The Experts below are selected from a list of 48 Experts worldwide ranked by ideXlab platform

Dai Jing-min - One of the best experts on this subject based on the ideXlab platform.

  • Research on Genetic Algorithm for Plume Temperature of Solid Propellant Rocket Engine
    Journal of Combustion Science and Technology, 2006
    Co-Authors: Dai Jing-min
    Abstract:

    The plume temperature is an important parameter, for solid propellant rocket Engines and it is useful for determining the combustion process of the Engine. Plume temperatures of a mounted solid propellant rocket Engine were measured by multi-wavelength pyrometer. According to the reference temperature model of multi-spectral thermometry and the obtained experimental data, the relationship between the emissivity and wavelength of the plume was predicted. The relationship was nonlinearly fitted and optimized by genetic algorithm to calculate plume temperatures and emissivities. The experimental results show that the temperature differences between the calculated values and the theoretical ones provided by the rocket Engine Designer are within 20 K. Therefore, this method is applicable to measure the plume temperatures of solid propellant rocket Engines.

Sun Xiao - One of the best experts on this subject based on the ideXlab platform.

  • RESEARCH ON THE DATA PROCESSING METHOD OF SOLID PROPELLANT ROCKET Engine PLUME TEMPERATURE
    Journal of Infrared and Millimeter Waves, 2003
    Co-Authors: Sun Xiao
    Abstract:

    Considering the characteristics of the plume temperature measurement of solid propellant rocket Engine, a new emissivity assumption was presented. Based on the assumption, a new data processing method of the multiwavelength pyrometer was introduced. By processing the measured data of the multiwavelength pyrometer at two different time, the true temperatures and spectral emissivities at two different time can be simultaneously calculated. The experimental results show that the temperature differences between the calculated values and the theoretical ones provided by the rocket Engine Designer are within ±20K. The above mentioned method is a practical data processing method of solid propellant rocket Engine plume temperature.

Shiau Chao-cheng - One of the best experts on this subject based on the ideXlab platform.

  • Measurements and Analysis of Film Cooling On Gas Turbine Vane Endwall and Suction Surface
    2020
    Co-Authors: Shiau Chao-cheng
    Abstract:

    Researchers in gas turbine field take great interest in the cooling performance on the first-stage vane in a more authentic configuration because of the complicated flow characteristics and intensive heat load that comes from the exit of the combustor. With the three-dimensional vane geometry and the corresponding wind tunnel design, a more realistic flow field can thus be simulated. The annular sector cascades were therefore selected and the Pressure-sensitive paint (PSP) technique was used to study the film cooling effectiveness on the endwall and vane’s suction surface. On the other hand, PSP technique was also applied on a linear cascade to study the effect of upstream leakage injection angle on various endwall film cooling designs. In the first part of the study, full-scale turbine vanes were used to construct a three-vane annular sector cascade. Two kinds of film cooling designs are attained through the layback fan-shaped and cylindrical holes dispersed on the vanes and endwalls. This study targets the film cooling effectiveness comparison on the inner endwall of turbine vane. Tests were performed under the mainstream Reynolds number 350,000; the related inlet Mach number is 0.09. Coolant-to-mainstream mass flow ratios (2%, 3%, 4%) and density ratios (1.0, 1.5) were examined. The results provide the gas turbine Engine Designer a direct performance comparison between two film-hole configurations on a full-scale vane endwall under the same amount of coolant usage. The second part of the study is focused on the film cooling on the suction surface of a turbine vane under transonic flow condition. The experiments were performed in a five-vane annular sector cascade. The exit Mach numbers were varied from 0.7, 0.9, and 1.1. Density ratios, ranging from 1.0, 1.5 to 2.0; three blowing ratios ranging from 0.7, 1.0, 1.6 for the suction surface were studied. Three rows of radial-angle cylindrical holes around the leading edge and two rows of compound-angle shaped holes on are the suction surface of the test vane. The results demonstrate the mix effects of coolant amount, density ratio, and exit Mach number on the film cooling as well as its interaction with the potential shock wave. The third part of the study is to investigate the effects of upstream leakage injection angle on film cooling effectiveness of a turbine vane endwall with various film-hole designs. To simulate the upstream leakage flow between the combustor and the turbine vane, three potential leakage injection angles were studied: 30 degrees, 40 degrees, and 50 degrees. To explore the optimum endwall cooling design, five different film-hole patterns were tested: axial row, cross row, cluster, mid-chord row, and downstream row. Experiments were conducted in a four-passage linear cascade at the exit isentropic Mach number 0.5 corresponding to the inlet Reynolds number 380,000 based on turbine vane axial chord length. For a fair performance comparison, the coolant was fixed at mass flow ratio 1% and density ratio 1.5. The results provide the gas turbine Designers a valuable information on how to select the best endwall cooling pattern with minimum cooling air consumption over a range of upstream leakage injection angles

A. Kumarasamy - One of the best experts on this subject based on the ideXlab platform.

  • Simulation of a Diesel Engine with Variable Geometry Turbocharger and Parametric Study of Variable Vane Position on Engine Performance
    Defence Science Journal, 2017
    Co-Authors: Anand Mammen Thomas, J Jensen Samuel, Mahulkar P. Pramod, A. Ramesh, Ramachandran Murugesan, A. Kumarasamy
    Abstract:

    Modelling of a turbocharger is of interest to the Engine Designer as the work developed by the turbine can be used to drive a compressor coupled to it. This positively influences charge air density and Engine power to weight ratio. Variable geometry turbocharger (VGT) additionally has a controllable nozzle ring which is normally electro-pneumatically actuated. This additional degree of freedom offers efficient matching of the effective turbine area for a wide range of Engine mass flow rates. Closing of the nozzle ring (vanes tangential to rotor) result in more turbine work and deliver higher boost pressure but it also increases the back pressure on the Engine induced by reduced turbine effective area. This adversely affects the net Engine torque as the pumping work required increases. Hence, the optimum vane position for a given Engine operating point is to be found through simulations or experimentation. A thermodynamic simulation model of a 2.2l 4 cylinder diesel Engine was developed for investigation of different control strategies. Model features map based performance prediction of the VGT. Performance of the Engine was simulated for steady state operation and validated with experimentation. The results of the parametric study of VGT’s vane position on the Engine performance are discussed.

Slava Gerovitch - One of the best experts on this subject based on the ideXlab platform.

  • Engine Designer Anatoliy Daron
    Voices of the Soviet Space Program, 2014
    Co-Authors: Slava Gerovitch
    Abstract:

    Anatoliy Davidovich Daron was born on April 26, 1926, in Odessa, Ukraine. In 1948 he graduated from the Moscow Aviation Institute as an Engineer specializing in liquid propellant rocket Engines. After graduation he worked for 50 years at the Experimental Design Bureau No. 456 (OKB-456), led by the Chief Designer of Rocket Engines Valentin Glushko. Daron was the lead Designer of the liquid propellant rocket Engines RD-107 and RD-108 for the R-7, the first Soviet ICBM. These Engines launched Sputnik and boosted into space all Soviet piloted spacecraft—Vostok, Voskhod, and Soyuz. Daron also served as the lead Designer of Engines for the R-9 silo-based ICBM and for the UR-700 rocket. He worked as the head of the design department at Glushko’s design bureau. Daron is a doctor of technical sciences and the author of more than 300 technical articles and patents. He also has a number of publications on the history of Engine design at OKB-456.1 He is the recipient of numerous honors, including the Order of Lenin, from the Soviet government for the launch of Sputnik, for the first human spaceflight of Yuriy Gagarin, and for participation in joint US-Soviet space programs. Dr. Daron has emigrated to the United States and currently lives in Brighton, Massachusetts. Open image in new window Figure 3.1 Anatoliy Daron (courtesy Anatoliy Daron).