基于Flow Simulation的某发动机涡轮压气机流场与效率分析

涡轮机内部流场对涡轮增压器的性能和效率有着重要影响,采用SolidWorks Flow Simulation模块对某发动机涡轮压气机侧流场和压气效率分析。在六种不同空气体积流量工况下,体积流量为0.29时,压气机效率最高,达到80%左右。模型的建模和流体分析均在SolidWorks环境下,分析效率高,为涡轮增压器设计和优化提供了支撑。

某舰用燃机高压涡轮压气机转子传递矩阵建模

利用有限元法推导某舰用燃气轮机高压涡轮压气机转子的传递矩阵,并建立转子的多体系统传递矩阵模型。通过算例证明,该方法计算准确,为用有限元法和多体系统传递矩阵法求解燃气轮机转子学问题提供了新思路。

低雷诺数和低膨胀比涡轮—压气机组件的设计技术研究

介绍了一种用于军用飞机吊舱内电子设备冷却的逆升压回冷式冲压空气循环的制冷系统 ,阐述了该系统的特点和技术关键 ,重点介绍了低膨胀比、低雷诺数涡轮—压气机组件的设计难点及所采取的技术措施。计算和试验结果表明 。

稳态联合畸变下多级轴流压气机的气动稳定性分析

发展了一种分析稳态压力 -温度联合畸变下多级轴流压气机气动稳定性的逐级平行压缩系统模型。导出了基于双对角线格式的数值预测方法。对三级实验压气机进行数值分析后 ,给出了压气机进口稳态压力、压力 -温度联合畸变与压气机稳定裕度损失之间的定量关系 ;并给出了压气机失稳首发级的识别方法。

高温气冷堆能量转换气轮机基本特性的研究

高温气冷堆气轮机循环被认为是将来核能发电领域中最有潜力的方案之一。本文试图将高温堆气轮机循环中各种循环方案总结归纳为几种典型的循环，再将这几种典型循环从理论上抽象为氦气、氮气和空气布雷登循环并进行优化。然后针对这三种循环中的气轮机从热力学和气体动力学角度进行广泛的研究，得出氦气、氮气和空气气轮机的基本特性。

叶片前缘不同后掠角对离心压气机气动性能的影响

采用全三维气动设计技术,设计了4种具有掠角叶片和带翼型叶片扩压器的涡轮增压跨音速离心压气机,并采用数值模拟手段研究了叶片前缘不同后掠角对压气机内部工质流动的影响。研究结果表明:主叶片前缘不同后掠角会使压气机堵塞流量(堵塞工况下的工质流量)增加,提高压气机流通能力,同时,可以有效改善通道内低能流团的分布;但由于主叶片轴向弦长缩短,会造成喘振裕度的减少,以及主叶片前缘脱体激波角增大和槽道激波的增强;对截面二次流分析结果表明:叶片前缘的后掠角对二次流的影响主要表现在叶轮进口附近,对出口影响不大。对比不同前缘后掠角压气机内部流动情况发现,掠角越小,叶片叶顶负荷越小,叶片表面压差也越小,流动越稳定;掠角越大,虽然叶轮通道上游产生的激波越强烈,但是可以明显改善通道下游气流流动情况。

BCY-10典型冬季故障分析

BCY-10是安装在-86大型宽体客机上的辅助动力装置,位于机身的尾舱,由燃气涡轮发动机、减速器、联动压气机和发电机等组成.辅助动力装置舱由防火墙与机身隔开.由于乌鲁木齐冬季气候条件比较恶劣,因此对BCY-10的起动准备工作及其过程提出了一些具体要求:

姜鹏明破译“华夏”

走近一个成功者,便是走近一个谜。姜鹏明使我着迷。时代不该沉默。生活从来公平。北京华夏环保产业有限公司在科海的浪潮中,历经风雨,到现在已发展到在新、马、泰、美、加、墨、韩、港均设有总代理商,生意可谓兴隆。它的坎坷道路是怎样走过的?它的业绩是怎样创下的呢?

发动机制动工况将导致什么?

快速性和燃油储备行程是坦克的机动性指标,它们更多的取决于驾驶员操纵动力传动装置的熟练程度。 T-80坦克动力传动部件的结构特点是,当传动装置给坦克主动轮传递动力时,第二级串联的涡轮压气机的转子和动力涡轮之间没有运动学的联系。这就是确定燃油耗量的第一级涡轮压气机的工况。

Numerical investigation of radial inflow in the impeller rear cavity with and without baffle

In typical small engines, the cooling air for high pressure turbine （HPT） in a gas turbine engine is commonly bled off from the main flow at the tip of the centrifugal impeller. The pressurized air flow is drawn radially inwards through the impeller rear cavity. The centripetal air flow creates a strong vortex because of high inlet tangential velocity, which results in significant pressure losses. This not only restricts the mass flow rate, but also reduces the cooling air pressure for down-stream hot com- ponents. The present study is devoted to the numerical modeling of flow in an impeller rear cavity. The simulations are can＇ied out with axisymmetric and 3-D sector models for various inlet swirl ratio ,80 （0-0.6）, turbulent flow parameter 2-r （0.028-0,280） with and without baffle. The baffle is a thin plate attached to the stationary wall of the cavity, and is proved to be useful in re- ducing the pressure loss of centripetal flow in the impeller rear cavity in the current paper. Further flow details in impeller rear cavity with and without baffle are displayed using CFD techniques. The CFD results show that for any specified geometry, the outlet pressure coefficient of impeller rear cavity with or without baffle depends only on the inlet swirl ratio and turbulent flow parameter. Meanwhile, the outlet pressure coefficient of the cavity with baffle is indeed smaller than that of cavity without baffle, especially for the cases with high inlet swirl ratio. The suppression of the effect of centrifugal pumping and the mixing beween the main air which is downstream of the baffle and the recirculating flow of the vortex in the stationary cavity, which are caused by the use of baffle, are the underlying reasons that lead to the reduction of outlet pressure loss.

Design and Prototyping of Micro Centrifugal Compressor for Ultra Micro Gas Turbine

In order to establish the design methodology of an ultra micro centrifugal compressor, which is the most important component of an ultra micro gas turbine unit, a 10 times size of the final target compressor （impeller outer diameter 40 mm, corrected rotational speed 220,000 r/min） was designed. The problems to be solved for downsizing were examined and a 2-dimensional impeller was chosen as the first model due to its productivity. The conventional 1D prediction method and CFD were used. The prototyped compressor was tested by using cold air at the reduced speed of 110,000 r/min. Following to the 10 times model, a 5 times size of the final target model having fully 3-dimensional shape （impeller outer diameter 20mm, corrected rotational speed 500,000 r/min） was designed and tested by using hot gas at the reduced speed of 250,000 r/min.

Very-High-Cycle-Fatigue of in-service air-engine blades,compressor and turbine

In-service Very-High-Cycle-Fatigue(VHCF)regime of compressor vane and turbine rotor blades of the Al-based alloy VD-17and superalloy GS6K,respectively,was considered.Surface crack origination occurred at the lifetime more than 1500 hours for vanes and after 550 hours for turbine blades.Performed fractographic investigations have shown that subsurface crack origination in vanes took place inspite of corrosion pittings on the blade surface.This material behavior reflected lifetime limit that was reached by the criterion VHCF.In superalloy GS6K subsurface fatigue cracking took place with the appearance of flat facet.This phenomenon was discussed and compared with specimens cracking of the same superalloy but prepared by the powder technology.In turbine blades VHCF regime appeared because of resonance of blades under the influenced gas stream.Both cases of compressor-vanes and turbine blades in-service cracking were discussed with crack growth period and stress equivalent estimations.Recommendations to continue aircrafts airworthiness were made for in-service blades.

Unsteady Rotor-Stator Interaction in High Speed Compressor and Turbine Stages

The blade row interaction can alter the time-mean flow and therefore be of interest for aerodynamic design analysis. Whereas results within low subsonic turbomachines are quite numerous in the literature, there have been far fewer works which give results of blade row interaction within high speed cases. Two cases are related in this paper. First, the effects of an incoming wake on the rotor flow field of a transonic compressor are analyzed. The blade row interaction proved to be positive regarding the total pressure ratio, but negative regarding the losses. The second case concerns a transonic turbine. Particular emphasis is placed on the assessment of the deterministic correlations included in the Averaged Passage Equation System.

OWC air chamber performance prediction under impulse turbine damping effects

Oscillating water columns(OWCs)are most widely used in coastal wave energy conversion.The air duct opens into the atmosphere through the air turbine,which is the power take-off device,and this results in a pressure drop across the air chamber.However,because of the complex configure of the impulse turbine and its high rotation speed,it is difficult to install it in the experimental simulator and numerical model.Therefore,the turbine damping effects on the operation of the OWC air chamber are induced to predict its performance more accurately.Orifice plates are used as a substitute for the impulse turbine as it generates a similar pressure drop and power output;the experimental and numerical pressure drops and output powers are compared.A 3D numerical wave tank based on the two-phase VOF model is established using the commercial CFD code Fluent,which can predict air flow and pressure variations in the chamber and duct.Water surface elevations,air flow velocity and pressure variation inside the chamber with the orifice plate are studied numerically,and validated by the corresponding experimental data.The air chamber of the Yongsoo OWC pilot plant is used as the engineering project case.The operating performance of the air chamber installed with a 0.428D orifice plate as the substitute for the designed impulse turbine is computed and analyzed.It is found that the turbine damping effects will cause around 30%reduction in the peak values of the pneumatic energy output of the OWC air chamber in the resonant wave domain.

Analyses of surrogate models for calculating thermophysical properties of aviation kerosene RP-3 at supercritical pressures

Aviation kerosene is commonly used in combustion and regenerative engine cooling processes in propulsion and power-generation systems,including rocket,scramjet,and advanced gas turbine engines.In this paper,many surrogate models proposed in the open literature are examined for their applicability and accuracy in calculating thermodynamic and transport properties of the China aviation kerosene RP-3 at supercritical pressures,based on the extended corresponding-states methods.The enthalpy change from endothermic decomposition and low heating value from combustion of the jet fuel are also evaluated.Results from a number of simple and representative surrogate models,which contain species components ranging from 1 to10,are analyzed in detail.Data analyses indicate that a surrogate model with four species is the best choice for thermophysical property calculations under the tested conditions,with fluid temperature up to 650 K at various supercritical pressures.The surrogate model is particularly accurate in predicting the pseudo-critical temperature of aviation kerosene RP-3 at a supercritical pressure.A simple surrogate model containing the n-decane species and a surrogate model containing 10 species are the other two acceptable options.The work conducted herein is of practical importance for theoretical analyses and numerical simulations of various physicochemical processes at engine operating conditions.

Analysis of Aerodynamic Load on Straight-bladed Vertical Axis Wind Turbine

This paper presents a wind tunnel experiment for the evaluation of energy performance and aerodynamic forces acting on a small straight-bladed vertical axis wind turbine(VAWT) depending on several values of tip speed ratio. In the present study, the wind turbine is a four-bladed VAWT. The test airfoil of blade is symmetry airfoil(NACA0021) with 32 pressure ports used for the pressure measurements on blade surface. Based on the pressure distributions which are acted on the surface of rotor blade measured during rotation by multiport pressure-scanner mounted on a hub, the power, tangential force, lift and drag coefficients which are obtained by pressure distribution are discussed as a function of azimuthally position. And then, the loads which are applied to the entire wind turbine are compared with the experiment data of pressure distribution. As a result, it is clarified that aerodynamic forces take maximum value when the blade is moving to upstream side, and become small and smooth at downstream side. The power and torque coefficients which are based on the pressure distribution are larger than that by torque meter.

Experimental Study on the Inlet Fogging System Using Two-Fluid Nozzles

Large-capacity compressors in industrial plants and the compressors in gas turbine engines consume a considerable amount of power. The compression work is a strong fimction of the ambient air temperature. This increase in compression work presents a significant problem to utilities, generators and power producers when electric demands are high during the hot months. In many petrochemical process industries and gas turbine engines, the in- crease in compression work curtails plant output, demanding more electric power to drive the system. One way to counter this problem is to directly cool the inlet air. Inlet fogging is a popular means of cooling the inlet air to air compressors. In the present study, experiments have been performed to investigate the suitability of two-fluid nozzle for inlet fogging. Compressed air is used as the driving working gas for two-fluid nozzle and water at am- bient conditions is dragged into the high-speed air jet, thus enabling the entrained water to be atomized in a very short distance from the exit of the two-fluid nozzle. The air supply pressure is varied between 2.0 and 5.0 bar and the water flow rate entrained is measured. The flow visualization and temperature and relative humidity measurements are carried out to specify the fogging characteristics of the two-fluid nozzle.