期刊文献+
共找到26篇文章
< 1 2 >
每页显示 20 50 100
Academy of Aerospace Solid Propulsion Technology
1
作者 Zhang Lizhong Academy of Aerospace Solid Propulsion Technology 《Aerospace China》 2011年第3期17-18,共2页
Academy of Aerospace Solid Propulsion Technology (AASPT) is a professional research institution which is responsible for the design, development, manufacture, conducting various tests
关键词 Academy of aerospace Solid propulsion Technology
下载PDF
航空发动机高速滚珠轴承振动特性研究
2
作者 唐云冰 章璟璇 +1 位作者 施玲玲 谢小虎 《风机技术》 2023年第3期59-65,共7页
Ball bearing is widely used as rotor supporting.It is a non-negligible source of vibration in aero-engines.The vibration characteristics of the highspeed ball bearing are studied in this paper.Bearing kinematics theor... Ball bearing is widely used as rotor supporting.It is a non-negligible source of vibration in aero-engines.The vibration characteristics of the highspeed ball bearing are studied in this paper.Bearing kinematics theory is applied to discuss the basic characteristics of ball bearings.The vibration factors caused by ball bearings are analyzed,and then the vibration model of ball bearings is set up.The effect of the unbalance,the ball passage vibration,the radial clearance and the surface waviness are considered.It is found that the ball passage vibration is excited by the contact force between the balls and the races.Increasing the numbers of ball can reduce the vibration amplitude.The surface waviness which is caused due to the geometric imperfection of ball bearings is considered as one of the important vibration sources of bearing systems. 展开更多
关键词 aerospace propulsion System Ball Bearing Ball PassageVibration SurfaceWaviness
下载PDF
Aerodynamic Design and Analysis of a Low-reaction Axial Compressor Stage 被引量:13
3
作者 羌晓青 王松涛 +1 位作者 冯国泰 王仲奇 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第1期1-7,共7页
There is introduced a new low-reaction, highly-loaded axial compressor design concept which is coupled with boundary layer suction method. The characteristic features of the concept are made clear through its comparis... There is introduced a new low-reaction, highly-loaded axial compressor design concept which is coupled with boundary layer suction method. The characteristic features of the concept are made clear through its comparison with the MIT boundary layer suction compressor. Also are pointed out the potential applications of this concept as well as its key technological problems. Based on this concept, a single-stage, low-reaction and low-speed axial compressor is constructed in association with analysis and computation of boundary layer suction on vanes with the aid of a three-dimensional numerical approach. The results attest to the effectiveness of this way to control separation in blade cascades by the boundary layer suction and the feasibility of this proposed design concept. 展开更多
关键词 aerospace propulsion system low-reaction axial compressor boundary layer suction energy loss
下载PDF
Foreign Object Damage to Fan Rotor Blades of Aeroengine Part II: Numerical Simulation of Bird Impact 被引量:8
4
作者 关玉璞 赵振华 +1 位作者 陈伟 高德平 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第4期328-334,共7页
Bird impact is one of the most dangerous threats to flight safety. The consequences of bird impact can be severe and, therefore, the aircraft components have to be certified for a proven level of bird impact resistanc... Bird impact is one of the most dangerous threats to flight safety. The consequences of bird impact can be severe and, therefore, the aircraft components have to be certified for a proven level of bird impact resistance before being put into service. The fan rotor blades of aeroengine are the components being easily impacted by birds. It is necessary to ensure that the fan rotor blades should have adequate resistance against the bird impact, to reduce the flying accidents caused by bird impacts. Using the contacting-impacting algorithm, the numerical simulation is carded out to simulate bird impact. A three-blade computational model is set up for the fan rotor blade having shrouds. The transient response curves of the points corresponding to measured points in experiments, displacements and equivalent stresses on the blades are obtained during the simulation. From the comparison of the transient response curves obtained from numerical simulation with that obtained from experiments, it can be found that the variations in measured points and the corresponding points of simulation are basically the same. The deforming process, the maximum displacements and the maximum equivalent stresses on blades are analyzed. The numerical simulation verifies and complements the experiment results. 展开更多
关键词 aerospace propulsion system bird impact numerical simulation fan rotor blade transient response
下载PDF
A Ventral Diverterless High Offset S-shaped Inlet at Transonic Speeds 被引量:5
5
作者 谢文忠 郭荣伟 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第3期207-214,共8页
An investigation on the ventral diverterless high offset S-shaped inlet is carried out at Mach numbers from 0.600 to 1.534, angles of attack from -4° to 9.4°, and yaw angles from 0° to 8°. Results ... An investigation on the ventral diverterless high offset S-shaped inlet is carried out at Mach numbers from 0.600 to 1.534, angles of attack from -4° to 9.4°, and yaw angles from 0° to 8°. Results indicate: (1) a large region of low total pressure exists at the lower part of the inlet exit caused by the counter-rotating vortices in the S-shaped duct; (2) the performances of the inlet at Mach number 1.000 reach almost the highest, so the propulsion system could work efficiently in terms of aerodynamics; (3) the total pressure recovery increases slowly at first and then remains unvaried as the Mach number rises from 0.6 to 1.0, however, it does in an opposite manner in the conventional diverter-equipped S-shaped inlet; (4) the performances of the inlet are generally insensitive to angles of attack from -4° to 9.4° and yaw angles from 0° to 8° at Mach number 0.850, and angles of attack from -2° to 6° and yaw angles from 0° to 5° at Mach number 1.534. 展开更多
关键词 aerospace propulsion system diverterless inlet high offset transonic inlet S-shaped inlet experimental investigation
下载PDF
Discharge Coefficient of 3-in-1 Hole with Various Inclination Angle and Hole Pitch 被引量:4
6
作者 李广超 朱惠人 樊慧明 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第5期385-392,共8页
Discharge coefficients of 3-in-1 hole of three inclination angles and three spacing between holes are presented which described the discharge behavior of a row of holes. The inlet and outlet of the 3-in-1 hole both ha... Discharge coefficients of 3-in-1 hole of three inclination angles and three spacing between holes are presented which described the discharge behavior of a row of holes. The inlet and outlet of the 3-in-1 hole both have a 15° lateral expansion. The flow conditions considered are mainstream turbulence intensities and density ratios of secondary flow to mainstream. The momentum flux ratios varied in the range from 1 to 4. The comparison is made of the discharge coefficients of three shaped holes to find an optimal hole with low flow loss. The results show that the discharge coefficients of 3-in- 1 hole are highest in three shaped holes and therefore this article is focused on the measurements of discharge coefficients of 3-in-1 hole for various geometries and aerodynamic parameters. The measured results of 3-in-1 hole indicate that turbulence intensities, density ratios and momentum flux ratios have weak influence on discharge coefficients for inclination angle of 20°. The high turbulence intensity yields the small discharge coefficients for inclination angle of 45° and 90°. The increased both momentum flux ratios and density ratios lead to the increased discharge coefficients for inclination angle of 45° and 90°. The increased inclination angle causes the rapidly increased discharge coefficients. There is a weak dependence of discharge coefficients on hole pitches. 展开更多
关键词 aerospace propulsion system gas turbine film cooling hole discharge coefficient
下载PDF
Foreign Object Damage to Fan Rotor Blades of Aeroengine Part I:Experimental Study of Bird Impact 被引量:14
7
作者 关玉璞 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2007年第5期408-414,共7页
The conditions of experiment for bird impact to blades have been improved. The experiment of bird impact to the fan rotor blades of an aeroengine is carried out. Through analyzing the transient state response of blade... The conditions of experiment for bird impact to blades have been improved. The experiment of bird impact to the fan rotor blades of an aeroengine is carried out. Through analyzing the transient state response of blades impacted by bird and the change of blade profile before and after the impact, the anti-bird impact performance of blades in the first fan rotor is verified. The basis of anti-foreign object damage design for the fan rotor blades of an aeroengine is provided. 展开更多
关键词 aerospace propulsion system bird impact experiment fan rotor blade transient response
下载PDF
Influences of Hole Shape on Film Cooling Characteristics with CO_2 Injection 被引量:1
8
作者 李广超 朱惠人 樊慧明 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第5期393-401,共9页
This article presents the data about heat transfer coefficient ratios, film cooling effectiveness and heat loads for the injection through cylindrical holes, 3-in-1 holes and fanned holes in order to characterize the ... This article presents the data about heat transfer coefficient ratios, film cooling effectiveness and heat loads for the injection through cylindrical holes, 3-in-1 holes and fanned holes in order to characterize the film cooling performance downstream of a row of holes with 45° inclination and 3 hole spacing apart. The trip wire is placed upstream at a distance of 10 times diameter of the cooling hole from the hole center to keep mainstream fully turbulent. Both inlet and outlet of 3-in-1 holes have a 15° lateral expansion. The outlet of fanned holes has a lateral expansion. CO2 is applied for secondary injection to obtain a density ratio of 1.5. Momentum flux ratio varies from 1 to 4. The results indicate that the increased momentum flux ratio significantly increases heat transfer coefficient and slightly improve film cooling effectiveness for the injection through cylindrical holes. A weak dependence of heat transfer coefficient and film cooling effectiveness, respectively, on momentum flux ratio has been identified for the injection through 3-in-1 holes. The in- crease of the momentum flux ratio decreases heat transfer coefficient and significantly increases film cooling effectiveness for the injection through fanned holes. In terms of the film cooling performance, the fanned holes are the best while the cylindrical holes are the worst among the three hole shapes under study. 展开更多
关键词 aerospace propulsion system gas turbine film cooling effectiveness heat transfer coefficient
下载PDF
Experimental Investigation of a Fixed-geometry Two-dimensional Mixed-compression Supersonic Inlet with Sweep-forward High- light and Bleed Slot in an Inverted "X"-type Layout 被引量:10
9
作者 Wan Dawei Guo Rongwei 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2007年第4期304-312,共9页
A fixed-geometry two-dimensional mixed-compression supersonic inlet with sweep-forward high-light and bleed slot in an inverted "X"-form layout was tested in a wind tunnel. Results indicate: (1) with increases of... A fixed-geometry two-dimensional mixed-compression supersonic inlet with sweep-forward high-light and bleed slot in an inverted "X"-form layout was tested in a wind tunnel. Results indicate: (1) with increases of the free stream Mach number, the total pressure recovery decreases, while the mass flow ratio increases to the maximum at the design point and then decreases; (2) when the angle of attack, a, is less than 6°, the total pressure recovery of both side inlets tends to decrease, but, on the lee side inlet, its values are higher than those on the windward side inlet, and the mass flow ratio on lee side inlet increases first and then falls, while on the windward side it keeps declining slowly with the sum of mass flow on both sides remaining almost constant; (3) with the attack angle, a, rising from 6° to 9°, both total pressure recovery and mass flow ratio on the lee side inlet fall quickly, but on the windward side inlet can be observed decreases in the total pressure recovery and increases in the mass flow ratio; (4) by comparing the velocity and back pressure characterristics of the inlet with a bleed slot to those of the inlet without, it stands to reason that the existence of a bleed slot has not only widened the steady working range of inlet, but also made an enormous improvement in its performance at high Mach numbers. Besides, this paper also presents an example to show how this type of inlet is designed. 展开更多
关键词 aerospace propulsion system supersonic inlet two-dimensional mixed-compression experimental investigation bleed slot "X"-type sweep-forward high-light
下载PDF
The Application of Support Vector Machines to Gas Turbine Performance Diagnosis 被引量:9
10
作者 郝英 孙健国 +1 位作者 杨国庆 白杰 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2005年第1期15-19,共5页
SVMs(support vector machines) is a new artificial intelligence methodology derived from Vapnik's statistical learning theory, which has better generalization than artificial neural network. A Csupport vector classi... SVMs(support vector machines) is a new artificial intelligence methodology derived from Vapnik's statistical learning theory, which has better generalization than artificial neural network. A Csupport vector classifiers Based Fault Diagnostic Model (CBFDM) which gives the 3 most possible fault causes is constructed in this paper. Five fold cross validation is chosen as the method of model selection for CBFDM. The simulated data are generated from PW4000-94 engine influence coefficient matrix at cruise, and the results show that the diagnostic accuracy of CBFDM is over 93 % even when the standard deviation of noise is 3 times larger than the normal. This model can also be used for other diagnostic problems. 展开更多
关键词 aerospace propulsion system performance diagnosis support vector machines model selection
下载PDF
Linear-in-Parameter Models Based on Parsimonious Genetic Programming Algorithm and Its Application to Aero-Engine Start Modeling 被引量:3
11
作者 李应红 尉询楷 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2006年第4期295-303,共9页
A novel Parsimonious Genetic Programming (PGP) algorithm together with a novel aero-engine optimum data-driven dynamic start process model based on PGP is proposed. In application of this method, first, the traditio... A novel Parsimonious Genetic Programming (PGP) algorithm together with a novel aero-engine optimum data-driven dynamic start process model based on PGP is proposed. In application of this method, first, the traditional Genetic Programming(GP) is used to generate the nonlinear input-output models that are represented in a binary tree structure; then, the Orthogonal Least Squares algorithm (OLS) is used to estimate the contribution of the branches of the tree (refer to basic function term that cannot be decomposed anymore according to special rule) to the accuracy of the model, which contributes to eliminate complex redundant subtrees and enhance GP's convergence speed; and finally, a simple, reliable and exact linear-in-parameter nonlinear model via GP evolution is obtained. The real aero-engine start process test data simulation and the comparisons with Support Vector Machines (SVM) validate that the proposed method can generate more applicable, interpretable models and achieve comparable, even superior results to SVM. 展开更多
关键词 aerospace propulsion system linear-in-parameter nonlinear model Parsimonious Genetic Programming (PGP) aero-engine dynamic start model
下载PDF
Numerical Simulation of Particle/Matrix Interface Failure in Composite Propellant 被引量:6
12
作者 常武军 鞠玉涛 +2 位作者 韩波 胡少青 王政时 《Defence Technology(防务技术)》 SCIE EI CAS 2012年第3期146-153,共8页
Interface debonding between particle and matrix in composite propellant influences its macroscopic mechanical properties greatly. For this, the laws of interface cohesive damage and failure were analyzed. Then, its mi... Interface debonding between particle and matrix in composite propellant influences its macroscopic mechanical properties greatly. For this, the laws of interface cohesive damage and failure were analyzed. Then, its microscopic computational model was established. The interface mechanical response was modeled by the bilinear cohesive zone model. The effects of interface properties and particle sizes on the macroscopic mechanical behavior were investigated. Numerical simulation of debonding damage evolution of composite propellant under finite deformation was carried out. The debonding damage nucleation, propagation mechanism and non-uniform distribution of microscopic stress-strain fields were discussed. The results show that the finite element simulation method based on microstructure model can effectively predict the trend of macroscopic mechanical behavior and particle/matrix debonding evolution process. It can be used for damage simulation and failure assessment of composite propellants. 展开更多
关键词 propulsion system of aviation and aerospace interface debonding cohesive zone model composite propellant cohesive element damage evolution
下载PDF
Study on Instable Combustion of Solid Rocket Motor with Finocyl Grain 被引量:4
13
作者 胡大宁 何国强 +1 位作者 刘佩进 王占利 《Defence Technology(防务技术)》 SCIE EI CAS 2011年第1期24-28,共5页
The instable combustion or oscillation combustion which occurs in three high capacity solid rocket motors using high energy composite propellant with finocyl grain is studied. The reasons of the acoustic combustion in... The instable combustion or oscillation combustion which occurs in three high capacity solid rocket motors using high energy composite propellant with finocyl grain is studied. The reasons of the acoustic combustion instability are also discussed. Three engineering methods that can eliminate combustion instability are proposed and discussed. The study shows that the combustion instability mainly depends on the propellant grain shape and nozzle structure. Some measures to reduce the acoustic energy and mass generation rate of combustion gas can be adopted. The test results indicate that the modified rocket motors can significantly eliminate the instable combustion and improve the motor internal ballistic performance. 展开更多
关键词 propulsion system of aviation & aerospace solid rocket motor finocyl grain combustion instability
下载PDF
Experimental Research on Dynamic Erosion of EPDM Insulation Subjected to Particle-Laden Flow 被引量:2
14
作者 徐义华 胡春波 +1 位作者 张胜敏 陈剑 《Defence Technology(防务技术)》 SCIE EI CAS 2010年第4期225-233,共9页
The instantaneous degradation of erosion surface of ethylene propylene diene monomer(EPDM)insulation subjected to the particle-laden flow in two operating conditions was measured by using a real-time X-ray radiography... The instantaneous degradation of erosion surface of ethylene propylene diene monomer(EPDM)insulation subjected to the particle-laden flow in two operating conditions was measured by using a real-time X-ray radiography system.The images of its erosion state and dynamic ablation rate were obtained.And the charring-layer was analyzed by using SEM and energy spectrum.The experimental results indicate that the erosion rate of EPDM insulation layer impacted by low speed and low concentration particle flow is relatively small in the 1st second since the motor starting,but increases rapidly in 1 to 2.5 s,while the erosion rate of EPDM insulation layer impacted by high speed and high concentration particle flow increases rapidly in the 1st second;the ablation rate at the section eroded intensively by particle flow increases at first,then decreases,and goes to stabilization after 4.5 s;the higher speed and concentration particle flow are,the deeper particles get into charring layer,which lead to more thermal increment and thinner charring layer. 展开更多
关键词 propulsion system of aviation & aerospace particle-laden flow EPDM dynamic ablation charring layer
下载PDF
Experimental Investigation on Ablation Characteristic of EPDM Insulator in Different Gas Environments 被引量:2
15
作者 王书贤 何国强 +1 位作者 李江 刘佩进 《Defence Technology(防务技术)》 SCIE EI CAS 2010年第2期109-113,共5页
Some ablation experiments of Ethylene-Propylene-Diene Monomer(EPDM)insulator were carried out in quasi-static low temperature gas environment,gas-phase environment,two-phase environment with Al2O3 grain and high conce... Some ablation experiments of Ethylene-Propylene-Diene Monomer(EPDM)insulator were carried out in quasi-static low temperature gas environment,gas-phase environment,two-phase environment with Al2O3 grain and high concentration Al2O3 grain gas environments.Their charring ablation rate,thickness,surface morphology and main ingredient of the charring layer were analyzed.The experiment results show that the main influent factors for the charring ablation rate are the gas temperature,grain concentration and state of grain impact;the main influent factors for the charring layer thickness are the gas velocity and environment pressure;and the process of SiO2 migrating in the charring layer occur commonly in different gas environments.They provide a foundation for the ablation mechanism research and modeling of EPDM insulator. 展开更多
关键词 propulsion system of aviation and aerospace EPDM insulator experiment environment charring ablation rate charring layer thickness surface morphology INGREDIENT
下载PDF
Theoretical Analysis on Thermal Choking in Expanding RBCC Duct 被引量:1
16
作者 吴亚可 何国强 刘佩进 《Defence Technology(防务技术)》 SCIE EI CAS 2010年第4期234-240,共7页
A one-dimensional theoretical model was adopted in this paper to describe and analyze the flow in an expanding RBCC(rocket based combined cycle)duct.It can be concluded that the expanding angle,heating amount and dist... A one-dimensional theoretical model was adopted in this paper to describe and analyze the flow in an expanding RBCC(rocket based combined cycle)duct.It can be concluded that the expanding angle,heating amount and distribution of heating play crucial roles on the thermal choking.They mainly influence the acceleration of flow,the position of choking throat and the total pressure loss.In order to fulfill the transition of subsonic flow to supersonic flow in the expanding RBCC duct,the heating amount has to change from a bigger value to a smaller one along the duct.When the thermal choking occurs in the RBCC duct,the moderate expanding angle,proper heating amount and distribution of heating are necessary for the best performance of RBCC combustor.Adopting the RBCC duct with smaller expanding angles anterior and bigger expanding angles posterior has positive effects on the thermal choking and flexibility of selecting heating method,and can restrain the negative effect of the combustion on the inlet also. 展开更多
关键词 propulsion system of aviation & aerospace RBCC expanding duct one-dimensional analysis thermal choking
下载PDF
Cold Flow Experiments and Acoustic Investigation on Pressure Oscillation Induced by Flow Instability
17
作者 陈晓龙 何国强 刘佩进 《Defence Technology(防务技术)》 SCIE EI CAS 2010年第2期85-90,共6页
Pressure oscillation in solid rocket motor is believed to be the results of the interaction between the flow instability and the acoustics of combustion chamber.Several reasonable and necessary hypothesizes are given ... Pressure oscillation in solid rocket motor is believed to be the results of the interaction between the flow instability and the acoustics of combustion chamber.Several reasonable and necessary hypothesizes are given to establish an equation to describe this coupling.A cold flow motor called CVS60D(corner vortex shedding 60°)was designed to study the flow-acoustic coupling based on theoretical analysis.Experimental investigations were carried out to determine the acoustics of CVS60D.Corner vortex shedding is generated at the backward facing step which is designed similar to the geometry of the motor with finocyl propellant after the burnout of its fins.A pintle was used to modify the velocity in the duct to change the frequency of vortex shedding.It is found that large amplitude pressure oscillation occurs when the pintle moves to a range of specific position,which indicates that the frequency of vortex shedding is close to one order of acoustic modes of combustion chamber.The amplitude of pressure oscillation changes as the pintle moves. 展开更多
关键词 propulsion system of aviation & aerospace cold flow experiment ACOUSTICS pressure oscillation flow instability
下载PDF
Identification of Backflow Vortex Instability in Rocket Engine Inducers
18
作者 Luca d’Agostino 《风机技术》 2024年第5期7-18,共12页
Bayesian estimation is applied to the analysis of backflow vortex instabilities in typical three-and four bladed liquid propellant rocket(LPR)engine inducers.The flow in the impeller eye is modeled as a set of equally... Bayesian estimation is applied to the analysis of backflow vortex instabilities in typical three-and four bladed liquid propellant rocket(LPR)engine inducers.The flow in the impeller eye is modeled as a set of equally intense and evenly spaced 2D axial vortices,located at the same radial distance from the axis and rotating at a fraction of the impeller speed.The circle theorem and the Bernoulli’s equation are used to predict the flow pressure in terms of the vortex number,intensity,rotational speed,and radial position.The theoretical spectra so obtained are frequency broadened to mimic the dispersion of the experimental data and parametrically fitted to the measured pressure spectra by maximum likelihood estimation with equal and independent Gaussian errors.The method is applied to three inducers,tested in water at room temperature and different loads and cavitation conditions.It successfully characterizes backflow instabilities using the signals of a single pressure transducer flush-mounted on the casing of the impeller eye,effectively by-passing the aliasing and data acquisition/reduction complexities of traditional multiple-sensor cross correlation methods.The identification returns the estimates of the model parameters and their standard errors,providing the information necessary for assessing the accuracy and statistical significance of the results.The flowrate is found to be the major factor affecting the backflow vortex instability,which,on the other hand,is rather insensitive to the occurrence of cavitation.The results are consistent with the data reported in the literature,as well as with those generated by the auxiliary models specifically developed for initializing the maximum likelihood searches and supporting the identification procedure. 展开更多
关键词 aerospace propulsion Liquid Propellant Rockets LPR Feed Turbopumps Turbopump Flow Instabilities BackflowVortex Instability Bayesian Parametric Identification
下载PDF
Aircraft Engine Sensor Fault Diagnostics Based on Estimation of Engine's Health Degradation 被引量:9
19
作者 薛薇 郭迎清 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2009年第1期18-21,共4页
A duty in development of an on-line fault detection algorithm is to make it associate with estimation of engine s health degradation. For this purpose,an on-line diagnostic algorithm is put forward. Using a tracking f... A duty in development of an on-line fault detection algorithm is to make it associate with estimation of engine s health degradation. For this purpose,an on-line diagnostic algorithm is put forward. Using a tracking filter to estimate the engine s health condition over its lifetime,can be reconstructed an onboard model,which is then made to match a real aircraft gas turbine engine. Finally,a bank of Kalman filters is applied in fault detection and isola-tion (FDI) of sensors for the engine. Through the bank... 展开更多
关键词 aerospace propulsion system Kalman filter health degradation sensor fault diagnostics
原文传递
Redesign of an 11 cm-diameter Micro Diffuser
20
作者 陈杰 黄国平 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2010年第3期298-305,共8页
In order to improve the performances of an 11 cm-diameter turbine engine,this article suggests to substitute a new-style micro diffuser redesigned based on a new concept for the traditional diffuser having poor perfor... In order to improve the performances of an 11 cm-diameter turbine engine,this article suggests to substitute a new-style micro diffuser redesigned based on a new concept for the traditional diffuser having poor performances. The new diffuser comprises integral blades and splitters,which are taken for a series of ducts in designing. This article investigates the effects of the cross-section area distribution along the flow path on the redesigned diffuser's performances. Having furnished with the new diffuser in place of the original vaned one,the 11 cm-diameter prototype engine is tested on the rig for its performances. CFD and experiments have shown that the improved diffuser with the unchanged original size has gained excellent performance parameters of pressure coefficient over 0.65 and total pressure recovery coefficient over 0.9. Equipped with the redesigned micro diffuser,the engine increases the thrust by 11% and decreases the specific fuel consumption by 9%. 展开更多
关键词 aerospace propulsion new-style micro diffuser numerical analysis micro turbine engine centrifugal compressor
原文传递
上一页 1 2 下一页 到第
使用帮助 返回顶部