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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
20 Dec 2004
TL;DR: In this article, the leading edge and root of an axial compressor are revealed, along with a dovetail attached to a side of the platform opposite to the airfoil, and a slot in the neck and generally parallel to the platform.
Abstract: A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.

41 citations

Journal ArticleDOI
TL;DR: In this paper, three-dimensional numerical simulations of tornado-like vortices are presented of particular interest is a regime with multiple suction vortice within a larger cyclone, where the authors assess the magnitude and mechanism by which low pressure is sustained in a suction vortex.
Abstract: Three-dimensional numerical simulations of tornado-like vortices are presented Of particular interest is a regime with multiple suction vortices within a larger cyclone The simulations are designed to assess the magnitude and mechanism by which low pressure is sustained in a suction vortex The pressure in the transient suction vortices can be nine times that supported by the buoyancy of the ‘storm’ The low pressure is sustained by transient axial flow; the pressure-gradient force along the axis is balanced by the inertia of the axial flow, rather than by buoyancy

41 citations

Journal ArticleDOI
01 May 1999
TL;DR: In this paper, the basic principles and rules associated with the design of axial flow compressors, principally for aero-engines, as well as the practical c... are discussed.
Abstract: The purpose of this paper is to set out some of the basic principles and rules associated with the design of axial flow compressors, principally for aero-engines, as well as the practical c...

41 citations

Journal ArticleDOI
TL;DR: The relative importance of convection by secondary flows and diffusion by turbulence as mechanisms responsible for mixing in multistage axial-flow compressors has been investigated by using the ethylene tracer-gas technique and hot-wire anemometry as discussed by the authors.
Abstract: The relative importance of convection by secondary flows and diffusion by turbulence as mechanisms responsible for mixing in multistage, axial-flow compressors has been investigated by using the ethylene tracer-gas technique and hot-wire anemometry. The tests were conducted at two loading levels in a large, low-speed, four-stage compressor. The experimental results show that considerable cross-passage and spanwise fluid motion can occur and that both secondary flow and turbulent diffusion can play important roles in the mixing process, depending upon location in the compressor and loading level. In the so-called freestream region, turbulent diffusion appeared to be the dominant mixing mechanism. However, near the endwalls and along airfoil surfaces at both loading levels, the convective effects from secondary flow were of the same order of magnitude as, and in some cases greater than, the diffusive effects from turbulence. Calculations of the secondary flowfield and mixing coefficients support the experimental findings.

41 citations

Patent
31 May 2013
TL;DR: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelles compartment of the gas turbine.
Abstract: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.

41 citations


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