∥. Much of the evidence for e _∥ comes from particles, from ‘inverted V’ spectra, rising ion beams and expanded loss cones, while ‘conies’ may signify acceleration by Electrostatic Ion Cyclotron (EIC) waves, associated with beams accelerated by E _∥. Different theoretical studies predict for E _∥ a smooth, disordered or abrupt structure, and evidence for all 3 types can be deduced from S3-3 electric field probe observations.

     

Certain features of GTE combustion chamber open-type nozzles

In this paper, we consider the capability of GTE centrifugal open-type nozzles to recover combustion in the main combustion chamber at short-term fuel cutoffs into the fuel manifolds, when the anti-surge system operates, as well at actuation of “emergency brake” or the “dipping and shutdown valve”. We describe some features of the centrifugal open-type nozzles that make it possible to ensure the stable operation of the combustion chamber even at the “lean” blow-off boundary at α _CC ^max ≤ 65. The possibility of combustion recovery without using the spark plugs after the anti-surge system actuation has been experimentally confirmed.     

RANS simulations on combustion and emission characteristics of a premixed NH3/H2 swirling flame with reduced chemical kinetic model

Ammonia (NH₃) is considered as a potential alternative carbon free fuel to reduce greenhouse gas emission to meet the increasingly stringent emission requirements. Co-burning NH₃ and H₂ is an effective way to overcome ammonia’s relative low burning velocity. In this work, 3D Reynolds Averaged Navier-Stokes (RANS) numerical simulations are conducted on a premixed NH₃/H₂ swirling flame with reduced chemical kinetic mechanism. The effects of (A) overall equivalence ratio Φ and (B) hydrogen blended molar fraction X_H2 on combustion and emission characteristics are examined. The present results show that when 100%NH₃-0%H₂-air are burnt, the NO emission and unburned NH₃ of at the swirling combustor outlet has the opposite varying trends. With the increase of Φ, NO emission is found to be decreased, while the unburnt ammonia emission is increased. NH₂ → HNO, NH → HNO and HNO → NO sub-paths are found to play a critical role in NO formation. Normalized reaction rate of all these three sub-paths is shown to be decreased with increased Φ. Hydrogen addition is shown to significantly increase the laminar burning velocity of the mixed fuel. However, adding H₂ does not affect the critical equivalence ratio corresponding to the maximum burning velocity. The emission trend of NO and unburnt NH₃ with increased Φ is unchanged by blending H₂. NO emission with increased X_H2 is increased slightly less at a larger Φ than that at a smaller Φ. In addition, reaction rates of NH₂ → HNO and HNO → NO sub-paths are decreased with increased X_H2, when Φ is larger. Under all tested cases, blending H₂ with NH₃ reduces the unburned NH₃ emission, especially for rich combustion conditions. In summary, the present work provides research finding on supporting applying ammonia with hydrogen blended in low-emission gas turbine engines.     

CARS spectroscopy of CH4 for implication of temperature measurements in supercritical LOX/CH4 combustion

Experimental and theoretical investigations of coherent anti-Stokes Raman spectroscopy of CH₄ have been carried out. Experimental spectra were measured in a heated high-pressure test cell and compared with numerical simulations. Good agreement was obtained for the temperature and the pressure dependence of CARS spectra in the ranges 300–1100 K and 0.1–5.0 MPa. The observed dependencies provide useful guidance for CARS thermometry, allowing quantitative measurements of temperature in high-pressure combustors. Application of multiplex CH₄ CARS thermometry for single-shot measurements in a LOX/CH₄ combustion at high pressure was demonstrated at supercritical conditions (5.6 MPa).     

Interaction of non-perpendicular/parallel solar wind shock waves with the earth's magnetosphere

The interaction of travelling interplanetary shock waves with the bow shock-magnetosphere system is considered. We consider the general case when the interplanetary magnetic field is oblique to the Sun-planetary axis, thus, the interplanetary shock is neither parallel nor perpendicular. We find that an ensemble of shocks are produced after the interaction for a representative range of shock Mach numbers. First, we find that the system S ₊ R _– CS _– S ₊ appears after the collision of travelling fast shock waves S ₊ (Mach number M = 2 to 7) with the bow shock. Here, S _– and R _– represent the slow shock wave and slow rarefaction wave, and C represents the contact surface. It is shown that in the presence of an interplanetary field that is inclined by 45° to the radial solar wind velocity vector, the waves R _– and S _– are weak waves and, to the first degree of approximation, the situation is similar to the previously studied normal perpendicular case. The configuration, R ₊ C _m S _– S ₊ or R ₊ C _m R _– S ₊ where C _m is the magnetopause, appears as the result of the fast shock wave's collision with the magnetopause. In this case the waves S _– and R _– are weak. The fast rarefaction wave reflected from the magnetosphere is developed similar to the case for the collision of a perpendicular shock. The shock wave intensity is varied for Mach numbers from 2 to 10. Thus, in the limits of the first approximation, the validity of the one-dimensional consideration of the nonstationary interaction of travelling interplanetary shock waves with the bow shock-magnetosphere system is proved. The appearance of the fast rarefaction wave, R ₄, decreasing the pressure on the magnetosphere of the Earth after the abrupt shock-like contraction, is proved. A possible geomagnetic effect during the global perturbation of the SSC or SI⁺ type is discussed.An invited paper presented at STIP Workshop on Shock Waves in the Solar Corona and Interplanetary Space, 15–19 June, 1980, Smolenice, Czechoslovakia.     

乙醇燃烧加热空气污染物对煤油超燃的影响

在燃烧室入口来流马赫数为2.5的条件下,研究乙醇燃烧加热空气污染物对煤油超声速燃烧的影响.在加热器中,采用预混稳态燃烧火焰模型和61组分388步详细反应机理模拟乙醇燃烧加热过程,获得与实验温度条件相同的详细污染出口组分组成.其主要污染空气作为煤油超声速燃烧室的入口组分,采用17组分30步反应机理模拟煤油超声速燃烧过程,研究了污染物组分对煤油超燃室性能的影响.通过化学动力学和热力学分析,对比了地面电加热、乙醇燃烧加热和25km高空三种工况.结果表明:由于自由基作用以及平 均分子质量的减小和平均比定压热容的增加,乙醇燃烧加热污染空气造成超燃室的燃烧效率和内推力均上升.      

Non-linear resonant excitation of whistler mode waves in the Earth's ionosphere

We examine the resonant non-linear interaction in the Earth's ionosphere of two powerful high frequency radio beams with frequencies f ₁ and f ₂ (both larger than the plasma frequency at F2_max) and wave numbers k ₁ and k ₂ such that a whistler mode wave can be excited with a frequency f ₃ = f ₁ — f ₂ and a wave number k ₃ = k ₁ – k ₂. The feasibility of an effective ground based installation, sited at low latitudes, is discussed and the field strength of the wave emerging from a 10 km wide ionospheric region illuminated by the beams is evaluated for a range of transmitted frequencies, beam orientations and plasma frequencies in the interaction region. It is suggested that the longitude dependence of the enhancement of VLF noise bands detected by the Ariel 3 satellite may be due to a non-linear interaction of this type between any two or more medium wavelength signals from areas where there is a high concentration of commercial broadcasting stations, such as the NE region of the U.S.A.     

Evaluation of the influence of a measurable parameter error on precision of determining αΣ and Tg* by regression models

We present the regression models for determining the total excess air ratio α_Σ and gas temperature T _g ^* upstream of the high-pressure turbine formed on the basis of the engine parameter values that are regularly measured. The sensitivity of the regression models presented to the sensor and instrumentation precision is studied. The errors of measuring and calculating α_Σ and T _g ^* in different altitude-speed engine operation conditions are shown.     

Absolute and Convective Instabilities of Circularly Polarized Alfvén Waves

We discuss the recent progress in studying the absolute and convective instabilities of circularly polarized Alfvén waves (pump waves) propagating along an ambient magnetic field in the approximation of ideal magnetohydrodynamics (MHD). We present analytical results obtained for pump waves with small dimensionless amplitude a, and compare them with numerical results valid for arbitrary a. The type of instability, absolute or convective, depends on the velocity U of the reference frame where the pump wave is observed with respect to the rest plasma. One of the main results of our analysis is that the instability is absolute when U _l < U < U _r and convective otherwise. We study the dependences of U _l and U _r on a and the ratio of the sound speed to the Alfvén speed b. We also present the results of calculation of the increment of the absolute instability on U for different values of a and b. When the instability is convective (U < U _l or U > U _r) we consider the signalling problem, and show that spatially amplifying waves exist only when the signalling frequency is in two symmetric frequency bands. Then, we write down the analytical expressions determining the boundaries of these frequency bands and discuss how they agree with numerically calculated values. We also present the dependences of the maximum spatial amplification rate on U calculated both analytically and numerically. The implication of the obtained results on the interpretation of observational data from space missions is discussed. In particular, it is shown that circularly polarized Alfvén waves propagating in the solar wind are convectively unstable in a reference frame of any realistic spacecraft.     

Presupernova models and supernovae

Present status of the theories for presupernova evolution and triggering mechanisms of supernova explosions are summarized and discussed from the standpoint of the theory of stellar structure and evolution. It is not intended to collect every detail of numerical results thus far obtained, but to extract physically clear-cut understanding from complexities of the numerical stellar models. For this purpose the evolution of stellar cores is discussed in a generalized fashion. The following types of the supernova explosions are discussed. The carbon deflagration supernova of intermediate mass star which results in the total disruption of the star. Massive star evolves into a supernova triggered by photo-dissociation of iron nuclei which results in a formation of a neutron star or a black hole depending on its mass. These two are typical types of the sueprnovae. Between them there remains a range of mass for which collapse of the stellar core is triggered by electron captures, which has been recently shown to leave a neutron star despite oxygen deflagration competing with the electron captures. Also discussed are combustion and detonation of helium or carbon which take place in accreting white dwarfs, and the collapse which is triggered by electron-pair creation in very massive stars.Appendix: Notations A mass number of atomic nucleus - B _v(a, b) incomplete beta function - c _p specific heat at constant pressure - c _p sound velocity - c(sub) center of the star - E _e mean energy of an electron captured by nucleus - E _n nuclear energy release from unit mass of the nuclear fuel specified by n - E _thr threshold energy (9.3) - E _thr,0 energy difference between the ground states of daughter nucleus and parent nucleus (9.1) - E energy of gamma ray emitted from daughter nucleus (9.1) - E _v mean energy of a neutrino emitted by electron capture (9.1) - f flatness parameter (2.17) - g local gravitational acceleration (2.16) - H atomic mass unit - H _p scale height of pressure (2.22) - H (sub) hydrogen-burning shell - k Boltzmann constant - l mixing length of convection - L _cr(M _r ) local Eddington's critical luminosity (4.3) - L _n integrated nuclear energy generation rate by nuclear fuel specified by n - L _v neutrino luminosity - L _{v, cr}(M _r ) local Eddington's critical neutrino luminosity (11.2) - M (current) mass of a star - m _M core mass contained interior to the carbon-burning shell - M _Ch Chandrasekhar's limiting mass (9.6) - M _H core mass contained interior to the hydrogen-burning shell - M _He core mass contained interior to the helium-burning shell - M _ms mass of a star at its zero-age min-sequence - M _O core mass contained interior to the oxygen-burning shell - M _r mass contained interior to a shell at r - M _Si core mass contained interior to the silicon-burning shell - M _WD mass of white dwarf (7.1) - M ₀ normalization factor to the non-dimensional mass (3.3) - M ₁ core mass (3.6) - N polytropic index between pressure and density (2.3) - n polytropic index between pressure and temperature (10.1) - N _A Avogadro number - N _ad adiabatic polytropic index - N _e number of electrons in unit mass of matter - NSE nuclear statistical equilibrium - P pressure - ph (sub) photosphere - Q _e mass fraction of the envelope exterior of the shell e (2.14) - R stellar radius - r radial distance of a shell - r ₀ normalization factor to the non-dimensional radius (3.2) - s specific entropy - S _i specific entropy of ions - T temperature - U homology invariant defined by (2.1) - u _gas specific internal energy of gas - u _rad energy of the radiation field per volume in which unit mass of gas is contained (6.4) - V homology invariant defined by (2.2) - _def velocity of deflagration front (6.10) - X concentration by weight of hydrogen - Y concentration by weight of helium - Y _e mole number of electrons in one gram of matter (9.7) - Y _v mole number of neutrinos in one gram of matter - Z concentration by weight of the elements other than hydrogen and helium - z shock strength (6.6) - 1 (sub) usually denotes the core edge (2.13) - ratio of the mixing length to the scale height of pressure (l/H _p ) - ratio of gas pressure to the total pressure - ratio of the specific heats - gD locus of singularity in U-V plane (2.5) - M(H _p ) mass contained within unit scale height of pressure (4.4) - _ec energy rate by electron captures (9.5) - _n nuclear energy generation rate by the nuclear fuel specified by n - _v neutrino loss rate - L _v ^(D) neutrino loss rate excluding the neutrinos from the electron captures (9.4) - non-dimensional density (3.1) - P/, not the non-dimensional temperature (2.7) - _W Weinberg's angle (5.8) - opacity - _v neutrino opacity (11.2) - describes the effect of electron degeneracy in equation of state (2.19) - _ec rate of electron capture - mean molecular weight - _e mean molecular weight of electrons - _e chemical potential of an electron excluding the rest mass (8.1) - _i mean molecular weight of ions - non-dimensional radius (3.1) - non-dimensional pressure (3.1) - matter density - _cr ^GR critical density above which the general relativistic instability sets in - _cr critical density for reimplosion of the core by beta processes (Section 5) - _ign density at the ignition - _nse density above which the deflagrated matter results in NSE composition - _e non-dimensional entropy of electron-per one electron in units of k(9.2) - _ff timescale of free fall (6.2) - _h (H _p ) timescale of heat transport over unit scale height of pressure (4.4) - _n nuclear timescale for a change in temperature (6.1) - non-dimensional mass (3.1) - _e chemical potential of an electron in units of kT (8.1)     

Lift coefficient prediction at high angle of attack using recurrent neural network

In this paper, identification of dynamic stall effect of rotor blade is considered. Recurrent Neural Networks have the ability to identify the nonlinear dynamical systems from training data. This paper describes the use of recurrent neural networks for predicting the coefficient of lift (C_Z) at high angle of attack. In our approach, the coefficient of lift (C_Z) obtained from the experimental results (wind tunnel data) at different mean angle of attack θ_mean is used to train the recurrent neural network. Then the recurrent neural network prediction is compared with experimental ONERA OA212 airfoil data. The time and space complexity required to predict C_Z in the proposed method is less and it is easy to incorporate in any commercially available rotor code.     

Experimental study on NOx emission correlation of fuel staged combustion in a LPP combustor at high pressure based on NO-chemiluminescence

Experimental investigations on NO_x emissions of a single-cup, Lean Premixed Prevaporized (LPP), module combustor were carried out at elevated inlet temperature and pressure up to 810 K and 2.0 MPa, close to the real operating conditions of aero-engine combustors. This LPP combustor adopts centrally staged fuel injections which could produce separated stratified swirling spray flame. In the NO_x emissions measurements, the ranges of dome equivalence ratio and fuel stage ratio were from 0.55 to 0.58 and 8% to 24%, respectively. The optical diagnosis on separated stratified swirling spray flame were carried out with fuel stage ratio changing from 15% to 30%. Therefore, NO* and OH* chemiluminescence images were obtained. The results show that NO_x emissions increase with the increase of the fuel stage ratio. And from the chemiluminescence images, the main flame and pilot flame are found weakly coupled. The pilot flame plays a significant role in NO_x emission production because of its higher adiabatic flame temperature. Based on the results of chemiluminescence optical tests, a new NO_x emission prediction model is proposed based on the Lefebvre’s single flame model. The estimate of local equivalence ratio of the pilot stage’s non-premixed flame is modified considering the characteristics of spray combustion, and a “PLUS” emission prediction model suitable for separated stratified swirling spray flame is obtained. Compared to the experimental data, the “PLUS” model exhibits a good prediction in a range of ±13% of deviation.     

Electron density and temperature,as measured by the mutual impedance experiment on board GEOS-1

The mutual impedance experiment on GEOS-1 provides an original diagnostic of the thermal electron population. The electron density N _e, and temperature T _e, are derived from the plasma frequency and Debye length, the values of which determine the shape of the frequency dependent mutual impedance curves. The existing limits of the method are pointed out. They may be instrumental or arise from a lack of theoretical development, for instance when the steady magnetic field or the drift velocity of the plasma cannot be neglected. Nevertheless, first geophysical results have been derived, using measurements obtained on the dayside of the equatorial magnetosphere where most of the data enter within the above limits. In particular, we have drawn a map of the dayside magnetosphere, in terms of densities, Debye lengths, temperatures, at geocentric distances of 4 to 7 Earth radii. The conventional shape of the plasmasphere is recognized, but the temperatures obtained are lower than expected (2 eV at apogee, outside the plasmasphere). The influence of the magnetic activity on apogee measurements is reported: N _e values and A _m indices are shown to be correlated, but it is not the case for T _e and A _m. Finally, detailed T _e and N _e profiles are shown, and the presence of a plasmapause boundary is discussed.     

加力燃烧室用齿冠状混合器的数值研究与验证

基于CFD(computational fluid dynamics)技术,分别采用有限速率/涡耗散(finite-rate/eddy-dissipation)、涡耗散(eddy-dissipation)和涡耗散概念(EDC)燃烧模型,对一种曲面齿冠状混合器作用下的加力燃烧室进行数值计算.计算结果表明:曲面齿冠状混合器下游产生明显的流向涡对,流向涡的存在可以增强内外涵冷热气流掺混;与直面齿冠状混合器相比,曲面齿冠状混合器下游流向涡强度大于直面齿冠状混合器,其混合效率高于直面齿冠状混合器;加力燃烧室内氧气和二氧化碳质量分数分布结构表明了涡耗散模型的计算更为合理;计算结果可为加力燃烧室混合器选型和燃烧数值模拟提供依据.