Shenyang Aerospace Engine Research Institute

Shenyang, China

Shenyang Aerospace Engine Research Institute

Shenyang, China
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Wang Z.,Nanjing University of Aeronautics and Astronautics | Shen X.,Shenyang Aerospace Engine Research Institute | Hu J.,Nanjing University of Aeronautics and Astronautics
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2017

Three-dimensional CFD numerical simulation, engine stability calculation and bench test of engine inlet distortion are combined to predict and assess the influence of re-ingestion of the reverser flow on the aerodynamic stability of the high bypass ratio turbofan engine when the thrust reverser is deployed. By means of three-dimensional CFD numerical simulation, the distortion degree of the engine inlet flow field is acquired. On this basis, the aerodynamic stability of the engine is predicted by the stability calculation program, and the prediction results are verified by the engine bench test. The CFD calculation results show that, with the decrease of the relative flow Mach number, the possibility of re-ingestion of the reverser flow is increased, and the inlet flow field distortion of the outboard engine is the most serious when the relative flow Maher number decreases to 0.05. The results of stability calculation analysis and engine bench test in the inlet distortion situation show that, in the assessment of the target state, if the inlet distortion is only caused by the re-ingestion of the reverser flow, the engine will not be unstable. © 2017, Press of Chinese Journal of Aeronautics. All right reserved.


Zhao M.,Hefei University of Technology | Zhou T.,Hefei University of Technology | Ye T.,Hefei University of Technology | Zhu M.,Hefei University of Technology | Zhang H.,Shenyang Aerospace Engine Research Institute
International Journal of Hydrogen Energy | Year: 2017

Large eddy simulation (LES) has been performed to investigate transverse hydrogen jet mixing and combustion process in a scramjet combustor model with a compression ramp at inlet to generate shock train. Partially Stirred Reactor (PaSR) sub-grid combustion model with a skeleton of 19 reactions and 9 species hydrogen/air reaction mechanism was used. The numerical solver is implemented in an Open Source Field Operation and Manipulation (OpenFOAM) and validated against experimental data in terms of mean wall pressure. Effects of a shock train induced by the inlet compression ramp on the flame stabilization process are then studied. It can be observed that the interaction of the oblique shock and the jet mixing layer enhance the combustion and stabilize the flame. Symmetrical recirculation zone, which contributes to the flame anchoring of the supersonic transverse jet combustion, is observed in the near wall region of 10 < x/D < 20. The hydrogen fuel is transported from the center of jet plume to the near wall region on both sides of the central plane (z/D = 0) and thus intense combustion near the wall is observed due to the enhanced mixing and shock compression heating. Besides, the jet penetration in the reacting field is different from that in non-reacting case with the influence of the interaction between the reflected oblique shock and the jet shear layer on the windward side. © 2017 Hydrogen Energy Publications LLC.


Liang D.,The Aerospace Corporation | Gong Z.-Q.,The Aerospace Corporation | Chen C.-P.,The Aerospace Corporation | Gao S.,Shenyang Aerospace Engine Research Institute
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2017

By analyzing the transonic single-stage compressors NASA Stage 35, the results of numerical simulation and the experimental results were combined, proving the veracity of numerical simulation. The hole and slot bleeding were calculated by two ways, and the same results were got. At last, the results of hole bleeding and the slot were compared. Result showed that, the slot bleeding was better. The bleeding/cooling block of NUMECA software was easy to realize the bleeding, another way increased the difficulty and complexity of numerical simulation, but it agreed with the fact of bleeding on compressor. Before the bleeding, the efficiency improved, and the total pressure ratio declined little. At same time, stall margin was enhanced. © 2017, Editorial Department of Journal of Aerospace Power. All right reserved.


Hou P.,Shenyang Aerospace Engine Research Institute | Luo A.-R.,Shenyang Aerospace Engine Research Institute | Han F.-J.,Shenyang Aerospace Engine Research Institute
MATEC Web of Conferences | Year: 2017

High bypass ratio aero-engine was widely used on military and civil aviation domain, as the power of larger aircraft. Fan frame unit was the main bearing frame of high bypass ratio aero-engine, which composed of strut, HUB MID BOX and external bypass parts. Resin/composite was used on external bypass parts(acoustic liner, containment ring, fan outlet guide vane and fan case skin fillets), which not only reduced the weight and manufacturing cost, but also improved the noise absorption, containment and anti-fatigue ability of engine. The design of composite was becoming a key technique for high bypass ratio aero-engine. In special test of the core engine, nitrogen cooling system was designed to cool the cavity of spool. The nitrogen pipeline passed through the inner cavity of fan frame, then inserted into NO. 3 bearing seal, so nitrogen gas was sent into the cavity of core engine spool. On high bypass ratio aero-engine, the external bypass and fan frame inner cavity were the design platform for advanced technique, such as composite and pipeline system, and also provided guarantee for reliable operation of engine. © The Authors, published by EDP Sciences, 2017.


Li Z.-Y.,Beihang University | Wang J.-J.,Beihang University | Qiu M.-X.,Shenyang Aerospace Engine Research Institute
Hangkong Dongli Xuebao/Journal of Aerospace Power | Year: 2016

For analysis of dynamic characteristics of aero-engine pipe system, a fluid-structure coupling dynamic model using the user-defined three-dimensional (3D) pipe element was proposed based on the finite element method. The flexural fluid-structure coupling, axial and torsional dynamic behavior of the pipe was considered in the user-defined pipe element. The support was modeled using the nonlinear spring element. The user-defined pipe element was verified through comparisons with the measured data and analytical results. The natural frequencies and responses of a pipe system were calculated. The results show that the natural frequencies and the critical velocity decrease as the fluid pressure increases. And the effects of the nonlinear stiffness coefficient and the excitation amplitude on the pipe system under harmonic base excitation can be obtained. © 2016, Editorial Department of Journal of Aerospace Power. All right reserved.


Cui J.G.,Shenyang Aerospace University | Zhang L.,Shenyang Aerospace University | Wang G.H.,Shenyang Aerospace Engine Research Institute | Cui B.,Shenyang Aerospace Engine Research Institute | Jiang L.Y.,Shenyang Aerospace University
Applied Mechanics and Materials | Year: 2014

Since the fault of marine gas turbine is difficult to predict accurately, making the rolling bearing as the specific object, a fault prediction model of the marine gas turbine based on Neural Network and Markov method is built through the data analysis, preprocessing and feature extraction for the rolling bearing history test data. First, it uses the neural network method to realize the health state recognition of the marine gas turbine. Then, the fault of the marine gas turbine is predicted by taking advantage of the fault prediction which is based on the Markov model. The results show that the efficiency of fault prediction for the marine gas turbine can be realized better through the fault prediction model constructed in view of the Neural Network and Markov. And it also has a significant practical value in project item. © (2014) Trans Tech Publications, Switzerland.


Huang X.,Nanjing University of Aeronautics and Astronautics | Wang Y.,Shenyang Aerospace Engine Research Institute | Sheng L.,Nanjing University of Aeronautics and Astronautics
Proceedings of the American Control Conference | Year: 2015

Propeller synchrophasing control is an active noise control technology with high feasibility and significant effect among various kinds of passive and active methods. A simple and effective synchrophasing control strategy was proposed based on the relationship analysis of phase and angular displacement. Digital simulations and experiments of synchrophasing platform which adopts two propellers driven by servo motors verified that the control strategy can reduce the phase vibration because of external disturbance on propellers. Two synchrophasing control methods, including speed command correction and integrated speed/power command correction, are introduced to solve the synchrophasing control on the existing integrated speed/command control system. Simulation results based on a turboprop engine component level model show that the latter has the merits of rapid response swiftness, high precision and effective suppression of limit circle caused by actuator deadband. © 2015 American Automatic Control Council.


Huang X.,Nanjing University of Aeronautics and Astronautics | Sheng L.,Nanjing University of Aeronautics and Astronautics | Wang Y.,Shenyang Aerospace Engine Research Institute
Journal of Engineering for Gas Turbines and Power | Year: 2014

Propeller synchrophasing is an effective way of reducing interior noise and vibration of turboprop-driven aircraft. However, synchrophasing has achieved limited success in practice for the reason that the predetermined phase angles are not acoustically optimized for maximum noise reduction during all flight conditions. An investigation has been conducted out which includes two folds: first, the noise vector based on laboratory experimental data has been modeled and second, optimal phase to acquire minimum noise is obtained via optimization search. An improved identification method of vector noise model which can be less dependent to noise phase message is presented. Compared with traditional methods, this method can greatly reduce the real-time requirement between phase optimization model and control model or sound acquiring model, so it can eliminate the influence which communication delay brings on identification precision. A synchrophasing experimental platform is established to verify the vector noise modeling. It adopts two propellers-driven servo motors to simulate the interior noise environment of the aircraft. The influence of the date sampling condition on identification is also researched. Ant colony optimization with two improvements is applied to phase optimization of four propellers. Simulation results show that the improved algorithm requires much less calculation. © 2014 by ASME.


Ma C.-W.,Shenyang Aerospace Engine Research Institute
Applied Mechanics and Materials | Year: 2010

Thermal paints, as a kind of temperature sensor, provided a non-intrusive method for surface temperature measurement. Based on chromaticity theory, the system described in this paper realized thermal paints temperature intelligent interpretation with digital image processing and database technology. The system overcome the effects of subjective interpretation, environment light and human color discrimination ability and made the analysis more accurate and consistent than manual interpretation. The digital image acquisition system was described in detail. Cubic spline interpolation algorithm was adopted to process the data in the L*a*b* color space. The system had been applied to measure the surface temperature of aero-engine combustor. The results showed that the system can greatly improve the accuracy of temperature-recognition. © (2010) Trans Tech Publications.


Wang J.,Anhui University of Science and Technology | Feng Z.,Anhui University of Science and Technology | Zhang Q.,Anhui University of Science and Technology | Wu X.,Shenyang Aerospace Engine Research Institute | Ma S.,Shenyang Aerospace Engine Research Institute
International Journal of Heat and Mass Transfer | Year: 2012

An experimental investigation on overall heat transfer performance of a rectangular channel, in which one wall has periodically placed oblique ribs to enhance heat exchange and cylindrical film holes to bleed cooling air, has been carried out in a hot wind tunnel at different mainstream temperatures, hot mainstream Reynolds numbers, coolant Reynolds numbers and blowing ratios. To describe the cooling effect of combined external coolant film with the internal heat convection enhanced by the ribs, the overall cooling effectiveness at the surface exposed in the mainstream with high temperature was calculated by the surface temperatures measured with an infrared thermal imaging system. The total mass flow rate of cooling air through the coolant channel was regulated by a digital mass flow rate controller, and the blowing ratio passing through the total film holes was calculated based on the measurements of another digital-type mass flow meter. The detailed distributions of overall cooling effectiveness show distinctive peaks in heat transfer levels near the film holes, remarkable inner convective heat transfer effect over entire channel surface, and visible conductive heat transfer effect through the channel wall; but only when the coolant Reynolds number is large enough, the oblique rib effect can be detected from the overall cooling effectiveness; and the oblique bleeding hole effect shows the more obvious trend with increasing blowing ratios. Based on the experimental data, the overall cooling effectiveness is correlated as the functions of Re m (Reynolds number of hot mainstream) and Re c (Reynolds number of internal coolant flow at entrance) for the parametric conditions examined. © 2012 Elsevier Ltd. All rights reserved.

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