新型封严涂层高温高速磨耗试验机的研制

为模拟航空涡轮发动机气路封严配副在工作状态下的磨损磨耗现象,研究封严涂层的可磨耗性能,研制了1套新型的可磨耗性能评价试验器。该试验器采用叶片-涂层刮削式磨耗副,使用模拟轮盘带动叶片高速旋转实现叶尖的切线速度;采用封严涂层试样径向进给以模拟叶片刮削切入;使用压电石英晶体3向测力仪定量测量瞬态刮削力;采用高速高温火焰加热试样。考核结果表明:试验器能够完成叶尖切线速度为0~300 m/s、进给速率为1.5~2025μm/s、加热温度为20~800℃条件下的磨耗试验,试验效果良好,数据稳定可靠。     

Generalization of experimental data on two-phase critical efflux through axisymmetric channels

The results of studying the characteristics of a two-phase flow being formed during adiabatic water efflux through axisymmetric cylindrical and Laval nozzle channels are presented. Experiments were carried out with saturated water in the range of initial pressures 0.6–4.0 MPa. The fluid efflux was performed into the air with atmospheric pressure. The generalizing relations for calculating thrust pulse and critical flowrate were obtained.     

Some qualitative manifestations of the physical libration of the Moon by observing stars from the lunar surface

Targets and problems of the future Japanese project ILOM (In situ Lunar Orientation Measurement), which is planned to be realized as one kind of observations of lunar rotation at the second stage of SELENE-2 mission, are briefly described in the article. Inverse problem of lunar physical libration is formulated and solved. Accuracy of libration angles depending on accuracy of measuring selenographic coordinates is estimated. It is shown that selenographic coordinates of polar stars are insensitive to longitudinal librations τ(t). Comparing coordinates calculated for two models of a rigid and deformable Moon is carried out and components sensitive to Love number k₂ and to anelastic time delay are revealed.     

Probabilistic estimation of fulfilling favorable conditions to realize the gravity-sensitive processes aboard a space laboratory

We consider a probabilistic estimation of microaccelerations being produced in the inboard environment of an orbital laboratory as a random process; based on this estimation we analyzed a probability of fulfilling the favorable conditions to realize gravity-sensitive processes. The approach suggested can be applied when designing a space laboratory to meet the requirements for the microaccelerations inside the working zone of technological equipment.     

Computational analysis of strength,stability, and durability for gas turbine engine exhaust frame

A computational technique, developed for analysis of strength, stability and low-cycle durability of GTE exhaust frame complex structure under operational and emergency loads is described. The presented technique, based on the ANSYS and STAR-CD engineering analysis software, and self-design software can improve the accuracy and efficiency of calculations, and reduce efforts on finite element mesh development, performing calculations and processing of results.     

Aerodynamic refinement of turbine cascades

Based on the experimental data, a dependence of the minimal friction losses in cascades was obtained. A turbine stage efficiency gain as a result of cascade improvement over the last three decades of the 20th century was estimated by this dependence.     

Prediction of aerodynamic characteristics of an aircraft model with and without winglet using fuzzy logic technique

This paper describes the potentials of an aircraft model without and with winglet attached with NACA wing No. 65-3-218. Based on the longitudinal aerodynamic characteristics analyzing for the aircraft model tested in low subsonic wind tunnel, the lift coefficient (CL) and drag coefficient (CD) were investigated respectively. Wind tunnel test results were obtained for CL and CD versus the angle of attack α for three Reynolds numbers Re (1.7×¹⁰⁵, 2.1×¹⁰⁵, and 2.5×¹⁰⁵) and three configurations (configuration 1: without winglet, configuration 2: winglet at 0° and configuration 3: winglet at 60°). Compared with conventional technique, fuzzy logic technique is more efficient for the representation, manipulation and utilization. Therefore, the primary purpose of this work was to investigate the relationship between lift coefficients and drag coefficients with free-stream velocities and angle of attacks, and to illustrate how fuzzy expert system (FES) might play an important role in prediction of aerodynamic characteristics of an aircraft model with the addition of winglet. In this paper, an FES model was developed to predict the lift and drag coefficients of the aircraft model with winglet at 60°. The mean relative error of measured and predicted values (from FES model) were 6.52% for lift coefficient and 4.74% for drag coefficient. For all parameters, the relative error of predicted values was found to be less than the acceptable limits (10%). The goodness of fit of prediction (from FES model) values were found as 0.94 for lift coefficient and 0.98 for drag coefficient which were close to 1.0 as expected.