Gas compressor

About: Gas compressor is a research topic. Over the lifetime, 91817 publications have been published within this topic receiving 552209 citations.

Small Turbomachinery Compressor and Fan Aerodynamics

Abstract: This paper discusses aerodynamic considerations in the design of small turbomachinery axial and centrifugal compressors and fans. Test results are presented to show the effect of scaling on compressor performance. Correlations are presented which relate compressor efficiency to Reynolds Number and clearance. It is shown that clearance effects are more prominent when scaling designs, and Reynolds Number effects are more prominent as density is lowered.

Design and Analysis of Multiplier Using Approximate 15-4 Compressor

Abstract: This paper presents the design of approximate 15-4 compressor using 5-3 compressors as basic module. Four different types of approximate 5-3 compressors are used in a 15-4 compressor for less power consumption and high pass rate. We have analysed the results in all the cases. A $16 \times 16$ bit multiplier is simulated using the proposed 15-4 compressor. Simulation results show that the multipliers with proposed approximate compressors achieve significant improvement in power as compared to the multipliers with accurate 15-4 compressor. Pass rate of the proposed multipliers are high as compared to other existing approximate multipliers. Finally, the proposed multiplier is used in image processing applications, where the peak signal to noise ratio of the image is measured. Quality of the image is compared with an accurate multiplier and the obtained results show that our proposed multiplier performs better than existing approximate multiplier.

High bypass turbofan engine having a partially geared fan drive turbine

Abstract: The present invention provides a high bypass turbofan engine configuration wherein a fan drive turbine is divided into first and second turbine sections mounted for independent rotation within the engine frame. The first, higher pressure, higher speed turbine section is coupled to the fan section drive shaft via a gear box which reduces the rotational speed of the power delivered by the higher pressure first turbine section to match the design rotational speed of the fan section. The second turbine section, having a larger diameter and lower rotational speed as compared to the first turbine section, is directly connected to the fan section and drives the fan section at the same rotational speed as that of the second turbine section. In this manner, the fan drive shaft horsepower is provided while reducing the weight and size of the necessary gearing between the fan drive turbine and the fan. The weight and size of the fan drive turbine and the booster compressor are also reduced.

Interstage cooled turbine engine

Abstract: A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.

An Evaluation of the Effects of Water Injection on Compressor Performance

Abstract: The injection of water droplets into compressor inlet ducting is now commonly used as a means of boosting the output from industrial gas turbines. The chief mechanisms responsible for the increase in power are the reduction in compressor work per unit flow and the increase in mass flow rate, both of which are achieved by evaporative cooling upstream of and within the compressor. This paper examines the impact of such evaporative processes on compressor operation, focussing particular attention on cases with substantial over-spray — i.e., for which significant evaporation takes place within the compressor itself, rather than in the inlet. A simple numerical method is described for the computation of wet compression processes, based on a combination of droplet evaporation and mean-line calculations. The method is applied to a “generic” compressor geometry in order to investigate the nature of the off-design behaviour that results from evaporative cooling. Consideration is also given to the efficiency of the compression process, the implications for choking and stall, and the magnitude of the thermodynamic loss resulting from irreversible phase change.Copyright © 2003 by ASME