The precise prediction of compressor operation within gas turbine performance simulation is key to an accurate performance simulation model. This paper describes the modeling of multistage axial-flow compressors in gas turbine performance simulations. An alternative modeling technique to the conventional characteristic based approach is presented. The purpose is an improved prediction of the co...

A probabilistic methodology to quantify the impact of geometric variability on compressor aerodynamic performance is presented. High-fidelity probabilistic models of geometric variability are derived using a principal-component analysis of blade surface measurements. This probabilistic blade geometry model is then combined with a compressible, viscous blade-passage analysis to estimate the impa...

and other process equipment in a secure web-based environment and allows users to; • Run your process more efficiently. • Improve your operating margins. • Avoid unnecessary shutdowns. • Improve your maintenance management decisions. GAS TURBINE PERFORMANCE is subject to degradation over time. When gas turbine engines are run, they become fouled with airborne contaminants such as oil, pollen, s...

Conceptual design of scroll expander and scroll compressor for 10 kW-class Stirling engine utilizing solar energy as heat source has been carried out. CO2 was chosen as the working fluid, since it is nontoxic, inflammable and it has relatively higher density among probably usable gases. Gas temperature at the expander inlet was set at 700 C, and that at the compressor inlet was at 40°C. System ...

The effect of the tip gap size on the performance of a multistage axial compressor was studied by means of computational fluid dynamics (CFD). It was found that the performance of the compressor was very sensitive to the size of the tip gap. By increasing the gap size, the stall margin value, the total pressure ratio and the compressor efficiency reduced considerably. The flow field at the tip ...

This study investigates the aerodynamic and aeroelastic characteristics of a transonic axial compressor, focusing on blade count reduced rotor behavior. The analysis is based experiments, conducted at Transonic Compressor Darmstadt test rig Technical University compulsory simulations. In order to obtain measurement data for detailed investigation, extensive steady unsteady instrumentation was a...

The paper presents the results of a stage development an analytical model for assessing impact various defects on operation axial-flow compressor. Some recommendations setting numerical models carrying out gas dynamic and strength analysis compressor stages blades with account are proposed. Verification was carried presented: also presented in paper. On basis verification some special aspects C...

Stable hydrodynamic lubrication film is needed between the tooth profiles for smooth running and long life ofa single-screw compressor. This lubrication film is easily established with "straight line enveloping screw pair" rotors, but this kind of engagement pair is very difficult to machine. In this paper it is suggested that 11 a conical surface two-envelope engagement pair '' be used as the ...

Back-to-back testing has been done using NASA fan rotor 67 in the Glenn Research Center W8 Axial Compressor Test Facility. The rotor was baseline tested with a normal industrial RMS surface finish of 0.5-0.6 μm (20-24 microinches) at 60, 80 and 100% of design speed. At design speed the tip relative Mach number was 1.38. The blades were then removed from the facility and ultrapolished to a surfa...