Stages Of Axial Flow Compressor - amazonia.fiocruz.br

Stages Of Axial Flow Compressor Video

FPE EP 65 WORKING OF AXIAL FLOW COMPRESSOR WITH STAGE VELOCITY AND COMBINED TRIANGLE

Stages Of Axial Flow Compressor - really. All

Either your web browser doesn't support Javascript or it is currently turned off. In the latter case, please turn on Javascript support in your web browser and reload this page. Data from a two-stage axial vapor cryogenic compressor on the dual-fuel diesel—electric DFDE liquefied natural gas LNG carrier were measured and analyzed to investigate compressor energy and exergy efficiency in real exploitation conditions. The running parameters of the two-stage compressor were collected while changing the main propeller shafts rpm. As the compressor supply of vaporized gas to the main engines increases, so does the load and rpm in propulsion electric motors, and vice versa. The results show that when the main engine load varied from 46 to 56 rpm at main propulsion shafts increased mass flow rate of vaporized LNG at a two-stage compressor has an influence on compressor performance. Higher exergy efficiency is achieved at lower ambient temperatures. Stages Of Axial Flow Compressor

For a given degree of reaction and value of Va or flow rate, a choice can be made of the stagger angle or setting of the blades.

Stages Of Axial Flow Compressor

From the consideration of two defining equations:. For fixed values of R and Va, a selection of a value of a2 corresponding to a value of stagger angle fixes a limiting value of X] from cascade data. Thus the blade speed, u, is determined and then the energy transfer E is found. Therefore, high stagger blades tend to have a steeper characteristic curve. However, another feature of increased stagger that cannot be demonstrated simply, but requires use of cascade data, is that the design point or point of maximum efficiency on the characteristic curve is at a value of mass flow somewhat greater than that for maximum pressure ratio. As a result, the design point is further away from the surge mass Flos and allows more flexibility on that part of the characteristic curve.

Low stagger, on Stages Of Axial Flow Compressor other hand, tends to place the FFlow point closer to the surge point.

While this approach offers more flexibility for increased mass flow, some efficiency may be sacrificed to avoid operating too near surge. Since for a given value of Va the blade speed must be greater for high stagger, the energy transfer is increased because. Because the relative velocity is higher, the Mach number may be prohibitive, or alternatively thinner blades may have to be used in order to obtain a higher critical Mach number for the drag value.

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Thinner blades would require larger chords Stsges order to maintain reasonable levels of bending stress. As a net result, the overall length would not decrease in proportion to the decrease source number of stages. The assumption for this result was that the drag-lift ratio was constant. In actual practice, cascade data indicate that drag-lift is not constant but increases as a2 increases. Compressor performance can be changed by alteration of blade stagger. This is usually done by changes of stator stagger in preference of changes to the rotor.

1. Introduction

This can be accomplished on both process compressors and gas turbines, including the aircraft engine by use of Stages Of Axial Flow Compressor stator vane control. While the mechanism is somewhat complex, it gives the axial compressor, with its inherently steep pressure-volume curve, the ability to be matched to a changing load without changing the speed. Figure is a pressure-volume chart for an axial compressor with a partial stator vane control only a portion of the stator blades is movable. Figure Pressure-volume chart for an axial-flow compressor with partial stator vane control. Courtesy ofA-C Compressor Corporation.

Beyond Discovery Alternative Energy. Stagger Wed, 15 Feb Centrifugal Compressors.]