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Axial compressor

About: Axial compressor is a research topic. Over the lifetime, 12035 publications have been published within this topic receiving 127766 citations.


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Patent
07 Mar 1977
TL;DR: In this paper, a method and apparatus for improving the efficiency of a compressor of a gas turbine engine is described, where the inlet gas entering the compressor is stratified into two portions of different temperatures.
Abstract: A method and apparatus for improving the efficiency of a compressor of a gas turbine engine is disclosed. The inlet gas entering the compressor is stratified into two portions of different temperatures. The higher temperature gas is introduced adjacent the outer tips of the compressor blades to reduce the relative Mach number of the flow at that area.

34 citations

Patent
12 Mar 2013
TL;DR: A gas turbine engine comprises a fan including a plurality of fan blades rotatable about an axis, and a turbine section is in fluid communication with the combustor as discussed by the authors, and a geared architecture is driven by the turbine section for rotating the fan about the axis.
Abstract: A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

34 citations

Journal ArticleDOI
TL;DR: In this article, the meridional profiles of the impeller impact the overall compressor efficiency and pressure ratio at the same rotational speed, and the authors presented some recent studies of meridial impacts of the compressor.
Abstract: Centrifugal compressor developments are interested in using optimization procedures that enable compressor high efficiency and wide operating ranges. Recently, high pressure ratio and efficiency of the centrifugal compressors require impeller design to pay attention to both the blade angle distribution and the meridional profile. The geometry of the blades and the meridional profile are very important contributions of compressor performance and structure reliability. This paper presents some recent studies of meridional impacts of the compressor. Studies indicated that the meridional profiles of the impeller impact the overall compressor efficiency and pressure ratio at the same rotational speed. Proper meridional profiles can improve the compressor efficiency and increase the overall pressure ratio at the same blade back curvature.

34 citations

Journal ArticleDOI
TL;DR: In this paper, the aerodynamic stability of a long, thin cylindrical shell with the outer surface exposed to an inviscid, helical flow of ah* is investigated.
Abstract: The aeroelastic stability of a long, thin cylindrical shell with the outer surface exposed to an inviscid, helical flow of ah* is investigated. The cylinder behavior is described by classical shell equations, whereas the aerodynamic forces are described by the linearized potential theory. The approach that is used herein examines the nature of stability of the system when the system is "slightly" perturbed from its initial equilibrium state. In this paper, numerical results are presented only for the special case of swirl flow around a nonrotating shell, i.e., the axial flow velocity is set to zero. These results indicate that traveling wave type of flutter can be caused by coalescence of backward and forward traveling waves. Two approximate theories are presented and the results are compared.

34 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202398
2022304
2021217
2020288
2019316
2018353