2019 Vol. 34, No. 10

Display Method:
Experiment on flow characteristics of a reverse-flow combustor
ZHAI Weikuo, HU Ge
2019, 34(10): 2081-2090. doi: 10.13224/j.cnki.jasp.2019.10.001
Abstract:
To reveal the flow field differences and flow characteristics between the non-reacting flow and the reacting flow, the flow fields at different sections of a reverse-flow combustor with different total pressure loss conditions were measured and investigated through particle image velocimetry (PIV) measurement technology. The result showed that: with the increase of the total pressure loss, the non-reacting flow field in the specific section was consistent, the penetrating depth,jet angle,reverse-zone position and size,and the flow line were all similar. Otherwise, the velocity rose. And the reacting flow field in the specific section was also consistent with the increase of the total pressure loss. Also there were some differences from the reacting flow field to the non-reacting flow field in the same total pressure loss condition. The relative motion of fuel injection and airflow will affect the flow field structure of the head zone of the combustor, and the velocity of reaction is faster than the non-reaction.
Experiment on atomization of high disturbance fuel nozzle
CHEN Lei, LONG Wuqiang
2019, 34(10): 2091-2097. doi: 10.13224/j.cnki.jasp.2019.10.002
Abstract:
In order to improve the fuel atomization and verify the feasibility of high perturbed atomization scheme applied to the fuel injection of aero-engine, the spray characteristics of V-shaped cross hole nozzlesand single hole nozzles were measured by using phase Doppler particle analyzer (PDPA) and high-speed photography technology. Results showed that with the increase of injection pressure, the atomization angle increased and the Sauter mean diameter(SMD) value decreased. The cross-hole structure had a significant promoting effect on fuel atomization. Under the same injection pressure and exit cross-section area conditions, the atomization cone angle of the cross-hole was larger and the SMD was smaller; at the same SMD, the required injection pressure of the cross-hole was much smaller than that of the traditional circular straight hole; with the increase of intersection angle, the spray cone angle and SMD were both improved. Air-assisted method can effectively increase the spray cone angle and reduce the SMD value, but the improvement effect decreased gradually with the increase of air pressure. Compared with the traditional single hole nozzle scheme, the high perturbation nozzle can greatly improve the atomization effect of the fuel under the same pressure conditions, and has great potential for aero engine application.
Effects of nozzle spacing on lean blowout performance and flow fields
JIANG Lei, WANG Bohan, XIAO Bo
2019, 34(10): 2098-2107. doi: 10.13224/j.cnki.jasp.2019.10.003
Abstract:
In order to deepen understanding of the influence of nozzle spacing on lean blowout and aerodynamic performance of gas turbine combustor, a dual-head model combustor with continuously adjustable nozzle position was designed based on the typical dual-stage swirling diffusion nozzles. The maximum flame propagation spacing between nozzles was measured and the dynamic process of flame propagation was analyzed with different initial equivalent ratios. Additionally, the effects of nozzle spacing on the lean blowout equivalent ratio, reacting flow field and root mean square velocity field were studied. The experimental results show that: with the increase of the equivalent ratio of 0.1, the dimensionless maximum flame propagation spacing increases by about 0.2,and the flame propagation process between nozzles can be roughly divided into four stages. The lean blowout equivalent ratio of single nozzle is bigger than that of double nozzles with arbitrary nozzle spacing. As the double nozzles spacing decreases, the lean blowout equivalent ratio first decreases and then increases. In addition, the decrease of nozzle spacing leads to jet mergence, decrease of radial velocity, increase of central jet velocity peak and decrease of size of central recirculation zone.As the nozzles move close to each other, the value and distributionarea of root mean square velocity between nozzles become larger and wider.
Modeling and uncertainty analysis of chemical reactor network model in lean premixed combustion chamber
MU Bin, LEI Fulin
2019, 34(10): 2108-2119. doi: 10.13224/j.cnki.jasp.2019.10.004
Abstract:
The chemical reactor network (CRN) model based on three-dimensional numerical simulation results of CFD has great advantage in fast and accurate prediction of NOx emissions for combustor. In this work, the characteristic distributions of flow and temperature fields in a lean premixed combustor were simulated using CFD method. The combustor was separated in several regions, includingpreheating region, flame front region, flame transition region, post flame region, central recirculation region and corner recirculation region, based on the fuel-air blending characteristics, velocity field, temperature field, OH distribution, and Damkohler number. A complex CRN model was established to characterize the flow characteristics and flame structure inside the combustion chamber. The preliminary verification of CRN model was performed with experimental data of lean premixed burner. The effects of several crucial parameters, including the residence time and the flue gas recirculation ratio, on NOx emission were analyzed through sensitivity and uncertainty analysis. The CFD-CRN hybrid method can quickly and effectively predict the NOx production of the lean premixed combustor under high equivalence conditions. The residence time disturbances of preheating zone and the flame front zone have more significant effects on emissions and stability of NOx prediction of CRN models under the same disturbance intensity. The flue gas recirculation ratio of CFD-CRN method should be accurately calculated under high adiabatic flame temperature, which has significant effect on NOx formation.
Numerical simulation of total pressure loss on vortex-reducer with bafflers
XIANG Yang, LUO Xiang
2019, 34(10): 2120-2130. doi: 10.13224/j.cnki.jasp.2019.10.005
Abstract:
The effect of different vortex reducers with bafflers on the characteristics of total pressure loss was studied by numerical simulation. Results showed that the total pressure loss was composed of the slow decrease in the bafflers because of work and the sharp decrease of velocity at the turning point due to the excessive tangential velocity. The loss was mainly caused by the former with long bafflers and by the latter with short bafflers. It was significant to reduce the work done by flow to bafflers, whilelimiting the tangential velocity. The total pressure loss of the system decreased and then increased with the increase of the number of bafflers and the outlet position. The shape and length of the bafflers also affected the total pressure loss.
Cooling and heat transfercharacteristics of high-pressure turbine blade with cutback squealer tip
WANG Weijie, MA Haiteng, ZHANG Qiang
2019, 34(10): 2131-2139. doi: 10.13224/j.cnki.jasp.2019.10.006
Abstract:
In order to study the surface heat transfer of turbine blades with cutback squealer tip, surface heat transfer coefficient was investigated experimentally through a transient wind tunnel experiment for an uncooled blade and a blade with dust purge holes. The experimental outcome was compared with the numerical simulation result. The uncertainty of the experiment was less than 5%. By analyzing the over tip leakage (OTL) flow condition, it revealed that on the uncooled blade tip, due to the cavity vortex and the separation bubbles, high surface heat transfer coefficient values were scattered on squealer rims of both pressure side (PS) and suction side (SS), and on cavity floor near the leading edge. A strip of low surface heat transfer coefficient values appeared onthe PS of the second half cavity. In the cooled case, coolant flow from dust purge holes was separated into two parts. The high-energy fluid merged into the OTL flow, resulting in multiple high surface heat transfer coefficient distributions on the SS rim, while the low-energy fluid flowed backward along the SS of the cavity. Cooling effectiveness can reach over 0.4 in this region.
Numerical study on water film formation on aerodynamic effect of axial flow fan
HOU Shengwen, WU Feng
2019, 34(10): 2140-2148. doi: 10.13224/j.cnki.jasp.2019.10.007
Abstract:
In order to study the effect of water film on aerodynamic charactristics of the fan, the mean square thickness of water film on blade surface was calculated by using water film equation combined with the parameters of the water droplets colliding with the wall surface. Then the sand grain roughness model was added to the numerical calculation to simulate the change of blade surface roughness caused by water film. Fan blades were numerically simulated under different rain ingestion rates and water droplet diameters. Results indicate that water film mainly distributes in the leading edge and root region of blade pressure surface. The water film’s thickness and depositional area are positively correlated with rain ingestion rate. In addition, the existence of water film can reduce the pressure ratio and temperature ratio of the fan. When the average diameter of the water droplet is 1000μm and the rain ingestion rate is 5%, thewater droplet depositionalarea is 0.0758m2, accounting for 33.91% of the pressure surface area of the blade.
Analysis of method of air mass flow measurement based on array of critical flow Venturi nozzle in high-altitude simulation facility
SU Jinyou, TIAN Jinhu
2019, 34(10): 2149-2157. doi: 10.13224/j.cnki.jasp.2019.10.008
Abstract:
In order to meet the accurate measurement of air flow under the low flow intake conditions of the engine high-altitude test, reduce the influence of the air flow surface layer in the intake duct, and weaken the correlation between the air flow measurement and the tested engine, the working characteristics of the single piece/combined critical flow Venturi nozzle (CFVN) were analyzed, and the calculation method of the air flow of the array of critical flow Venturi nozzle (ACFVN) was expounded. The calculation method of combined CFVN was also given. The combination structure was designed according to the given test engine and the size of the high-altitude cabin. The control method and test layout of the combined CFVN in high-altitude cabin were obtained. The design and application methods of the combined nozzles were verified by small-sized nozzles. The results show that the method of opening and closing the nozzles and adjusting the intake pressure could be applied in the high-altitude cabin, the test layout meets the measurement requirements, and the Turbulence of engine intake flow is better than 0.3%, meeting the requirements of engine high altitude simulation test.
Distributed electrical propulsion system design and fuel consumption evaluation for a blended-wing-body transport
DA Xingya, LI Yonghong, XIONG Neng
2019, 34(10): 2158-2166. doi: 10.13224/j.cnki.jasp.2019.10.009
Abstract:
Adistributed electrical propulsion system was preliminarily designed and its fuel consumption was evaluated for a blended-wing-body transport. Aerodynamic design and optimization for this blended-wing-body transport with 70t pay-loads were completed through numerical computations. At the design point of cruise Mach number 0.80 and cruise altitude 10km, the maximum lift-to-drag ratio reached 24. The preliminary design of distributed electrical propulsion system was accomplished by solving integral boundary layer equations. The electrical propulsion system was composed of 10 electrically driven fans with diameter of 1.45m, pressure ratio of 1.35 and cruise power of 2.94MW. An one-dimensional engine performance model considering the burning process was established and the engine fuel consumption was evaluated for different engine cycles. Analysis shows that the blended-wing-body configuration with distributed electrical propulsion can reduce the fuel consumption by 50% as compared with C-17 transport.
Mach number control strategy for continuous wind tunnel with second throat
CHEN Dan, ZHANG Yongshuang
2019, 34(10): 2167-2176. doi: 10.13224/j.cnki.jasp.2019.10.010
Abstract:
In order to reduce pressure fluctuation and improve Mach number stability in continuous trans-supersonic wind tunnel, it is necessary to study the Mach number control model of second throat.In view of the few descriptions involved in existing literature, taking 0.6m continuous transonic wind tunnel as an example, the principle of the Mach number control with second throat was analysed, then the precise position control of second throat was realized based on the double PID(proportion-integral-derivative) control mode of motion controller plus servo driver, and the combined control sequence of second throat and compressor speed was presented, and then the algorithm of segmented variable parameter fuzzy PID and cascade control was proposed to control the Mach number. Finally, experiments were carried out. The results show that the Mach number control accuracy can be better than 0.001, and the time of each Mach number polar curve (9 attack angles) can be controlled within 4minutes, proving that the control strategy proposed is effective, and can provide reference for the design and construction of continuous trans-supersonic wind tunnel.
Longitudinal flight characteristics analysis and control design for hybrid VTOL UAV in accelerative transition
WANG Zian, XU Jinfa
2019, 34(10): 2177-2190. doi: 10.13224/j.cnki.jasp.2019.10.011
Abstract:
A comprehensive aerodynamic/flight-control problem was studied on a high-cost hybrid vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) in the accelerative stage from hovering to cruising. A computational model of the rotor under oblique inflow was established based on the blade-element momentum theory (BEMT), and its accuracy was verified by comparison with the CFD calculation model. It was analyzed that the rotor system caused the aerodynamic focus of the aircraft to move forward, resulting in static instability effect, and its center should be placed after the center of gravity of the aircraft. By analyzing acceleration features and the control input margin under different acceleration strategies, the fixed -5 degree pitch angle and fixed throttle acceleration strategy were determined. Considering the control input redundancy and the different response of the actuator, the allocation criterion of frequency domain was adopted to realize static allocation. Considering the modeling error, the L1 adaptive attitude control framework was designed to achieve dynamic control stabilization, and the deflection simulation was used to verify its robustness. Flight test verified the effectiveness of the modeling method, acceleration strategy, and control law framework.
Optimization design of the inward turning inlet in the Mach number 3-6 wide velocity domain
DAI Chunliang, ZHANG Kunyuan
2019, 34(10): 2191-2202. doi: 10.13224/j.cnki.jasp.2019.10.012
Abstract:
Based on the parameterization study of the axisymmetric basic flowfield, a variable center body with properly small radius was selected, then the sensitivity analysis of other design parameters was conducted to obtain the influence law of design parameters on the overall performance of the basic flowfield. This showed that the coefficient c had the most obvious effect, and the coupling effect between various design parameters was also significant. The sample database was used to construct the corresponding neural network approximate model, and the three-objective optimization of the axisymmetric basic flowfield at Mach number of 6 was carried out in combination with the neighborhood cultivation multi-objective genetic algorithm. After the optimization, the internal compression ratio in the basic flowfield reduced by 17.7%, the total pressure recovery coefficient increased by 2.3%, and the static pressure ratio increased by 7.1%. Based on the optimization results, the inward turning inlet profile was designed. The results from its viscous numerical simulation at Mach number of 3-6 show that the optimized inward turning inlet can start normally at Mach number of 3, and has higher compression, better flow capture ability and total pressure recovery performance at Mach number of 4-6.
Impact of local cavities on evolution of the second-mode disturbances in hypersonic boundary layers
LI Chuang, DONG Ming
2019, 34(10): 2203-2210. doi: 10.13224/j.cnki.jasp.2019.10.013
Abstract:
The influence of local rectangular cavities on the evolution of the second-mode disturbances in a incoming Mach number 6.0 hypersonic boundary layer over a flat plate was investigated by using direct umerical simulation. The local scattering effect was quantified by a transmission coefficient defined as the ratio of perturbation amplitude downstream cavity to upstream cavity. It was found from the numerical results that, for a shallow cavity, thesecond-mode disturbance with a relatively low frequency was enhanced by the cavity, while the opposite was true when the frequency was high. In most of the cases, the transmission coefficient reduced with the increase of the cavity depth, implying a weaker enhancement or a stronger suppression effect. When the cavity depth exceeded a critical value, the dependence of the transmission coefficient on cavity depth was changed to a positive correlation, implying the emergence of a new regime. The critical depth relies on the disturbance frequency: it is larger for a lower frequency.
Numerical simulation on influence of thrust reverser device on aerodynamic erformance of blended-wing-body distributed propulsion system
LOU Yuzhu, CHEN Zhen, JIANG Shiyi
2019, 34(10): 2211-2217. doi: 10.13224/j.cnki.jasp.2019.10.014
Abstract:
In order to study the influence of the new thrust reverser device on the aerodynamic performance of the blended-wing-body distributed propulsion system, the fuselage was simplified into a two-dimensional airfoil, the numerical simulation method was used to study the angle of attack, the openness of the thrust reverser and the effect of the fan on/off on the flight parameters. Some suggestions about the design of the thrust reverser device on the blended-wing-body distributed propulsion system were carried out. The results show that when the thrust reverser and the fan are turned on, the lift coefficient and pitch moment coefficient of the model increase greatly; as the openness of thrust reverser increases, the lift coefficient and the pitching moment coefficient also increase; the attack angle of incoming flow also has a large impact on the aerodynamic performance of the blended-wing-body distributed propulsion system.
Rolling bearing fault diagnosis based on smoothness priors approach and fuzzy entropy
DAI Shaowu, CHEN Qiangqiang, NIE Zijian
2019, 34(10): 2218-2226. doi: 10.13224/j.cnki.jasp.2019.10.015
Abstract:
Due to the complexity of mechanical systems, the randomicity of the vibration signal on different scales, it’s necessary to analyze the vibration signal with fuzzy entropy (FE) in a multi-scale way. Based on multi-scale fuzzy entropy analysis of vibration signals, a method of rolling bearing fault diagnosis based on FE and the smoothness priors approach (SPA) was put forward. The SPA algorithm was used to decompose the vibration signal, and the trend with de-trend was obtained. Secondly, the FE of the trend and de-trend was calculated. The FE entropies were accordingly seen as the characteristic vectors, then inputed to the optimized support vector machine (OSVM). Finally, the proposed method was applied to the experimental data. The analysis results showthat the proposed approach can achieve 100% fault diagnosis accuracy when only two component features are extracted, so it can effectively achieve fault diagnosis of rolling bearings.
Loading performances simulation analysis of roller needle bearing with partial loading
NIU Rongjun, HU Yusheng, WANG Yonggang
2019, 34(10): 2227-2236. doi: 10.13224/j.cnki.jasp.2019.10.016
Abstract:
Based on the characteristics of partial loading and support modes, afinite element analysis model of roller needle bearing fully considering the flexible structure influence of the cam and pin was established. Then, the influences of bearing load, radial clearance and installation misalignment angle on the mechanical property, stiffness and life of the bearing were analyzed systematically, and the correctness of the simulation results was verified by numerical and experimental methods. Results show that the radial load and installation misalignment angle have great influence on the contact performance and service life of bearings under partial loading conditions, while the clearance of bearings has little effect on the contact performance and service life of bearings; the increase of radial load and installation misalignment angle makes the bearing area smaller, and the original symmetrical contact pressure distribution pattern “hump” of the needle generatrix is gradually shifting to the deflection angle, resulting in the pressure distribution pattern of “one high one low”; the maximum contact pressure increases, and the bearing life decreases rapidly. However, under the conditions of limit load and installation misalignment angle, the service life index still meets the bearing design requirements.
Fault diagnosis method of inter-shaft bearing based on adaptive bistable stochastic resonance
TIAN Jing, ZHOU Jie, WANG Shugang
2019, 34(10): 2237-2245. doi: 10.13224/j.cnki.jasp.2019.10.017
Abstract:
In view of the problem that the aeroengine inter-shaft bearing fault signal is weak and the fault feature extraction is difficult, an adaptive bistable stochastic resonance (BSR) fault diagnosis method based on tolerance genetic algorithm (TAGA) of inter-shaft bearing was proposed. The tolerance theory was introduced into the traditional adaptive genetic algorithm, and a TAGA was established. The structural parameters a and b of the BSR system were optimized by the TAGA. The fault signal was processed by adaptive BSR system. In order to verify the effectiveness of the proposed method, an inter-shaft bearing fault simulation test rig was built, and the inner ring and outer ring fault simulation experiments of the inter-shaft bearing were carried out. The simulation signal and the experimental signal were processed separately by the method established. The results show that the proposed method can enhance the fault signal and the ability of fault feature frequency extraction. After adaptively optimizing the structural parameters, the error between the extracted fault feature frequency and the theoreticalvalue of the fault frequency is less than 0.1%.
Damage mechanics-finite element method for contact fatigue life prediction of ball bearings
ZHANG Jieyi, CHEN Guo, XIE Jiedong
2019, 34(10): 2246-2255. doi: 10.13224/j.cnki.jasp.2019.10.018
Abstract:
Based on linear elastic mechanics and continuous damage mechanics, the damage evolution equation of ball bearing contact fatigue was constructed.The material parameters in the damage evolution equation were obtained by fitting the GCr15 bearing steel torsional fatigue test data. The torsional fatigue life of GCr15 bearing steel was estimated by this equation, and the results were in agreement with the test data. The contact stress distribution of 6206 ball bearing was simulated by ABAQUS finite element analysis software and the maximum contact stress area of 6206 ball bearing was analyzed. The maximum stress contact area was simplified to a two-dimensional plane stress model according to the load and stress-strain state of the 6206 ball bearing. Based on this, the contact fatigue life of 6206 ball bearings was estimated. The 6206 ball bearing fatigue acceleration test was designed and carried out. Bearing contact fatigue spalling was initiated in the inner ring, which was consistent with the results of stress simulation analysis. The relative errors of test and predicted contact fatigue life of the three test bearings were 29.52%, 3.03% and 51.16% respectively, verifying the validity of the contact fatigue life prediction method. This research shows that using the damage mechanics to predict the contact fatigue life of ball bearings is a feasible and practical method in engineering.
Analysis and test verification of model rotor sudden nbalanceresponse
YU Lei, MA Huifang, WANG Weiguo
2019, 34(10): 2256-2263. doi: 10.13224/j.cnki.jasp.2019.10.019
Abstract:
Inorder to accurately obtain the transient load caused by fan blade out, contact modeling and transient analysis were carried out by explicit dynamic finite element simulation method. Multi-level calibration and verification test were performed, and these test results were compared with the analysis. The comparison results showed that the explicit dynamic finite element simulation method can provide a feasible simulation method for accurately simulating thedynamic characteristics of sudden unbalance process, and a set of model updating methods from parts, components to whole finite element model, from statics to dynamics were formed. According to the physical quantities such as main path load and sudden unbalanced load defined by the test priority, the selectionof test parameters for model updating was determined. With the calibration results of the model, the peak radial dynamic load can be accurately obtained by using the dynamic strain measurement data of the bearing cone, and the prediction error of peak dynamic load was within 10% compared with thetest observation. This method can be applied to indirect measurement of the impact load, so as to improve the accuracy and simplicity of the measurement.
Accelerated parametric model order reduction method
LIU Ying, LI Hongguang, LI Yue
2019, 34(10): 2264-2270. doi: 10.13224/j.cnki.jasp.2019.10.020
Abstract:
Given the relatively time-consuming offline data trainingphase of the parametric model order reduction (PMOR) method, an accelerated method was proposed. Based on the PMOR method by matrix interpolation, the combined approximation reanalysis technology was applied to accelerate the repeated model order reduction (MOR) procedure. The factorization matrices of the initial stiffness matrix were utilized to generate the basis vectors to reduce the system matrices, calculated the final modal shape vectors via reduced matrices and repeated the calculation procedure for the sampling points in parameter space to build the offline database. Then the moving coil of the electrical-dynamic shaker was used as an example. The regular and improved methods were also used to perform the simulation for the uniformly distributed sample points. The results show that the proposed method can significantly reduce the MOR times more than 80% and improve the efficiency of building offline parametric database with guaranty of the reduced models’ accuracy.
Linear active disturbance rejection control method for intake pressure control in aero-engine transient test
QIAN Qiumeng, DAN Zhihong, ZHANG Song
2019, 34(10): 2271-2279. doi: 10.13224/j.cnki.jasp.2019.10.021
Abstract:
When aero-engine received transient test in altitude test facility, the intake control system was abnormally affected and the quality of intake pressure control couldn’t be improved by conventional control methods, so an intake pressure control method based on linear active disturbance rejection was proposed. The high-intensity intake control system simulation platform was built through mechanism simulation and system identification, and the linear active disturbance rejection law was designed to estimate and compensate engine disturbance in real-time manner. An intake pressure control method with active rejection mechanism was formed. Meanwhile, considering the switching problem between manual and automatic control or between different control laws in actual use, an practical bumpless transfer method was designed. Simulation results compared with PID showed that the intake pressure can be quickly converged and stabilized, meanwhile, the maximum deviation was reduced from 7.69kPa to 0.9kPa. So this method achieves good control effect without engine information and can greatly improve intake pressure control quality in transient test.
Effects of misaligned impingement on atomization characteristics of impinging jet injector
LI Jianan, LEI Fanpei
2019, 34(10): 2280-2293. doi: 10.13224/j.cnki.jasp.2019.10.022
Abstract:
In order to investigate the effects of misaligned impingement on the atomization characteristics of impinging jet injector, a numerical scheme to simulate cold atomization process of hypergolic propellants was established. Also atomization process with different misaligned degrees was simulated. Incompressible Navier-Stokes equations were directly solved by employing tree-based adaptive refinement algorithm. Interfaces of different fluids were captured by piecewise linear volume-of-fluid (VOF) method. The results revealed that atomization field was deflected due to misaligned impingement. When the dimensionless misaligned degree E was 1/8, the deflection angle of the atomization filed was about 9.2°, so the machining deviation should be controlled below this value. The deflected angle increased with the misaligned degree. The angle obtained by theoretical analysis was smaller than that of numerical simulation. When aligned impingement occurred, mass flow rate flux peaks of fuel and oxide were close in space and unimodal distribution of the total mass flow rate flux appeared. When misaligned impingement occurred, for the reason that partial momentums of fuel and oxide jet didn’t participate in impingement, mass flow rate flux distribution of fuel and oxide interlaced and bimodal distribution of the total mass flow rate flux appeared. Mixture ratio distribution in space changed a lot. Droplet velocity distribution of aligned impingement downstream the impingement point was approximately axial symmetric while that of misaligned impingement was approximately central symmetric. Jet momentum loss caused by misaligned impingement led to poorer atomization performance. When dimensionless misaligned degree E was 1/8, Sauter mean diameter of monomethylhydrazine(MMH) increased about 4.8% and that of nitrogen tetroxide(NTO) increased about 5.8%.
Investigation on the first passage shock loss with bump control inside a supersonic compressor cascade
LIU Yongzhen, XU Qiangren, MA Yingqun
2019, 34(10): 2294-2304. doi: 10.13224/j.cnki.jasp.2019.10.023
Abstract:
In order to effectively reduce both losses induced by the first passage shock and resulted from boundary layer separation inside a supersonic compressor cascade at variable inlet Mach numbers, a type of method employing a new kind of 2-D bump structure with straight transition region on the suction side of the supersonic compressor cascade was presented to control the shock-boundary layer interaction. Numerical simulations and then detailed analyses to demonstrate the control mechanism of the 2-D bump on shocks and shock-boundary layer nteractions were conducted as well to investigate the influences of geometric dimensions and positions of the 2-D bump on control results. The investigations show that the compression wave system induced from concave windward surface of the 2-D bump effectively weakens the intensity of the first passage shock and that the expansion wave system produced by the transition region of the bump accelerates the flow in boundary layer, both of which suppress the local flow separation significantly and make the separation reattach in advance. While the first passage shock inside a supersonic cascade impinged on the straight section of the bump, optimal control effect was achieved at dimensionless height of the bump which retained 0.35 times of boundary layer thickness, and also at dimensionless length of windward and leeward side which remained 4 and 5 times of transition region respectively. Moreover, compared with the cascade without 2-D bump, the level for total pressure loss reduced by the bump reached 4.6% with the free stream Mach number 1.75, while the aerodynamic loss of the supersonic compressor cascade with bump was still better than that without bump when the inlet Mach number varied from 1.65 to 1.80.